ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ

... 1. Газотурбинный двигатель (1; 21), содержащий приспособление для выхлопов (4) с внутренним контуром выхлопа двигателя, имеющее профилированный центр (6) и выходное сопло (7), вокруг профилированного центра (6), выполненного для образования канала (прохода) (2) между ними, имеющего область плоскости (5) перемешивания, при этом приспособление для выхлопов (4) отличается тем, что оно включает в себя механизм (10) осевого смещения для создания относительного смещения между выходным соплом (7) и профилированным центром (6) для изменения размера области плоскости (5) перемешивания. ! 2. Двигатель по п.1, в котором механизм смещения закреплен на выходном сопле (7) для создания смещения. ! 3. Двигатель по п.1 или 2, в котором приспособление включает в себя второй контур (19) двигателя вокруг выходного сопла (7), площадь (область) плоскости (5) перемешивания включает площадь (5а) поперечного сечения зазора между профилированным центром (6) и выходным соплом (7) в сочетании с площадью (5b) поперечного ...

Регулируемое сопло реактивного двигателя

Variable Kerntriebwerksverkleidung für Turbofan-Triebwerke mit hohem Nebenstromverhältnis

Beschrieben wird eine Kerntriebwerksverkleidung für Turbofan-Triebwerke mit hohem Nebenstromverhältnis, umfassend eine Vielzahl von beweglichen Segmenten 11, 12, welche das Kerntriebwerk 7 im Auslassbereich des Nebenstromkanals umhüllen, wobei die zur Fanleitschaufel 3 weisenden Segmente 11 und die zum Auslassbereich des Nebenstromkanals weisenden Segmente 12 eine Vielzahl von Überlappungsbereichen 21, 22 ausbilden, wobei die Überlappungsbereiche sowohl in Umfangsrichtung der Kerntriebwerksverkleidung als auch in axialer Richtung hierzu ausgebildet sind. Diese Erfindung nutzt den leeren Bauraum 17 zwischen der inneren Düsenkontur des Nebenstromkanals und dem Kerntriebwerk 7, der bei Turbofan-Flugtriebwerken mit großem Nebenstromverhältnis vorhanden ist. Die Erfindung stellt somit eine Vorrichtung bereit, welche die Veränderung der inneren Kontur des Nebenstromkanals durch sich überlappende Sektorprofile der Düse bewirkt.

Exhaust nozzle for jet engine, has centrally arranged sliding cone to change nozzle cross-section, where extension tube is provided to guide sliding cone

The exhaust nozzle (2) has a centrally arranged sliding cone (13) to change the nozzle cross-section, where an extension tube is provided to guide the sliding cone. A drive device (15) is provided for axial adjustment of the sliding cone relative to the nozzle opening (3). The drive device is arranged for axial adjustment of sliding cone relative to the nozzle opening in the engine axis (4).

An Improved Form of Combination Oil Filter and Pressure Release Valve for Adaptation to existing Types of Internal Combustion Engines.

... 111,195. Chinn, C. G. Jan. 10, 1917. Force-feed lubricating; filtering lubricant.-In a pump lubricating-system for internal-combustion engines, an oil filter is combined with a relief valve. Oil forced into a casing at 2 passes through a wire-gauze filter 5 and leaves the casing by a duct 10. A relief passage 13 fitted with a valve 11 allows surplus oil to return to the base sump.

A device for regulating the outlet sectional area of a jet propulsion nozzle

... 616,349. Jet-propulsion nozzles. SOC. RATEAU, and ANXIONNAZ, R. Nov. 16, 1945, No. 30845. Convention date, Feb. 6. [Class 110 (iii)] In a variable area jet propulsion nozzle of the kind comprising an auxiliary nozzle member telescopically disposed with reference to a main nozzle, the auxiliary nozzle has an outlet area smaller than that of the main nozzle and is displaceable along the axis of the main nozzle so that the whole of the gases pass through the auxiliary nozzle when it is in the position giving the minimum exit area. The propulsion nozzle shown has a main nozzle e along the axis of which the auxiliary nozzle f is movable by means of a control rod h. When the rod h is fully extended, the auxiliary nozzle which has an exit area less than that of the nozzle e forms the sole propulsion nozzle. Where a large variation in area is required, several concentric auxiliary nozzles may be used.

Improvements in or relating to gas turbine power plants

... 637,917. Jet propulsion plant. WESTING- HOUSE ELECTRIC INTERNATIONAL CO. May 27, 1948, No. 14337. Convention date, June 5, 1947. [Class 110(iii)) In a gas turbine plant in which the area of the discharge nozzle is varied by moving a tailpiece axially with respect to the main portion of an inner core structure, the tailpiece is moved by means including a cable or cables associated with a rotary element or elements carried by or within the main portion of the' inner core structure. The variable area jet propulsion nozzle shown is formed by a movable tailpiece 42 mounted on the end of a push rod 50 supported by a structure 29 and a bushing 25. The push rod is operated by endless cables 38 wound around drums 36, 37 and looped around idler pulleys 34. Rotation of the drums 36, 37 by a pneumatic, hydraulic or electric motor moves the cables 38 and operates the tailpiece 42. A cylindrical element 26 reinforces and forms a heat insulating shield for the frusto-conical support member 23. Pins 62 ...

PROPULSION NOZZLE FOR GAS TURBINE ENGINE

Thrust vectoring gas turbine engine nozzle

An optoelectronic transceiver 10 having a small footprint and has a laser diode package (56, Fig. 3) contained within a subassembly mounted within a housing 20 of the transceiver. The housing 20 may include latches for retaining subassemblies therein. The subassemblies may include first apertures for receiving mounting pins 80, 81 to lock the subassemblies within the housing. Plug latch members may be mounted onto the subassemblies. Optical transmitter and receiver circuits and one row of nine contacts 76 are mounted to a printed circuit board 63 mounted within the housing of the transceiver. The housing 20 has a fibre optic receptacle 42, 44 at its first end 40, and may contain a photodiode package (85, Fig. 3). ...

Nozzle capable of varying the direction of discharge of fluid therefrom

PROPULSION NOZZLE

VARIABLE AREA NOZZLE FOR A GAS TURBINE ENGINE

... 1362106 Variable area jet nozzles ROLLSROYCE (1971) Ltd 12 Dec 1972 57183/72 Heading F1J The invention relates to a variable area nozzle for a gas turbine engine the nozzle being movable between a first minimum area position shown in Fig. 1 and a second maximum area position shown in Fig. 2. The nozzle assembly shown is for a gas turbine ducted fan engine and comprises an outer casing 13, an intermediate casing 14 and a central plug assembly which together define an outer duct 11 for fan air-flow and an inner duct 12 for turbine exhaust gas flow. The central plug comprises a fixed central portion 16 in the form of a duct which is secured to the intermediate casing 14 by support struts 17, a core member 15 on which a series of flap members 25 are pivotally mounted and which engage at their downstream ends 27 with the forward edge of the central portion 16, and a downstream plug member 18 which is formed with a recess 19 which engages the downstream end of the central portion 16. The plug ...

Improvements in or relating to ducted-fan gas turbine jet propulsion engines

... 875,496. Gas turbine jet propulsion plant. GENERAL ELECTRIC CO. Dec. 7, 1959, No. 41473/59. Class 110 (3). A ducted fan gas turbine jet propulsion engine comprising a gas turbine engine disposed within a substantially cylindrical outer casing to form a by-pass duct which is provided with combustion means and an exhaust nozzle, has control vanes to control the air flow to the gas turbine engine to permit selective operation of the engine as a ducted fan engine or as a ram jet and means to vary the configuration of the by-pass exhaust nozzle in accordance with the position of the control vanes. A compressor 10 supplies combustion air to combustion equipment 11 feeding a turbine 12 driving the compressor. The exhaust of the turbine 12 is used to drive a turbine 14 before passing through a duct 20 which terminates in a convergent nozzle 24. The turbine 14 drives fan blades 15 arranged in a duct 16 formed by a casing 17 extending around the inner casing 18. Combustion means 27 is provided in ...

Jet propulsion plant

... 805,418. Jet-propulsion plant. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. Oct. 2, 1956 [Oct. 5, 1955], No. 28439/55. Class 110 (3). [Also in Group XII] A jet-propulsion plant comprises a main duct with an air intake at its forward end and a propulsion nozzle at its rearward end, a dynamic compressor arranged within the duct to compress the air therein, a source of high velocity gas independent of the atmospheric air connected to discharge through a secondary duct into the main duct downstream of the compressor and a turbine located in the secondary duct and forward of and in driving connection with the compressor. In the arrangement shown an annular main duct 1 extends between an intake 4 and a variable area propelling nozzle 5. An axial flow air compressor 6 which compresses air in the main duct 1 is driven by a turbine 17 having two-rows of velocity compounded impulse blading through shafts 28, 30 and reduction gearing 29. The turbine 17 is supplied with working fluid by a combustion chamber ...

JET ENGINE NOISE SUPPRESSION SYSTEM

"JET ENGINE NOISE SUPPRESSION SYSTEM" Abstract of the Disclosure A noise suppression system for use with a jet aircraft engine having a plug support cylinder affixed to the engine, a tubular ejector shroud affixed to the engine and encompassing the plug support, the shroud having a reduced internal diameter adjacent the aft end and a plurality of spaced apart blow-in openings formed circumferentially about the shroud forward end providing passageways for the entrance of ambient air from the exterior to the interior of the shroud. A blow-in door is secured to the shroud for opening and closing each of the blow-in openings. A translating plug is supported on the plug support cylinder and is positionable between a forward position And an aft position and forms an annular exhaust nozzle between the exterior of the plug and the interior of the aft end of the shroud. A daisy mixing nozzle is positioned within the shroud aft of the blow-in doors, the nozzle being configured of a plurality of lobes providing undulating interior and exterior surface. When the plug is in the forward position the blow-in doors are open permitting ambient air to mix with exhaust gas from the jet engine and the nozzle area is enlarged producing lower gas velocities and lower sound intensities. When the plug is in the aft position, the blow-in doors are closed and the nozzle area is reduced providing higher gas velocities for increased thrust with some increase in sound intensity.

TURBOFAN ENGINE COWL ASSEMBLY AND METHOD OF OPERATING THE SAME

An inner core cowl baffle assembly (100) for a turbofan engine assembly (10) including a core gas turbine engine (20), a core cowl (22) which circumscribes the core gas turbine engine, a nacelle (24) positioned radially outward from the core cowl, and a fan nozzle duct (26) defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes a first core cowl baffle (101) coupled to a portion (19) of the core cowl within the fan nozzle duct, a second core cowl baffle (102) coupled to a portion (21) of the core cowl and positioned a distance radially inward from the first core cowl baffle, and an actuator assembly (110) configured to vary the throat area of the fan nozzle duct by selectively repositioning the second core cowl baffle with respect to the first core cowl baffle.

NOZZLE AND AUXILIARY INLET ARRANGEMENT FOR GAS TURBINE ENGINE

DUAL-MODE PLUG NOZZLE

A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a maximum diameter section. An inner shroud surrounds the centerbody and cooperates with the centerbody to define the throat of the nozzle. An outer shroud surrounds the inner shroud and cooperates with the centerbody to define the exit area of the nozzle. Both shrouds are independently translatable to provide independent control of the nozzle throat area and the nozzle expansion ratio. Additional actuation of the inner shroud results in the throat A8 being disposed upon a fully forward portion of the centerbody, said fully forward shroud disposition being more forward than over the maximum diameter section. The nozzle may further comprise independent translation of the centerbody 32 with respect to the shrouds.

Gasturbinenaggregat.

Luftfahrzeug-Strahlvortriebsanlage.

pulse explosion drive.

Eine Vorrichtung dient zum wiederholten Erzeugen von Explosionen. Sie weist auf: einen Explosionsraum (11), eine Zufuhrleitung zum Zuführen eines fliessfähigen explosionsfähigen Materials, eine Ablassöffnung zum gerichteten Ablassen eines durch Zündung des explosionsfähigen Materials im Explosionsraum (11) erzeugten Gasdrucks, und ein bewegliches Verschlusselement (21) zum teilweisen oder gänzlichen Verschliessen der Ablassöffnung (17). Dabei weist die Vorrichtung eine Austrittsdüse (15) mit einer Düseneintrittsfläche (13) und einer Düsenaustrittsfläche (14) auf, sowie eine Stelleinrichtung (23). Die Stelleinrichtung (23) ist dazu ausgebildet, nach einem Öffnen der Ablassöffnung (17) und einem Ausströmen von Explosionsgasen durch die Austrittsdüse (15) ein Flächenverhältnis zwischen der Düseneintrittsfläche (13) und der Düsenaustrittsfläche (14) einzustellen, welches mindestens annähernd einem idealen Flächenverhältnis zur Erzeugung einer maximalen Austrittsgeschwindigkeit der Explosionsgase ...

Pulse drive.

Eine Vorrichtung dient zum wiederholten Erzeugen von Explosionen, insbesondere zum Antrieb eines Luftfahrzeuges. Sie weist auf: eine Brennkammer (21); mindestens eine Zufuhrleitung zum Zuführen eines fliessfähigen explosionsfähigen Materials oder von Komponenten, die bei Vermischung ein explosionsfähiges Material bilden, zur Brennkammer (21); eine Ablassvorrichtung zum gerichteten Ablassen eines durch Zündung des explosionsfähigen Materials in der Brennkammer (21) erzeugten Gasdrucks; ein bewegliches Düsenregelelement (26) zum teilweisen oder gänzlichen Verschliessen der Ablassvorrichtung; ein Stellelement (25), welches dazu ausgebildet ist, nach einem Öffnen der Ablassvorrichtung und während eines Ausströmens von Explosionsgasen durch die Ablassvorrichtung die Ablassvorrichtung weiter zu öffnen. Dabei weist die Ablassvorrichtung mehrere Teildüsen zum Ablassen des Gasdrucks auf und ist eine Stellung der Teildüsen durch das Stellelement (25) einstellbar.

Partitioned cooling axial-symmetric plug-type spray pipe

Supercritical medium metering method and adjusting device

The invention discloses a supercritical medium metering method and an adjusting device, and the metering method comprises the steps: S1, obtaining the real-time state information of a metering medium, and judging the real-time state of the metering medium; s2, the volume flow of the metering medium is metered according to different real-time states of the metering medium; and S3, calculating the mass flow through the medium density rho, the medium temperature and the measured volume flow. The problem that an existing supercritical medium adjusting method is narrow in application range can be solved.

Conduit with variable profile

Process of obtaining pushed by a jet of fluid and conduit of pushed for its implementation

La tuyère de poussée comprend un carter, un corps central disposé à l'intérieur du carter, une enveloppe entourant le corps central en formant avec ce dernier un passage annulaire ainsi que des lèvres de sortie de l'enveloppe délimitant avec la base aval du corps centrai dans le passage annulaire une partie à section contractée en convergent-divergent d'orientation radiale et à sortie axiale. La base aval (2) du corps central (1) est plane et est montée de manière à pouvoir être déviée par rapport à sa position perpendiculaire à l'axe longitudinal de la tuyère, l'enveloppe (5) étant dotée de lèvres de sortie profilées (6), susceptibles d'être déplacées axialement par des vérins (9) pour faire varier l'aire de la section contractée (7) de la tuyère. Application à la propulsion des aéronefs à grande maniabilité. The thrust nozzle comprises a casing, a central body arranged inside the casing, a casing surrounding the central body, forming with the latter an annular passage as well as outlet lips of the casing delimiting with the downstream base of the body. centered in the annular passage a portion with a section contracted in convergent-divergent orientation radially and axially outlet. The downstream base (2) of the central body (1) is flat and is mounted so as to be able to be deviated from its position perpendicular to the longitudinal axis of the nozzle, the casing (5) being provided with outlet lips sections (6), capable of being displaced axially by jacks (9) to vary the area of the contracted section (7) of the nozzle. Application to the propulsion of highly maneuverable aircraft.

PROPELLING NOZZLE FOR A HYPERSONIC REACTOR.

Une tuyère pour un réacteur hypersonique (1) comportant un corps central (17) en forme de champignon susceptible d'être déplacé en direction axiale, est pourvue de deux volets de détente (18, 19) qui sont montés de manière pivotante pour pouvoir être basculés l'un vers l'autre pour des nombres de Mach de vol faibles et l'un en s'écartant de l'autre pour des nombres de Mach de vol élevés. Ceci permet d'obtenir une grande variation de la divergence de la tuyère (7) tout en assurant une grande rigidité mécanique et des fuites faibles. A nozzle for a hypersonic reactor (1) having a mushroom-shaped central body (17) capable of being displaced in the axial direction, is provided with two expansion flaps (18, 19) which are pivotably mounted so that they can be moved. switched towards each other for low flight Mach numbers and one away from the other for high flight Mach numbers. This makes it possible to obtain a large variation in the divergence of the nozzle (7) while ensuring high mechanical rigidity and low leakage.

Turbine apparatus

Convergent-divergent nozzle

A convergent-divergent nozzle arranged to convey fluid from an upstream zone to a downstream zone via a throat aperture, wherein the nozzle includes an assembly movable to vary the size of the throat aperture of the nozzle, thereby regulating the flow of fluid to the downstream zone.

Variable area fan nozzle systems with improved drive couplings

A VAFN system is provided for a fan case of an engine. The system includes a motor; a gearbox; an actuator; a nozzle; and a drive coupling extending between the gearbox and the actuator and configured to transmit the mechanical torque from the motor to the actuator. The drive coupling includes an external tube extending from a first one of the gearbox or the actuator, the external tube defining first and second slots extending in a longitudinal direction, and an internal tube extending from a second one of the gearbox or the actuator and at least partially extending within the external tube, the internal tube including a pin with first and second ends respectively positioned within the first and second slots such that the internal tube is configured to translate within the external tube and to be rotatably coupled to the external tube.

THRUST REVERSER AND VARIABLE AREA FAN NOZZLE ACTUATION SYSTEM AND METHOD

SUPERSONIC AIRCRAFT TURBOFAN ENGINE

A turbofan engine for providing propulsive thrust to a supersonic aircraft is provided. The engine has an engine core comprising in flow series a compressor, a combustor and a turbine. The engine further has a fan located upstream of the engine core. The engine further has a supersonic intake for slowing down incoming air to subsonic velocities at an inlet to the fan formed by the intake. The engine further has a bypass duct surrounding the engine core, wherein the fan generates a core airflow to the engine core and a bypass airflow through the bypass duct. The engine further has a mixer for mixing an exhaust gas flow exiting the engine core and the bypass airflow exiting the bypass duct. The engine further has a thrust nozzle rearwards of the mixer for discharging the mixed flows. The engine further has a controller configured to control the thrust produced by the engine over a range of flight operations including relatively high thrust transonic push operation during which the aircraft ...

ГОНДОЛА ДЛЯ ДВИГАТЕЛЯ ЛЕТАТЕЛЬНОГО АППАРАТА С СОПЛОМ ПЕРЕМЕННОГО ПОПЕРЕЧНОГО СЕЧЕНИЯ

... 1. Гондола для двигателя летательного аппарата, содержащая: сдвижной капот (11) реверсора тяги, перемещаемый между положением прямой тяги и положением обратной тяги; реактивное сопло (13) переменного поперечного сечения, размещенное в нижнем по потоку продолжении указанного капота (11);и средства приведения в действие соответственно указанного капота (11) и указанного сопла (13), отличающаяся тем, что указанное реактивное сопло (13) установлено на указанном капоте (11) реверсора тяги с возможностью сдвига, при этом указанные средства реверса тяги содержат:по меньшей мере один силовой цилиндр (45) для приведения в действие указанного капота (11) реверсора тяги;по меньшей мере одну ведущую шестерню (37), установленную поворотно на неподвижно закрепленной конструкции (25) указанной гондолы;по меньшей мере одну зубчатую рейку (35) для приведения в действие указанного реактивного сопла (13), прикрепленную к указанному соплу (13), причем указанная зубчатая рейка (35) входит в зацепление с указанной ...

Регулируемое сопло

Механизм для перемещения подвижного конуса реактивного сопла турбореактивного двигателя

GASTURBINENSTRAHLTRIEBWERK MIT MINDESTENS EINEM AXIAL VERFAHRBAR ANGEORDNETEN SCHIEBER

Improvements in or relating to propulsion nozzles

... 1,073,278. Jet propulsion nozzles. ROLLS ROYCE Ltd. Feb. 15, 1966 [March 15, 1965], No.10964/65. Heading F1J. A gas turbine jet engine comprises a variable area jet nozzle having a throat formed in part by two overlapping flap members mounted so as to be movable in such a manner as to retain the throat of the nozzle at or upstream of the plane of the nozzle outlet when the flap members are moved, the upstream flap member moving pivotally slows its upstream end and the upstream and downstream ends of the downstream flap member moving substantially radially and axially respectively. Means are provided for causing said movement of the flaps. The engine shown in Fig. 3 comprises a propulsion nozzle 13 having a throat formed in part by a pair of movable flaps 14, 15. The flap member 14 is of curved form 16 at its upstream end Fig. 2 (not shown) and of flat form 18 at its downstream end. The flap member 14 is movable between its minimum area position shown in full lines in Fig. 3 and its maximum ...

Improvements in or relating to power plants

... 648,501. Jet propulsion nozzles. WESTINGHOUSE ELECTRIC INTERNATIONAL CO. Sept. 1, 1948, No. 23007. Convention date, Sept. 3, 1947. [Class 110(iii)] In a gas turbine plant the flow area of the jet nozzle is controlled by a core movable in response to the resultant pressure obtained from the pressure of the fluid in the nozzle reacting on the core and an opposing variable pressure obtained from an air compressor of the plant. The nozzle comprises a tapered section 23 of an outer casing 11 and a movable core 25 is slidably mounted on the end section 26 of an inner casing 12. The core is actuated by a bellows diaphragm 42 the interior of which is connected by a pipe 45 to a point on the compressor. The core 25 is vented through the passage 39 and rearwardly directed hood 41. Stops 36 co-operate with a flange 31 on the core to limit the amount of outward travel.

Improvements in jet engines

... 838,038. Jet propulsion nozzles. BOEING AIRPLANE CO. May 29, 1958 [Aug. 20, 1957], No. 17197/58. Class 110 (3). [Also in Group XXXIII] The duct leading to the nozzle of a jet propulsion engine and the nozzle itself are formed by the interior wall of a housing 9, Fig. 2 (part radial section) which, going downstream, first diverges and then converges, and by a bulbous plug 1 axially slidable on a central tube 91 by an actuator 10. Normally, the plug is located so that its greatest diameter is in the region of the greatest diameter of the wall, to form a throat in the duct. The plug then covers a set of vanes 2 housed in recesses 97. The plug can be moved axially to vary the area of the throat and nozzle, and in the position shown exposes the vanes 2 which may be swung radially as shown by an acutator 21 to split up the jet stream for noise suppression. The vanes are channel-shaped, open downstream, so that ambient air can flow radially inwards along the channels and mix with the jet. The ...

TURBOFAN ENGINE COWL ASSEMBLY AND METHOD OF OPERATING THE SAME

An inner core cowl baffle assembly (102) for a turbofan engine assembly (10) is provided. The engine assembly includes a core gas turbine engine (20), a core cowl (22) which circumscribes the core gas turbine engine, a nacelle (24) positioned radially outward from the core cowl, and a fan nozzle duct (26) defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly (110) configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.

COOLANT FLOW METERING DEVICE

TURBOFAN ENGINE COWL ASSEMBLY AND METHOD OF OPERATING THE SAME

An inner core cowl baffle assembly (102) for a turbofan engine assembly (10) is provided. The engine assembly includes a core gas turbine engine (20), a core cowl (22) which circumscribes the core gas turbine engine, a nacelle (24) positioned radially outward from the core cowl, and a fan nozzle duct (26) defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly (110) configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.

Turbine engine

Device for adjusting the outlet section of the nozzle of a jet engine

PROPELLING NOZZLE FOR A HYPERSONIC REACTOR.

Improvements with the conduits with openings of variable section

NOZZLE MIXER FOR AIRPLANE TURBOJET DUAL FLOW SECONDARY COWL HAS SEPARATE EXPANDABLE AND SHRINKABLE CENTRAL BODY

RAMJET FOR AIRCRAFT HAS SUPERSONIC AND/OR HYPERSONIC FLIGHT

Annular conduit of exhaust of the convergent-divergent type

Improvements brought to the devices throttle valves or diffusers for a fluid current

Dispositif d'injection de gaz pour propulseur combiné turbo-stato-fusée

Dans un propulseur combiné turbo-stato-fusée comprenant une turbine 6 à ergols disposée dans un corps central 2 entouré d'une veine annulaire 1 comportant à l'amont un compresseur d'air 4 entraîné par la turbine, dont les gaz d'échappement de la turbine 6 sont injectés dans la veine d'air comprimé pour y être mélangés à celui-ci et y être brûlés dans une chambre de combustion, selon l'invention le dispositif d'injection 13 des gaz dans la veine est constitué de bras radiaux 14 comportant un profil aérodynamique, régulièrement répartis entre une virole interne et une virole externe de la veine, lesdits bras radiaux comportant au moins une cavité radiale 14eaval alimentée depuis le corps central du propulseur par les gaz d'échappement de la turbine en mode turbo, les bras radiaux comportant sur leur intrados 14d des orifices 16 d'injection desdits gaz d'échappement dans la veine d'air comprimé, tandis qu'une cavité radiale amont 14f alimentée en hydrogène chauffé dans un échangeur de tuyère ...

DEVICE Of GAS INJECTION FOR ENGINE COMBINES TURBO-STATO-FUSEE

CONDUIT OF PROPULSION FOR ENGINE HAS GAS TURBINE

A Apparatus to Reduce the Lateral Thrust of Variable Nozzle and the Same Method

PYROTECHNICALLY DRIVEN NOZZLE RESTRICTOR

A pyrotechnically driven device for restricting the area of the nozzle throat (16) in a solid propellant rocket motor includes a piston support (22) mounted in the rocket motor exit cone (14). Attached to a piston (34) is a restrictor (54) movable from a retracted position outside of the nozzle throat (16) to a restricting position within the nozzle throat (16). The piston (34) and attached restrictor (54) are driven by a pyrotechnic charge (30) which includes an initiator (32) operable independently from the solid propellant of the rocket motor. A locking means (44, 48) locks the restrictor in its restricting position.

Variable area nozzles for turbomachines

Jet propulsion powerplant comprising a gas producer 11 having a first flow duct 12 for receiving the output of the gas producer 11. The flow duct 12 includes a nozzle 13 having a center body 16 which has an upstream part 17 and a downstream part 20. Motors 22 are provided for expanding and contracting the downstream part 20 relative to the upstream part 17. A second flow duct 33 having an inlet 30 openable to airflow and connected to the interior of said upstream part 17 is provided. An outlet 24 from the interior of the upstream part 17, is provided at the downstream end of the upstream part 17. The outlet 24 opens into the interior of the first flow duct 12 by contracting the downstream part 20 relative to the upstream part 17. By such an arrangement, infrared radiation may be suppressed when necessary by opening the inlet for air flow and controlling the upstream and downstream parts so that there can be a mixing of air with exhaust gases which reduces the mean temperature of the exhaust ...

Multiple bypass-duct turbofan with annular flow plug nozzle and method of operating same

A propulsion nozzle having a substantially cylindrical translatable shroud partially defining an outer flow duct and an articulated plug mounted within the shroud to partially define an inner coannular flow duct. A variable position valve comprises the downstream portion of the common wall between the ducts for modulating the relative flow rates between ducts and for creating a favorable static pressure balance therebetween. The shroud and plug cooperate to form a variable area throat for the combined duct flows.

Trailing edge for an aircraft engine, of the type with moving chevrons

This trailing edge is of the type with moving chevrons (9a, 9b, 9c). It comprises actuating means able to cause these chevrons (9a, 9b, 9c) to move from a passive position in which they are directed substantially in the direction of the airflow leaving the said engine, into an active position in which at least part of each chevron is inclined with respect to this direction. This trailing edge is notable in that the said active position is derived from the said passive position by pivoting, possibly combined with a translational movement, of at least part of each chevron about an axis (Aa, Ab, Ac) substantially parallel to the said direction.

EXHAUST NOZZLE

There is disclosed an exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a frame extending along a longitudinal axis, and a convergent petal pivotably attached at a convergent pivot point to the frame and extending axially downstream and radially inward from the frame. The exhaust nozzle comprises a follower roller fixed to the convergent petal on a radially outer side of the convergent petal, and a cam defining a working surface configured to engage the follower roller to react a force from the convergent petal. The cam is movable along a travel in an axial direction to actuate radial movement of the follower roller to pivot the convergent petal. The cam defines a convex working surface such that a contact angle between the follower roller and the cam varies along the travel to thereby vary an axial component of the force reacted by the cam. 1. An exhaust nozzle for a gas turbine engine , the exhaust nozzle comprising a frame extending along a longitudinal axis and the exhaust nozzle comprising:a convergent petal pivotably attached at a convergent pivot point to the frame and extending axially downstream and radially inward from the frame;a follower roller fixed to the convergent petal on a radially outer side of the convergent petal; anda cam defining a working surface configured to engage the follower roller to react a force from the convergent petal;wherein the cam is movable along a travel in an axial direction to actuate radial movement of the follower roller to pivot the convergent petal, whereby the cam defines a convex working surface such that a contact angle between the follower roller and the cam varies along the travel to thereby vary an axial component of the force reacted by the cam.2. The exhaust nozzle according to claim 1 , comprising a divergent petal pivotably attached at a divergent pivot point to a downstream end of the convergent petal claim 1 , the divergent petal extending axially downstream and radially outward from the ...

Gas ejection cone for an aircraft turbojet equipped with a device for generating turbulence in a primary flow limiting jet noise

A gas ejection cone for an aircraft turbojet, the cone including a hollow main body defining, on the outside, a radially inner skin of an annular primary flow channel, and a device generating turbulence in the primary flow limiting jet noise, mounted so as to move on the main body so as to be able to be displaced from an extracted position in which the device projects toward downstream in relation to a downstream end of the hollow main body, and a retracted position in which the device is retracted into the hollow main body, and vice versa. Further, the device includes a cylindrical support body having an axis parallel to an axis of the ejection cone, and at least one fin supported by the body.

VARIABLE AREA NOZZLE FOR GAS TURBINE ENGINE

PROPULSION SYSTEM FOR AN AIRCRAFT AND METHOD OF MANUFACTURING A PROPULSION SYSTEM FOR AN AIRCRAFT

A propulsion system for an aircraft is taught herein. The propulsion system includes, but is not limited to, an engine (22) that is configured to produce a gas jet. The propulsion system further includes a nozzle (24) that is coupled with the engine and that is disposed to receive the gas jet. The nozzle (24) has a throat (40) that is configured to expand and contract. The propulsion system still further includes a controller (26) that is operatively coupled with the throat (40). The controller (26) is configured to control the throat (40) to expand and contract and to control a magnitude of a thrust imparted by the gas jet by controlling the throat (40) to expand and contract. The controller (26) is further configured to control the magnitude of the thrust by controlling the throat (40) to expand and contract when the aircraft is flying at or above the local speed of sound.

Guide system for nacelle assembly

A guide system for translating components of an aircraft engine nacelle includes a track assembly (106) and a slider assembly (150). The track assembly includes a track guide member (108) and a track liner (112) engaged therewith. The track guide member includes a track channel (109) configured to receive the track liner. The track liner defines an interior surface and includes a projection portion (120) projecting inwardly of the track channel to define a convex surface. The slider assembly translatably engages the track assembly and includes a slider member having a head portion (154) configured to be received within the track channel. The head portion defines a concave surface substantially corresponding to the convex surface of the track liner and is configured to mate therewith. The slider member further includes an extension portion (156) extending from the head portion and outwardly of the track assembly.

VANE-TYPE THRUST VECTORING NOZZLE

An adjustable converging-diverging nozzle (10) includes a body (11) having a flow passageway (14) therethrough. The passageway is configured to define an entrance section (18), a narrowed throat section (19), and an exit section (20). Two opposing vane members (12, 13) are pivotally mounted on the body. Each vane member has a first surface (33, 33') facing into the passageway to form a movable wall portion of the throat secion. Each first surface is eccentric to the pivotal axis (38, 38') of the associated vane member. A pair of actuators (42, 43) are mounted on the body for selectively varying the angular positions of the associated vane members. The vane members may be moved to a closed position to reduce the orifice area of the throat section to zero, or may be moved to other angular positions to vary the magnitude and/or direction of the thrust vector of hot gas discharged through the nozzle. The invention also provides an improved method of operating the nozzle by selectively moving ...

NOZZLE FOR GENERATING THRUST

ПРЯМОТОЧНЫЙ ВОЗДУШНО-РЕАКТИВНЫЙ ДВИГАТЕЛЬ ДЛЯ ЛЕТАТЕЛЬНОГО АППАРАТА СО СВЕРХЗВУКОВОЙ И/ИЛИ ГИПЕРЗВУКОВОЙ СКОРОСТЬЮ ПОЛЕТА

Прямоточный воздушно-реактивный двигатель для летательного аппарата со сверхзвуковой и/или гиперзвуковой скоростью полета содержит камеру сгорания с переменной геометрией для осуществления смешивания топлива с окислителем и приготовления таким образом подлежащей сжиганию горючей смеси и реактивное сопло для отведения в атмосферу газов, выходящих из камеры сгорания. Камера сгорания образована зоной корпуса двигателя, имеющего в окрестностях переходной зоны между камерой сгорания и реактивным соплом эволютивную или изменяемую геометрию, меняющуюся в зависимости от числа Маха. Такое выполнение двигателя приводит к расширению его диапазона функционирования при сохранении максимальной эффективности во всем этом диапазоне. 9 з.п.ф-лы, 3 ил.

РОТОРНО-ПОРШНЕВОЙ ДВИГАТЕЛЬ

... 1. Роторно-поршневой двигатель, содержащий неподвижный полый корпус, установленный в корпусе с возможностью вращения ротор с элементами, образующими как минимум две рабочие камеры двигателя, элементы подачи рабочего тела в рабочие камеры двигателя и элементы газообмена для выхода газа из рабочих камер двигателя, отличающийся тем, что по крайней мере один элемент подачи рабочего тела представляет собой сопло Лаваля, содержащее расположенные на входе сопла свечу зажигания и управляемые форсунки подачи горючего, окислителя и также воды или водяного пара. ! 2. Роторно-поршневой двигатель по п.1, который содержит по крайней мере один коммутируемый перепускной канал между рабочими камерами двигателя для передачи плазмы из одной камеры в другую, а сопло Лаваля содержит расположенную на входе сопла форсунку для подачи плазмы, соединенную с указанным перепускным каналом. ! 3. Роторно-поршневой двигатель по п.1, который содержит расположенную на выходе сопла форсунку подачи дополнительной воды. !

ADJUSTABLE NOZZLE FOR HYPERSONIC ENGINE COMBUSTION CHAMBER.

In a ram jet combustion chamber having fuel injectors 34 and an exhaust nozzle 7, the nozzle throat cross-section (between the widest part of a displacement body 15 and an outer wall 10 increases along with increase in combustion space length as the body 15 axially slid able on a support pipe 18 is moved outwards, and conversely, both parameters decrease as the body (15) is moved inwards. This interdependence results in highly effective ram-jet operation. In other embodiments, air may be delivered to the ram jet combustion chamber by a double pipe (figs 2 to 5) or may serve as a combined ram-jet combustion chamber and afterburner chamber of turbo engine (figs 6 and 7) which may have a bypass arrangement. ...

Exhaust nozzle for gas turbine aeroengine

A nozzle is provided which is capable of varying its outlet area and varying the distribution of outlet area thereacross. The nozzle comprises a generally rectangular duct 32 and a parallelogram-shaped plug 40 which is expandable to vary the outlet area and translatable across the outlet 38 of the nozzle to vary the distribution of outlet area thereacross by means of independently actuatable ballscrews 66, 68. When the ballscrews 66,68 are rotated, as by motors 72, in the same direction, translation of the plug 40 across the outlet 38 occurs, whereas when they are rotated in opposite directions, a variation in width of the plug 40 occurs. The plug 40 is formed of four panels 42,44,46,48 hinged together at 54,56,58,60, and connected to sleeves 70 of the ballscrews 66,68. A pair of such nozzles spaced along an aircraft centreline can be used to provide both pitch and roll control.

Turbofan engine baffle assembly for varying throat of fan nozzle duct

A baffle assembly is provided for a turbofan engine assembly 10, which includes a core gas turbine engine, a core cowl 22 which circumscribes the core gas turbine engine, a nacelle 24 positioned radially outward from the core cowl, and a fan nozzle duct 26 defined between the core cowl and the nacelle. The baffle assembly includes a baffle 102, and an actuator assembly 110 configured to vary the throat area of the fan nozzle duct by selectively repositioning the baffle 102. The baffle may be an inner core cowl baffle coupled to the core cowl 22. Alternatively, a translating outer core baffle may be positioned along a portion of the radially inner surface 25 of the nacelle 24.

ADJUSTABLE INTAKE FOR A JET ENGINE.

A stationary central body 1, which may form part of the air intake of a turbo-jet engine, is provided with bulging parts 2, 3 displaced axially as well as over the circumference substantially by 180 DEG to one another. A telescopic sleeve 5, 6 may be axially extended into engagement with the bulging parts 2 and 3 to close off the passage 7. In an alternative embodiment (figure 2) the arrangement is applied to a composite gas-turbine/ram-jet engine having an outer annular ram air duct (10) into which air flows when the passage 7 is closed. Pivotable shutters 12, 13 obturate the ram air duct (10) when the passage 7 is open. The line of contact between the sleeve and the parts 2, 3 lies in an axially inclined plane thereby enabling a slim engine to be produced. ...

FLUID PROPULSION ENGINE WITH FLOW EXIT CONTROL DEVICE

Aeroengine ventilation system

ENGINE WITH VARIABLE AREA EXHAUST

The engine includes an annular flow splitters 32, 34 spaced radially outwardly of a core engine and generally aft of a fan 26. The splitter 34 receives a portion of the air flow and directs it into a mixer 42 which mixes that portion with a core gas flow to produce a mixed flow. An axially translatable center body 48 within an exhaust duct varies the exhaust area of the nozzle. ...

COMPOSITE CHANGEOVER-TYPE REACTION POWER UNIT FOR AIRCRAFT

Improvements in or relating to exhaust nozzle structures for jet propulsion engines

... 854,248. Jet propulsion engines. WESTING- HOUSE ELECTRIC CORPORATION. Nov. 17, 1958 [Nov. 26, 1957], No. 36883/58. Class 110(3). An exhaust nozzle structure for jet propulsion engines comprises a tubular casing 11 forming a fluid passageway, a rigid tubular shell structure 15 communicating with the passageway to form an exhaust nozzle and a series of pressure-responsive mechanisms disposed opposite apertures 21 in the shell and each comprising a tubular housing 25 in registry with its respective aperture and containing a member such as the piston 26 movable by the difference between the exhaust fluid pressure acting on one side thereof and the ambient air pressure acting on the other side thereof to effect a change in the cross-sectional area of the exhaust nozzle opening. The shell structure 15, Fig. 1, comprises an outer cylindrical shell 16 with apertures 19 and an inner shell 17 of convergent-divergent shape, the shells together enclosing an annular space 20. Each piston 26 has a plate ...

Means for actuating a variable area jet propulsion nozzle

... 865,881. Jet propulsion nozzle. CANADA, MINISTER OF NATIONAL DEFENCE OF. Dec. 7, 1959, No. 41480/59. Class 110 (3). A variable-area jet-propulsion nozzle having a series of annularly arranged longitudinally extending flaps pivotally mounted at their one ends to supporting structure to define a duct terminating in a discharge orifice, has cam members with profiled cam surfaces, which cooperate with abutments mounted on fixed structure surrounding the duct, pivoted on the exterior of the flaps adjacent the free ends thereof and means to pivot the cam members in synchronism to move the cam surfaces relative to the abutments to cause pivoting of the flaps. The tail pipe 14 terminates in a peripheral groove 18 in which are pivotally mounted flaps 19. Sealing members 22 comprising a pair of flanges 23, 24 spaced apart by a web 25 are located between each pair of flaps 19. The sealing members 22 are attached to the flap by rivets 30 which pass through holes 27 and slots 28. Each flap has a pair ...

A device for varying the effective nozzle area of a rocket or other jet propulsion unit

... 782,852. Jet propulsion nozzles. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Feb. 3, 1955 [Feb. 11, 1954], No. 3230/55. Addition to 745,630. Class 110 (3). A rocket or jet propulsion unit having a jet propulsion nozzle as claimed in the parent Specification in which the area of the propulsion nozzle is varied by means of an annular auxiliary jet inclined upstream with respect to the flow through the nozzle, has the passage extending around the end of the nozzle supplied with motive gas tapped from the main stream in the nozzle in a part thereof upstream of the end of the nozzle or in a part of the unit in direct communication with the nozzle. In the arrangement shown, gas from the main jet flow enters an annular conduit formed between the surface ABC of an annular body mounted in the propulsion nozzle and the propulsion nozzle casing. This gas is expanded in the nozzle CF. The annular body is attached by arms 1 to pistons 3, 31 mounted in a cylinder 6. Springs 8, 81 ...

Improvements in low drag variable diameter plug jet exhaust nozzle

... 1,016,198. Jet propulsion nozzles. GENERAL ELECTRIC CO. Nov. 29, 1963 [Dec. 3, 1962], No. 47228/63. Heading F1J. The invention relates to a propulsion nozzle of a jet propulsion engine, the nozzle comprising an inner plug member in the form of two frustoconical members which abut base to base, the plug member being formed of two sets of flaps, the upstream set being pivotally mounted at their upstream ends and the downstream set being pivotally mounted at their downstream ends, means being provided for adjusting the positions of the flaps so as to vary the diameter of the plug member and hence the area of the throat of the nozzle. The nozzle assembly comprises a central support tube 37 which is secured at 36 to a tube 12 of similar diameter, the tube 12 being the frame member of a gas turbine jet engine (not shown). A first set of flaps 30 is pivotally mounted on the tube 37 at 34, the flaps together defining a frusto-conical surface which together with the outer wall 10 of the engine exhaust ...

VARIABLE-GEOMETRY NOZZLES FOR JET PROPULSION ENGINES

... 1417504 Jet propulsion nozzles - variable geometry SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 24 April 1973 [2 May 1972] 19462/73 Headings F1G and F1J The invention relates to a variable geometry nozzle for a jet engine of the axially-movable centre plug type. The nozzle comprises an outer fixed casing 4 comprising upstream and downstream frames 1, 2 connected by members 3. A centre body 5 is disposed coaxially within the outer casing 4 and comprises a fixed support structure 8 and an axially-movable centre plug 6 mounted thereon. The support structure 8 is supported from the frame 1 by means of three tangential struts 15 which are secured at their inner ends to an outer ring 12 which is pivotally connected to an intermediate ring 14 in the vertical plane y-y, the intermediate ring being pivotally connected to an inner ring 13 in the horizontal plane z-z', the ring 13 being secured to support structure 8. The movable plug 6 is mounted on the support structure 8 by means ...

Supersonic jet with a controllable critical cross section

PROPULSION NOZZLE FOR GAS TURBINE ENGINE.

Process and adjusting devices of a flow and their various applications

DISPENSER ASSEMBLY TURBOFAN ENGINE AND METHOD FOR OPERATING THEREOF

Improvement with the turbojets with two flows

Convergent-divergent conduit with needle for the engines of jet

Improvements with the gas turbines or the engines with gas with reaction

ENGINE HAS TURBO BLOWER HAS FLOW MIXES

TURBOSOUFFLANTE A FLUX MELANGE AYANT UN RENDEMENT AMELIORE POUR TOUT REGIME DE FONCTIONNEMENT. ELLE COMPORTE: UN GENERATEUR DE GAZ 12 POUR CREER UN FLUX GAZEUX; UNE NACELLE ANNULAIRE 22 SITUEE RADIALEMENT VERS L'EXTERIEUR DU GENERATEUR DE GAZ 12; UNE SOUFFLANTE 26 A L'INTERIEUR DE LA NACELLE 22 POUR CREER UN FLUX D'AIR DE SOUFFLANTE 28; UN SEPARATEUR DE FLUX 34 ANNULAIRE SITUE RADIALEMENT A L'EXTERIEUR DU GENERATEUR DE GAZ 12 ET GENERALEMENT A L'ARRIERE DE LA SOUFFLANTE 26, LE SEPARATEUR 34 POUVANT RECEVOIR UNE PARTIE 36 DU FLUX D'AIR DE SOUFFLANTE; UN MELANGEUR 42 QUI MELANGE LA PARTIE 36 DU FLUX D'AIR DE SOUFFLANTE AVEC LE FLUX GAZEUX 14 POUR FOURNIR UN FLUX MELANGE 44; UN MOYEN DE DECHARGE 46 ET UN MOYEN DE MODIFICATION DE LA SECTION D'EJECTION. APPLICATION AUX MOTEURS A TURBINE A GAZ. MIXED FLOW TURBO BLOWER WITH IMPROVED EFFICIENCY FOR ANY OPERATING RATE. IT CONTAINS: A GAS GENERATOR 12 TO CREATE A GAS FLOW; AN ANNULAR NACELLE 22 LOCATED RADIALLY TOWARDS THE EXTERIOR OF THE GAS GENERATOR 12; A BLOWER 26 INSIDE THE NACELLE 22 TO CREATE A BLOWER AIR FLOW 28; AN ANNULAR FLOW SEPARATOR 34 LOCATED RADIALLY OUTSIDE THE GAS GENERATOR 12 AND GENERALLY BEHIND THE BLOWER 26, THE SEPARATOR 34 CAN RECEIVE A PART 36 OF THE BLOWER AIR FLOW; A MIXER 42 WHICH MIXES PART 36 OF THE BLOWER AIR FLOW WITH THE GAS FLOW 14 TO PROVIDE A MIXED FLOW 44; A MEANS OF DISCHARGE 46 AND A MEANS OF MODIFICATION OF THE EJECTION SECTION. APPLICATION TO GAS TURBINE ENGINES.

ENGINE COMBINES, COMMUTABLE, FOR the DRIVE Of PLANES AND SPECIAL MACHINES

DUAL-FLOW TURBOJET ENGINE HOOD.

Ensemble de déflecteur intérieur (102) de capot central pour un ensemble de turboréacteur double flux (10). L'ensemble de turboréacteur comprend un moteur central à turbine à gaz, un capot central (22) qui entoure le moteur central à turbine à gaz, un carénage (24) placé radialement à l'extérieur du capot central et un conduit (26) de tuyère de soufflante défini entre le capot central et le carénage. L'ensemble de déflecteur intérieur de capot central comporte un déflecteur intérieur de capot central et un ensemble d'actionneur (110) conçu pour faire varier la section d'étranglement du conduit de tuyère de soufflante en repositionnant sélectivement le déflecteur intérieur de capot central par rapport au capot central. An inner bonnet (102) baffle assembly for a turbojet engine assembly (10). The turbojet engine assembly comprises a central gas turbine engine, a central hood (22) surrounding the gas turbine central engine, a fairing (24) radially located outside the central hood and a duct (26). blower nozzle defined between the central hood and the fairing. The inner bonnet inner baffle assembly has a central bonnet inner baffle and an actuator assembly (110) adapted to vary the baffle section of the fan nozzle conduit by selectively repositioning the bonnet inner baffle by compared to the central hood.

Improvements brought to the conduits for reaction engines

Improvements to variable area orifice nozzles

MODULATING DEVICE GAS CONDITIONING METHOD

Un dispositif de modulation de section d'éjection de gaz (130) destiné à être placé dans une tuyère (120) en amont du col (121) de ladite tuyère comprend un pointeau (140). Le pointeau (140) comporte une partie proximale (142) reliée à un guide de commande (134) et une partie distale (143) en forme de pièce de révolution, le pointeau (140) étant mobile entre une position rétractée et une position avancée. Le pointeau (140) présente dans sa partie distale (143) une première section de forme convexe (1431) et une deuxième section de forme convexe (1432) située en aval de la première section.

ENGINE FLUID PROPELLING PROVIDED With a CONTROL DEVICE OF EXIT Of FLOW

PULSE DRIVE

A device serves for the repeated generation of explosions, in particular for the drive of an aircraft. It comprises: ∙ a combustion chamber (21), ∙ at least one feed line for feeding a flowable, explosive material or components which form an explosive material upon mixing to the combustion chamber (21); ∙ a discharge device for the targeted discharge of a gas pressure which is generated by way of ignition of the explosive material in the combustion chamber (21), ∙ a movable nozzle regulating element (26) for the partial or complete closure of the discharge device, ∙ an actuating element (25) which is configured to open the discharge device further after opening of the discharge device and during an outflow of explosion gases by way of the discharge device. Here, the discharge device has a plurality of part nozzles (40) for the discharge of the gas pressure, and a position of the part nozzles (40) can be set by way of the actuating element (25).

INTEGRATED NOZZLE

An aircraft engine exhaust nozzle system having thrust vectoring capability for use in flight path management, for in-flight thrust reversal or modulation, or for thrust reversal during landing; and which includes a variable area nozzle for improved propulsion efficiency. The preferred embodiment utilizes an exhaust passageway having a rectangular nozzle exit area for minimum base area, boattail, and interference drag. An aerodynamically shaped plug is centrally located in the path of the exhaust gases. The portion of the plug extending aft of the nozzle exit plane is used as a thrust vector control means and comprises a pair of oppositely facing surfaces which can be displaced for changing the flow pattern of the exhaust gases, thereby generating a thrust vector for use as a primary flight control in rotating the aircraft about one of its major axes. The oppositely facing surfaces can also be positioned for forward thrust modulation or for full reversal of the thrust vector. A portion ...

Variable area exhaust nozzle

A two dimensional vectoring nozzle assembly has an expandable plug therein including a first pair of panels and a second pair of downstream panels extending between spaced, parallel side walls and wherein a pivoted connection between the first pair of inlet panels and the second pair of downstream panels is located at the nozzle throat and is associated with a mechanism to cause the pivoted connection therebetween to move substantially in a vertical plane at the throat of the nozzle between open and closed positions therein and wherein an exhaust port in the nozzle is selectively opened by a movable door operated between open and closed positions by the mechanism and operative when the expandable nozzle is in its closed position to open the door to concurrently restrict flow through the throat region of the nozzle while opening the exhaust port whereby exhaust flow through the nozzle is directed by the blocking action of the expandable plug from a point upstream thereof through the exhaust ...

NACELLE FOR A POWER PLANT WITH A VARIABLE-AREA FAN NOZZLE

A power plant includes a nacelle with a bypass turbojet engine having a ducted fan with a low compression ratio. A secondary flow, drawn in and accelerated by the fan, is channeled through a secondary duct installed in the nacelle between the inner surface of the nacelle and the outer surface of the turbojet, toward a fan nozzle. The power plant has at least two moving parts on either side of a vertical plane of symmetry of the nacelle, at least one moving part being able to adopt one of a discrete number of positions, the moving part containing or releasing a portion of the secondary flow, depending on the moving part's position. A control unit controls a different displacement of each of the moving parts between their possible positions in order to create asymmetry of the moving parts relative to the vertical plane of symmetry. 1136681139. A nacelle for a power plant with a variable-area fan nozzle , the power plant comprising a nacelle () accommodating a bypass turbojet engine () incorporating a ducted fan () , the secondary flow , drawn in and accelerated by the fan () , being channeled through a secondary duct () installed in the nacelle () between the inner surface of said nacelle () and the outer surface of the turbojet () , towards a fan nozzle () , the nacelle also incorporating;at least two moving parts located on either side of a vertical plane of symmetry of the nacelle, said plane of symmetry defining two half nacelles;at least one of these moving parts being capable of adopting one of a discrete number of positions, said number being greater than or equal to two, the moving part containing or releasing a portion of the secondary flow, depending on the moving part's position, andmeans of controlling a different displacement of each of the moving parts between their possible positions in order to create a configurational asymmetry of the moving parts relative to the vertical plane of symmetry of the nacelle,wherein, since the two half nacelles each ...

NOZZLE HAVING A VARIABLE NECK SECTION FOR A SPACECRAFT THRUSTER PROVIDED WITH A MOBILE NEEDLE

A nozzle of variable throat section for an aerospace vehicle thruster, the nozzle including a cylindrical housing presenting a throat of aperture diameter less than the diameter of the housing, and a needle suitable for sliding inside the housing between a high discharge rate front position in which the nose is set back from the throat of the housing, and a low discharge rate rear position in which the nose is in abutment against the throat, the needle including a rod for sliding inside the housing of the nozzle, the rod terminating in a nose of decreasing diameter. The nose of the rod is suitable for coming into abutment against the throat of the nozzle housing forming a seat and includes at least two axial grooves formed in its outer periphery to allow gas to pass when the nose is axially in abutment against the throat of the housing of the nozzle. 1. A nozzle of variable throat section for an aerospace vehicle thruster , the nozzle comprising:a cylindrical housing presenting, at a rear end, a throat of aperture diameter less than a diameter of the cylindrical housing; anda needle suitable for sliding inside the cylindrical housing between a high discharge rate front position in which a nose of the needle is axially set back from the throat of the cylindrical housing, and a low discharge rate rear position in which the nose of the needle is axially in abutment against the throat of the cylindrical housing, the needle comprising a cylindrical rod for sliding inside the cylindrical housing of the nozzle, the rod terminating at a rear end in a nose of decreasing diameter, the nose of the rod being suitable for coming axially into abutment against the throat of the cylindrical housing forming a seat;wherein the nose of the rod of the needle includes at least two axial grooves formed in its outer periphery to allow gas to pass when the nose is axially in abutment against the throat of the cylindrical housing of the nozzle.2. A nozzle according to claim 1 , wherein the ...

Turbine engines with variable area nozzle

A turbine engine having an engine core, an inner cowl radially surrounding the engine core, an outer cowl radially surrounding the inner cowl and spaced from the inner cowl to form an annular passage between the inner and outer cowls that defines a nozzle, at least one control surface provided on the inner cowl and movable between a retracted position, where the nozzle has a first cross-sectional area, and an extended position where the nozzle has a second cross-sectional area that is less than the first cross-sectional area and an actuator operably coupled to the control surface and configured to move the control surface to control the cross-sectional area of the nozzle.

DUAL-MODE PLUG NOZZLE

A method for controlling flow through an exhaust nozzle includes: providing a centerbody including a maximum diameter section; providing an inner shroud surrounding the centerbody, including at least a middle section of decreased diameter and terminating at an aft edge; providing an outer shroud. wherein the centerbody and the inner shroud collectively define a throat, and the outer shroud and the centerbody collectively define an exit; selectively translating the inner shroud and outer shroud to vary the throat; and selectively translating the outer shroud to vary the ratio of the exit to the throat; wherein, when the inner shroud is in a forward position, its aft edge is forward of the maximum diameter section of the centerbody, such that the throat of the nozzle is formed between the aft edge of the inner shroud and the centerbody. 1. A method for controlling a fluid flow through an exhaust nozzle , comprising:providing a centerbody extending rearward along a longitudinal axis, the centerbody including a maximum diameter section relative to the remainder of the centerbody;providing an inner shroud surrounding the centerbody, the inner shroud having an outer surface and an inner surface, the inner surface including at least a middle section of decreased diameter relative to the remainder of the inner surface, the inner shroud terminating at an aft edge;providing an outer shroud surrounding the inner shroud, the outer shroud having a forward edge, an aft edge, and an inner surface extending from the forward edge to the aft edge, wherein the centerbody and the inner shroud collectively define a throat area of the nozzle, and the outer shroud and the centerbody collectively define an exit area of the nozzle;selectively translating the inner shroud and outer shroud to vary the throat area; andselectively translating the outer shroud to vary the ratio of the exit area to the throat area;wherein the inner shroud is movable between forward and aft positions, wherein, ...

Ramjet Engine with Rotating Detonation Combustion System and Method for Operation

A ramjet engine and system and method for operation is generally provided. The ramjet includes a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines an inlet section, a combustion section, and an exhaust section. A fuel nozzle assembly is extended from the longitudinal wall. The fuel nozzle assembly defines a nozzle throat area. The fuel nozzle assembly is moveable along a radial direction to adjust the nozzle throat area based at least on a difference in pressure of a flow of fluid at an inlet of the inlet section and a pressure of the flow of fluid at the fuel nozzle assembly.

EXHAUST NOZZLE AND METHOD FOR CHANGING EXHAUST FLOW PATH

Provided is an exhaust nozzle and a method for changing an exhaust flowpath, whereby noise can be reduced by using a simple and light-weight mechanism without increasing the complexity and size of the structure of the exhaust nozzle, and furthermore, the efficiency during cruising at supersonic speeds can be improved. The rear end side of main nozzle pieces of an exhaust nozzle are provided swingably in an inward and outward direction of an exhaust flow path , about an open/close bend section to the rear of an engine, coupling nozzle pieces are coupled bendably to adjacent main nozzle pieces on either side, and when the main nozzle pieces are swung inside the exhaust flow path , the coupling nozzle pieces form projecting sections inside the exhaust flow path 1. An exhaust nozzle extending to the rear of an engine and constituting an exhaust flow path ,wherein the exhaust nozzle has a plurality of main nozzle pieces and at least one coupling nozzle piece,a rear end portion of each of the main nozzle pieces is provided swingably in an inward and outward direction of the exhaust flow path about an open/close bend section to the rear of the engine,the coupling nozzle piece is disposed between adjacent main nozzle pieces and is coupled bendably to the main nozzle pieces on either side thereof,when the main nozzle pieces are swung outward from the exhaust flow path, the coupling nozzle piece forms a flat surface having no projecting section inside the exhaust flow path, andwhen the main nozzle pieces are swung inside the exhaust flow path, the coupling nozzle piece forms a projecting section inside the exhaust flow path.2. The exhaust nozzle according to claim 1 , wherein claim 1 , when the main nozzle pieces are swung inside the exhaust flow path claim 1 , the cross-sectional area of the rear end portion of the exhaust flow path is no more than the cross-sectional area at the position of the open/close bend section of the exhaust flow path.3. The exhaust nozzle according ...

Threaded rod for system for deploying a deployable divergent segment of a thruster

The divergent segment comprises a stationary divergent portion and a movable divergent portion suitable for occupying a retracted position and a deployed position. The threaded rod has a head suitable for being supported by a support secured to the stationary divergent portion in cooperation with rotary drive means for driving the threaded rod in rotation, and a tip suitable for being inserted in a holder sleeve secured to the stationary divergent portion. The threaded rod is suitable for co-operating with a nut secured to the movable divergent portion so that rotation of said rod causes the movable divergent portion to move. The tip presents an enlargement having at least one groove passing axially therethrough.

AIRCRAFT ENGINE ASSEMBLY COMPRISING AT LEAST TWO REAR ENGINE ATTACHMENTS AXIALLY SHIFTED FROM EACH OTHER

In order to reduce the width of the attachment between the rear portion of an aircraft engine and its attachment pylon, an engine assembly attachment include an assembly of rear engine attachments comprising a first connecting rod laid out in a longitudinal and median vertical plane, a second connecting rod substantially laid out tangentially to the inter-turbine case, and a rear engine attachment for transversely spreading the loads, axially shifted rearwards relatively to the first and second connecting rods, and comprising a shear pin oriented along a vertical direction of the engine assembly. 1. An aircraft engine assembly comprising:a dual-body engine comprising an inter-turbine casing;a pylon for mounting the engine on a structure of the aircraft, the pylon including a primary structure;a mount for mounting the engine on the primary structure of the mounting pylon; a first connecting rod articulated at one end with a bracket rigidly connected to the inter-turbine casing and articulated at another end with a bracket rigidly connected to the primary structure of the pylon, the first connecting rod being arranged in a median vertical and longitudinal plane;', 'a second connecting rod articulated at one end with a bracket rigidly connected to the inter-turbine casing and articulated at another end with a bracket rigidly connected to the primary structure of the pylon, the second connecting rod being arranged substantially tangential to the inter-turbine casing; and', 'a rear engine attachment for transverse force spreading, shifted axially backwards in relation to the first and second connecting rods, and including a shear pin oriented in a vertical direction of the engine assembly and rigidly connected to either the engine or the primary structure, as well as a seating bracket for the shear pin that is rigidly connected to another of the engine or the primary structure and that has a seating orifice for the shear pin, the shear pin being seated in the seating ...

CHEVRON SYSTEM FOR GAS TURBINE ENGINE

A surface-increasing feature system for a gas turbine engine comprising deployable surface-increasing features such as chevrons each defined by panels connected to a deployment mechanism providing a translational actuation to deploy said deployable surface-increasing feature from a stowed configuration concealed fore of a trailing edge of a case of the gas turbine engine, to a deployed configuration extending beyond the trailing edge. Joints provide one or more degree of freedom for the first panel and the second panel relative to the deployment mechanism. A guide operatively contacts the deployable surface-increasing feature to rotatably displace the first panel and the second panel away from one another in the at least one degree of freedom in response to movement induced by the translational actuation from the stowed configuration to the deployed configuration. A footprint of the deployable surface-increasing feature concurrently defined by the first panel and the second panel is greater in the deployed configuration than in the stowed configuration 1. A surface-increasing feature system for a gas turbine engine comprising:at least one deployable surface-increasing feature defined at least by a first panel and a second panel connected to a deployment mechanism providing a translational actuation to deploy said deployable surface-increasing feature from a stowed configuration in which the deployable surface-increasing feature is substantially concealed fore of a trailing edge of a case of the gas turbine engine, to a deployed configuration in which the deployable surface-increasing feature extends beyond the trailing edge;at least one joint providing at least one degree of freedom for the first panel and the second panel relative to the deployment mechanism; anda guide operatively contacting the deployable surface-increasing feature to rotatably displace the first panel and the second panel away from one another in the at least one degree of freedom in response to ...

Gas Turbine Engine System for Modulating Flow of Fan By-Pass Air and Core Engine Air

The system () provides a modulator ring () secured adjacent an exhaust end () of an inner wall of a by-pass fan air duct () and secured adjacent a convergent nozzle section () of the engine wherein flow of by-pass fan air () and core engine air () converge within an exhaust nozzle (), The modulator ring () may be actuated to extend beyond the exhaust end () of the duct () to decrease air passage () forcing more air into the core engine () for greater thrust from the core engine () with minimal loss of thrust from the by-pass fan air (). The modulator ring () stay alternatively rotate to uncover trailing-edge slots in the exhaust end () of the duct to also modulate flow rates of by-pass fan air () into the convergent nozzle section (), 1. A gas turbine engine system for modulating flow of by-pass fan air and core engine air , the system comprising:a. a gas turbine engine including an engine core defining passageways for directing flow of the core engine air sequentially through a compressor, a combustor wherein the air is combusted with a fuel, a high pressure turbine, a low pressure turbine, out of the engine core, and optionally through and out of an augmentor, at an engine convergent nozzle section downstream from the low pressure turbine and optional augmentor, and including a by-pass fan air duct for directing flow of by-pass fan air from a fan rotated upstream of the compressor by the core engine, through the by-pass fan air duct surrounding the engine core and optional augmentor and out of an exhaust end of the fan air duct at the engine convergent nozzle section and for directing flow of by-pass fan air in a direction parallel linear with the flow of core engine air downstream from the low pressure turbine and within the engine convergent nozzle section;b. a modulator ring selectively secured to surround an inner wall of the by-pass air duct adjacent to an exhaust end of the inner wall of the by-pass air duct and adjacent the engine convergent nozzle section; ...

EXHAUST NOZZLE OF A GAS TURBINE ENGINE

Aspects of the disclosure regard an exhaust nozzle for a gas turbine engine that includes an outer nozzle wall, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, and at least two struts connecting the centerbody to the nozzle wall. One of the struts is connected to the nozzle wall by a first connection, the first connection constraining movement of the strut relative to the nozzle wall in the radial direction and in the circumferential direction. The at least one other strut is connected to the nozzle wall by a second connection, the second connection constraining movement of the strut relative to the nozzle wall in the circumferential direction but allowing movement of the strut relative to the nozzle wall in the radial direction. 1. An exhaust nozzle of a gas turbine engine , wherein the exhaust nozzle comprises:an outer nozzle wall,a flow channel which is limited radially outwards by the nozzle wall,a centerbody arranged in the flow channel, andat least two struts connecting the centerbody to the nozzle wall,wherein one of the struts is connected to the nozzle wall by a first connection, the first connection constraining movement of the strut relative to the nozzle wall in the radial direction and in the circumferential direction,wherein the at least one other strut is connected to the nozzle wall by a second connection, the second connection constraining movement of the strut relative to the nozzle wall in the circumferential direction but allowing movement of the strut relative to the nozzle wall in the radial direction.2. The nozzle of claim 1 , wherein both the first connection and the second connection are further configured to allow movement of the strut relative to the nozzle wall in the axial direction of the nozzle.3. The nozzle of claim 2 , wherein the first connection is formed by a first sliding element and a first receiving slot claim 2 , whereinthe first sliding element extends radially ...

EXHAUST NOZZLE OF A GAS TURBINE ENGINE

An exhaust nozzle of a gas turbine engine includes an outer nozzle wall, a centerbody arranged in a flow channel, and two struts connecting the centerbody to the wall. A first strut is connected to the wall by a first connection allowing movement of the strut relative to the nozzle wall in the axial direction. Another strut is connected to the wall by a second connection allowing movement of the strut relative to the wall in the radial and axial directions. The second connection is formed by a sliding element and a receiving slot, wherein the sliding element includes an interaction zone interacting with an actuator for axial movement. The interaction zone has a radial length such that the interaction between the actuator and the interaction zone is maintained when the sliding element is moved in the radial direction by radial thermal expansion of the strut and/or the centerbody. 1. An exhaust nozzle of a gas turbine engine , wherein the exhaust nozzle comprises:an outer nozzle wall,a flow channel which is limited radially outwards by the nozzle wall,a centerbody arranged in the flow channel, andat least two struts connecting the centerbody to the nozzle wall,wherein a first strut is connected to the nozzle wall by a first connection, the first connection constraining movement of the strut relative to the nozzle wall in the radial direction and in the circumferential direction but allowing movement of the strut relative to the nozzle wall in the axial direction,a first actuator interacting with the first strut for displacing the first strut in the axial direction,wherein the at least one other strut is connected to the nozzle wall by a second connection, the second connection constraining movement of the strut relative to the nozzle wall in the circumferential direction only but allowing movement of the strut relative to the nozzle wall in the radial and axial directions,at least one second actuator, each second actuator interacting with one of the at least one other ...

EXHAUST NOZZLE OF A GAS TURBINE ENGINE

An exhaust nozzle of a gas turbine engine which includes a nozzle wall, the nozzle wall including an upstream, fixed structure and a downstream, translatable structure that is translatable relative to the fixed structure, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, at least one strut connecting the centerbody to the nozzle wall, a thrust reverser unit that comprises blocking doors, a first actuation system for deployment of the blocking doors into a deployed position for thrust reversal, and a second actuation system for translating the translatable structure between a stowed, upstream position and a fully deployed, downstream position. It is provided that the at least one strut is connected to the fixed structure, that the blocking doors are connected to the translatable structure, and that the first actuation system and the second actuation system are independent actuation systems. 1. An exhaust nozzle of a gas turbine engine , wherein the exhaust nozzle comprises:a nozzle wall, the nozzle wall comprising an upstream, fixed structure and a downstream, translatable structure that is translatable relative to the fixed structure,a flow channel which is limited radially outwards by the nozzle wall,a centerbody arranged in the flow channel,at least one strut connecting the centerbody to the nozzle wall,a thrust reverser unit that comprises blocking doors,a first actuation system for deployment of the blocking doors into a deployed position for thrust reversal, anda second actuation system for translating the translatable structure between a stowed, upstream position and a fully deployed, downstream position,wherein the at least one strut is connected to the fixed structure,wherein the blocking doors are connected to the translatable structure, andwherein the first actuation system and the second actuation system are independent actuation systems.2. The nozzle of claim 1 , wherein the nozzle wall ...

Stepped fairing modulated exhaust cooling

Aspects of the disclosure are directed to a system of an aircraft, comprising: at least one fairing, a liner, and an actuator configured to cause the at least one fairing to be translated relative to the liner in order to obtain a modulation of a metering area between the liner and the at least one fairing,

DIELECTRIC SEAL DEVICE

A seal device that may be for a variable area fan nozzle (VAFN) assembly of a turbofan engine is positioned between first and second surfaces configured to move between close and distant positions. The seal device includes a first electrode engaged to the first surface and a second electrode spaced between the first and second surfaces and spaced from the first electrode. A resilient first element of the device is disposed between and engages to the first and second electrodes, and is configured to move between contracted and expanded states when the electrodes are energized. A resilient second element of the device opposes the second surface and is engaged to the second electrode. The second element is configured to move between a compressed mode when the first and second surfaces are in the close position and an extended mode when the first and second surfaces are in the distant position. 1. A seal device positioned between first and second surfaces configured to move between close and distant positions , the dielectric seal device comprising:a first electrode engaged to the first surface;a second electrode spaced between the first and second surfaces and spaced from the first electrode;a resilient first element disposed between and engaged to the first and second electrodes, and configured to move between contracted and expanded states when the first and second electrodes are energized; anda resilient second element opposing the second surface and engaged to the second electrode, and configured to move between a compressed mode when the first and second surfaces are in the close position and an extended mode when the first and second surfaces are in the distant position.2. The seal device set forth in claim 1 , wherein the first surface is stationary.3. The seal device set forth in claim 1 , wherein the first element is configured to be in the contracted state when the first and second electrodes are energized and in the expanded state when the first and second ...

VARIABLE AREA FAN NOZZLE WITH DRIVE SYSTEM HEALTH MONITORING

A nacelle for a turbofan engine includes a variable area fan nozzle (VAFN) and a proximity sensor that is attached to a nacelle forward portion to sense the presence of the VAFN when stowed. The proximity sensor is not attached to the VAFN, thereby enabling the use of a proximity sensor such as linear variable displacement transformer having a relatively compact operational stroke. 1. A method for monitoring a movable fan nozzle of a turbofan engine , the method comprising:(a) using a first proximity sensor to detect presence of a first portion the fan nozzle, the first proximity sensor being attached to a nacelle forward portion and not attached to the fan nozzle;(b) supporting a first member of the first proximity sensor in a fixed position relative to the nacelle forward portion;(c) using motion of the fan nozzle relative to the nacelle forward portion to articulate a second member of the first proximity sensor relative to the first member during a subset of a total range of relative motion between the fan nozzle and the nacelle forward portion, the subset being less than 25% of the total range of relative motion; and(d) generating a first signal indicative of a position of the second member relative to the first member.2. The method of claim 1 , further comprising:using a second proximity sensor to detect presence of a second portion of the fan nozzle, the second proximity sensor being attached to the nacelle forward portion and not attached to the fan nozzle; andusing the second proximity sensor to detect the presence of the second portion of the fan nozzle.3. The method of claim 2 , further comprising comparing a first signal generated by the first proximity sensor with a second signal generated by the second proximity sensor to monitor for misalignment and/or defective positioning of the fan nozzle.4. The method of claim 1 , further comprising using a slave link supported by the sleeve to communicate a movement of the fan nozzle to the second member.5. The ...

NACELLE OF A TURBOJET COMPRISING A REVERSER FLAP AND A DEPLOYMENT SYSTEM WITH DELAY

A bypass turbojet nacelle comprising a fixed structure, a fixed cowl and a cowl movable in translation between advanced and withdrawn positions by a ram with a reverser flap movable thereon, and a deployment system comprising a first slider integral with the movable cowl, a first groove comprising a first part and a curved, second part integral with the fixed structure, a second slider movable in translation in the second groove part, a first connecting rod rotatable on the first slider and on the second slider, and a second connecting rod articulated on both the first connecting rod first end and the reverser flap. The ram rod is articulated on the first connecting rod. Moving the first slider from the advanced to the withdrawn position moves the second slider along the first part and, when the first slider reaches the withdrawn position, the second slider moves along the second part. 1. A nacelle for a bypass turbojet , said nacelle comprising:a fixed structure,a fixed cowl mounted immovably on the fixed structure and a movable cowl that is movable in translation relative to the fixed structure in a translational direction between an advanced position, in which it is close to the fixed cowl, and a withdrawn position, in which it is remote from the fixed cowl towards the rear, such as to define therebetween an opening connecting a duct of a secondary flow and an exterior of the nacelle,a ram configured to move the movable cowl from the advanced position to the withdrawn position, and vice versa,a reverser flap mounted to move in rotation about a principal axis of rotation on the movable cowl, between a stowed position in which the reverser flap is positioned outside the secondary duct and a deployed position in which the reverser flap is across the duct, and a first slide bar integral with the movable cowl,', 'a guide configured to guide the first slide bar in translation parallel to the translational direction relative to the fixed structure between two stop ...

Variable area nozzle exhaust system with integrated thrust reverser

A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

AIRCRAFT GAS TURBINE HAVING A VARIABLE OUTLET NOZZLE OF A BYPASS FLOW CHANNEL

An aircraft gas turbine having a core engine and having a bypass flow channel which surrounds said engine and which forms, with a casing of the core engine and a radially outer housing wall, an outlet nozzle, characterized in that, in the region of the outlet nozzle, there is arranged a ring-shaped element which is able to be displaced in the axial direction, wherein a ring-shaped channel which is able to be varied by way of the displacement of the ring-shaped element is formed between the casing of the core engine and the ring-shaped element. 1. An aircraft gas turbine having a core engine and having a bypass flow channel which surrounds said engine and which forms , with a casing of the core engine and a radially outer housing wall , an outlet nozzle , characterized in that , in the region of the outlet nozzle , there is arranged a ring-shaped element which is able to be displaced in the axial direction , wherein a ring-shaped channel which is able to be varied by way of the displacement of the ring-shaped element is formed between the casing of the core engine and the ring-shaped element.2. The aircraft gas turbine as claimed in claim 1 , wherein the ring-shaped element is able to be displaced into different displacement positions.3. The aircraft gas turbine as claimed in claim 2 , wherein the different displacement positions form different cross sections of the ring-shaped channel.4. The aircraft gas turbine as claimed in claim 1 , wherein the ring-shaped element is designed as a flow body.5. The aircraft gas turbine as claimed in claim 1 , wherein the casing of the core engine is formed to be flow-optimized in the region of the ring-shaped element.6. The aircraft gas turbine as claimed in claim 1 , wherein at least one oil cooler is arranged in the ring-shaped channel.7. The aircraft gas turbine as claimed in claim 6 , wherein the oil cooler is able to be automatically switched in operation or out of operation by way of the displacement of the ring-shaped ...

Exhaust nozzle control for a gas turbine engine

An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.

SINGLE ACTUATOR VARIABLE AREA FAN NOZZLE SYSTEM AND METHOD

A single actuator variable area fan nozzle (“VAFN”) system is provided. In contrast to typical system, the single actuator VAFN may comprise a single actuator, a linkage and a VAFN panel. The single actuator may be configured to actuate the VAFN panel between a stowed position and a deployed position. In various embodiments, the linkage may travel a path during deployment and/or retraction that is between the loft lines of the nacelle. 1. A variable area fan nozzle (“VAFN”) , comprising:a single actuator;an actuation linkage coupled to the single actuator;a VAFN panel coupled to the actuation linkage and configured to translate forward and aft based on inputs from the single actuator to change the nozzle area of a fan duct.2. The VAFN of claim 1 , wherein the actuation linkage comprises a ring crank having a first end and a second end.3. The VAFN of claim 2 , wherein the ring crank is a partial hoop structure.4. The VAFN of claim 2 , wherein the first end is configured to be pivotally mounted to a nacelle and wherein the second end is configured to be pivotally mounted to the nacelle.5. The VAFN of claim 2 , wherein the ring crank is configured to pivot from a stowed position to a deployed position within a loft line of the nacelle.6. The VAFN of claim 5 , wherein the loft line of the nacelle is defined between an outer surface of the nacelle and an inner surface of the nacelle.7. The VAFN of claim 2 , further comprising:a slave pushrod operatively coupled to the ring crank;a main crank coupled to the slave pushrod, the main crank configured to pivot between a first position and a second position in response to movement of the ring crank; anda VAFN pushrod coupled to the main crank and the VAFN panel.8. The VAFN of claim 1 , wherein the single actuator is at least one of an electric actuator and a hydraulic actuator.9. The VAFN of claim 1 , wherein the VAFN is a portion of a nacelle and is installed in the nacelle aft a translating sleeve.10. A nacelle claim 1 , ...

Sliding Nozzle Flap Assembly

Tracks (), fastened to static structure of an aircraft engine nozzle, guide sliders () journaled in struts () fastened to a flap () of the nozzle. Each slider and attached journal axle or bolt () is formed of cobalt, and each track slider surface () and journal bushings () are formed of a nickel alloy to reduce wear from rubbing. Track slides () are mounted to the static structure of the nozzle by blind bolts () having a tool recess () at its threaded tip to prevent the bolt () from turning as a nut is secured. Each slider has limited rotation due to a pin (), thereon engaging a slot in a tab () of the bushing () to assist in inserting the slider () into the beveled ends of the tracks (), when mounting or replacing a flap. 19-. (canceled)1021. Apparatus () for an aircraft engine nozzle , comprising:{'b': '23', 'an aircraft engine nozzle flap () moveable between first and second positions;'}{'b': '31', 'at least one flap positioning arm () for moving the flap between the first and second positions;'}{'b': 35', '36', '61, 'a plurality of guidance tracks (, ) disposed on the static structure of the nozzle, each having longitudinal sliding surfaces ();'}{'b': 27', '28, 'a plurality of guidance struts (, ), one end of each strut attached to the flap and the other end of each strut having a bore;'}{'b': 32', '33, 'a plurality of track sliders (), each of the plurality of track sliders rigidly connected to an axle () journaled in the bore of a corresponding one of said plurality of guidance struts, and each of the plurality of track sliders disposed in a related one of the plurality of guidance tracks;'}characterized by:the longitudinal sliding surfaces comprising a cobalt alloy and the plurality of track sliders comprising a nickel alloy.1121. Apparatus () according to further characterized in that{'b': 33', '43', '44, 'the axle () is journaled in a cobalt alloy bushing (, ).'}12. (canceled) This disclosure was made with Government support under Contract No. F33657-03-C- ...

VARIABLE-SECTION NOZZLE, AND AIRCRAFT TURBOJET ENGINE NACELLE EQUIPPED WITH SUCH A NOZZLE

A variable-section nozzle for an aircraft nacelle includes a deformable portion of which is movable between a narrow section position and a wide section position. In particular, the variable-section nozzle includes piezoelectric actuators and a controller to control the piezoelectric actuators in order to displace the deformable portion between the narrow and wide section positions. The piezoelectric actuators can be disposed on at least one faces of the deformable portion or be disposed end-to-end to form actuating rods. 1. A variable-section nozzle for an aircraft nacelle , at least one deformable portion of which is movable between a narrow section position and a wide section position , and the variable-section nozzle comprising:means for displacing said at least one deformable portion between said narrow and wide section positions, wherein said means for displacing comprise piezoelectric actuators and means for controlling said piezoelectric actuators, said piezoelectric actuators being disposed in one of the following manners:said piezoelectric actuators are disposed on at least one face of said at least one deformable portion, andsaid piezoelectric actuators are disposed end-to-end to form actuating rods.2. The variable-section nozzle according to claim 1 , wherein the at least one deformable portion rotates around a corresponding axis which is substantially perpendicular to a longitudinal axis of the aircraft nacelle.3. The variable-section nozzle according to claim 1 , wherein said piezoelectric actuators are bonded onto said at least one deformable portion.4. The variable-section nozzle according to claim 1 , wherein said at least one deformable portion comprises at least one hinged flap.5. The variable-section nozzle according to claim 1 , wherein movement amplification means are interposed between said actuating rods and said at least one deformable portion.6. The variable-section nozzle according to claim 5 , wherein the movement amplification means ...

Exhaust nozzle control for a gas turbine engine

An exhaust nozzle for a gas turbine engine according to an example of the present disclosure includes, among other things, a duct having a first surface and a second surface extending about a duct axis to define an exhaust flow path, and at least one effector positioned along the first surface. The at least one effector is pivotable about an effector axis to vary a throat area of the exhaust flow path. The at least one effector tapers along the effector axis. A method of exhaust control for a gas turbine engine is also disclosed.

Linear telescopic actuator for movement of first and second elements relative to fixed element

FIELD: machine building. SUBSTANCE: invention refers to aircraft industry, and namely to linear telescopic actuator for movement of the first and the second elements relative to fixed element. Actuator includes housing (101) that is attached to fixed element (102) and used as a sleeve for the first stock (106), the rotational movement of which is locked and which can be brought into translational movement with drive shaft (104) that is connected to drive (107) of rotational movement. The first stock is meant to be connected with one of its ends (108) to the first moved element and carries the second stock (117), with which it is aligned along common axis, and to end (118) of which the second moved element is attached. Besides, there is the possibility of locking rotational movement of the second stock (117); besides, it is brought into rotational movement with the second drive shaft (112, 115) that passes through the housing and is connected to drives (113, 111) of rotational movement. EFFECT: reduction of friction between elements of drive, as well as reduction of its dimensions. 8 cl, 9 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 470 205 (13) C2 (51) МПК F16H 25/20 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2010116841/11, 04.07.2008 (24) Дата начала отсчета срока действия патента: 04.07.2008 (73) Патентообладатель(и): ЭРСЕЛЬ (FR) (43) Дата публикации заявки: 10.11.2011 Бюл. № 31 2 4 7 0 2 0 5 (45) Опубликовано: 20.12.2012 Бюл. № 35 (56) Список документов, цитированных в отчете о поиске: WO 2007099333 A, 07.09.2007. FR 2895482 A, 29.06.2007. US 4179944 A, 25.12.1979. US 2006266146 A1, 30.11.2006. SU 268182 A1, 01.01.1970. 2 4 7 0 2 0 5 R U (86) Заявка PCT: FR 2008/000960 (04.07.2008) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 04.05.2010 (87) Публикация заявки РСТ: WO 2009/043981 (09.04.2009) Адрес для переписки: 191002, Санкт-Петербург, а/я 5, ООО "Ляпунов и партнеры" ( ...

A nozzle arrangement for a gas turbine engine

A gas turbine engine comprising: a bypass duct having a bypass nozzle; an engine core having a core nozzle; and, a mixer duct defined by a mixer fairing and having a mixer nozzle, wherein the mixer duct is arranged to receive an airflow from the bypass duct through a mixer duct inlet and an airflow from the engine core, when in use, and the geometry of the mixer duct is selectively adjustable by moving the mixer fairing relative to the bypass duct and engine core in use.

Aircraft gas turbine having a variable outlet nozzle of a bypass flow channel

The invention relates to an aircraft gas turbine, comprising a core engine (10) and a bypass flow channel (25), which bypasses the core engine and which forms an outlet nozzle (31) together with a casing (29) of the core engine (10) and together with a radially outer housing wall (30), characterized in that a ring element (32), which can be displaced in the axial direction, is arranged in the region of the outlet nozzle (31), wherein a ring channel (33) that can be varied by the displacement of the ring element (32) is formed between the casing (29) of the core engine (10) and the ring element (32).

Method and device for producing thrust

FIELD: jet engine engineering. SUBSTANCE: method includes producing combustion products of high pressure and temperature, accelerating the combustion products up to a velocity which corresponds to the supercritical pressure drop, and issuing the combustion products to the ambient in the form of counter streams perpendicular to the thrust vector under the flat base. To control the thrust in magnitude, the ratio of areas of critical sections of the counter flows to the area of the flat base is changed. To control the thrust direction the flat base is turned. The device has combustion chamber with gas duct 1, turbine 2, outlet pipe 3, and central body 6 with flat base 7 perpendicular to the axis of outlet pipe 3 whose face is made up as movable squeezing casing 4. The casing and the central body define a nozzle whose outlet sections face each other. Central body 6 and squeezing casing 4 are provided with drives 18 for their movement and rotation. The central body can be made up as sections which can move one with respect to the other. EFFECT: enhanced efficiency. 3 cl, 3 dwg 9901$ 0с ПЧ ГЭ РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (19) ВИ” 2 037 066. (51) МПК 13) Сл Е 02 К 9/80 12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ (21), (22) Заявка: 93046474/23, 01.10.1993 (46) Дата публикации: 09.06.1995 (56) Ссылки: Вопросы ракетной техники, 1963, М 3, с.62, рис.13. (71) Заявитель: Знаменский Владимир Павлович, Соколов Сергей Викторович, Чекмасов Владислав Дмитриевич (72) Изобретатель: Знаменский Владимир Павлович, Соколов Сергей Викторович, Чекмасов Владислав Дмитриевич (73) Патентообладатель: Знаменский Владимир Павлович, Соколов Сергей Викторович, Чекмасов Владислав Дмитриевич (54) СПОСОБ ПОЛУЧЕНИЯ ТЯГИ И УСТРОЙСТВО ДЛЯ ЕГО ОСУЩЕСТВЛЕНИЯ (57) Реферат: Использование: в реактивной технике, в частности в способах и устройствах для создания тяги и управления вектором тяги в двигателях. Сущность изобретения: способ заключается в выработке продуктов сгорания ...

Aircraft nacelle internal structure

FIELD: transport. SUBSTANCE: invention relates to aircraft engineering, particularly, to turbojet nacelles. Claimed nacelle internal structure comprises active and passive moving elements. Active elements drive the adjacent passive elements. Internal structure has three positions. At the first nominal position, an aerodynamic continuity exists between active moving elements and passive moving elements. At second position, the active moving elements extend beyond the passive moving elements outward from the internal structure. At third position, the active moving elements extend beyond the passive moving elements inside the internal structure. EFFECT: simplified design. 13 cl, 22 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК B64D 33/04 (13) 2 572 000 C2 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2013132646/11, 30.11.2011 (24) Дата начала отсчета срока действия патента: 30.11.2011 Приоритет(ы): (30) Конвенционный приоритет: (72) Автор(ы): ЮРЛЕН Эрве (FR), КЕРБЛЕР Оливье (FR), ЖИЛО Оливье (FR) 20.12.2010 FR 10/60816 (43) Дата публикации заявки: 27.01.2015 Бюл. № 3 R U (73) Патентообладатель(и): ЭРСЕЛЬ (FR) (45) Опубликовано: 27.12.2015 Бюл. № 36 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 22.07.2013 (86) Заявка PCT: 2 5 7 2 0 0 0 (56) Список документов, цитированных в отчете о поиске: WO 2008045067 A1, 17.04.2008. RU 2472678 C2, 20.01.2013. RU 2494273 C2, 27.09.2013. 2 5 7 2 0 0 0 R U (87) Публикация заявки PCT: WO 2012/085379 (28.06.2012) Адрес для переписки: 191002, Санкт-Петербург, а/я 5, ООО "Ляпунов и партнеры" (54) ВНУТРЕННЯЯ КОНСТРУКЦИЯ ГОНДОЛЫ ВОЗДУШНОГО СУДНА (57) Реферат: Изобретение относится к области авиации, в активные подвижные элементы выступают за частности к гондолам турбореактивных пассивные подвижные элементы в направлении двигателей. Внутренняя конструкция гондолы внутрь внутренней конструкции. Достигается турбореактивного двигателя содержит активные ...

TELESCOPIC LINEAR ACTUATOR FOR MOVING A FIRST AND A SECOND ELEMENTS RELATIVELY TO A FIXED ELEMENT

Linear telescopic actuator for moving a first and a second element relative to a stationary element

The invention relates to a linear telescopic actuator for moving a first (10b) and a second (10a) element relative to a stationary element (102). Said actuator comprises a base (101) that is to be connected to the stationary element (102) and is used as a cavity for a first rotationally locked rod (106) which can be translated by a drive shaft (104) that is to be connected to rotational driving means (107). One end (108) of said first rod is to be connected to the first element that is to be moved. The actuator is characterized in that the first rod (106) supports a second rod (117) which is aligned therewith and one end (118) of which is to be connected to the second element that is to be moved. Said second rod (117) can be rotationally locked and can be translated by a second drive shaft (112, 115) which extends through the base and is connected to rotational driving means (113, 111).

Linear telescopic actuator for moving a first and a second element relative to a stationary element

The invention relates to a linear telescopic actuator for moving a first ( 10 b ) and a second ( 10 a ) element relative to a stationary element ( 102 ). Said actuator comprises a base ( 101 ) that is to be connected to the stationary element ( 102 ) and is used as a cavity for a first rotationally locked rod ( 106 ) which can be translated by a drive shaft ( 104 ) that is to be connected to rotational driving means ( 107 ). One end ( 108 ) of said first rod is to be connected to the first element that is to be moved. The actuator is characterized in that the first rod ( 106 ) supports a second rod ( 117 ) which is aligned therewith and one end ( 118 ) of which is to be connected to the second element that is to be moved. Said second rod ( 117 ) can be rotationally locked and can be translated by a second drive shaft ( 112, 115 ) which extends through the base and is connected to rotational driving means ( 113, 111 ).

Linear telescopic actuator for moving a first and a second element relative to a stationary element

Linear telescopic actuator for moving a first and a second element relative to a stationary element

本发明涉及一种用于将第一元件(10b)和第二元件(10a)相对于固定元件(102)移动的伸缩式线性致动器。所述致动器包括底座(101)，该底座用来与固定元件(102)相接附，并用作转动被锁定的第一杆(106)的容座，转动被锁定的第一杆能够通过用来与转动驱动装置(107)相连接的驱动轴(104)被平移驱动，所述第一杆用来通过其一端(108)与要被移动的第一元件相接附，该致动器的特征在于，第一杆(106)支承第二杆(117)，第二杆与第一杆对准，并通过其一端(118)与要被移动的第二元件相接附，所述第二杆(117)的转动锁定，并能够通过穿过底座并与转动驱动装置(113、111)相连接的第二驱动轴(112)被平移驱动。

Telecopic Linear Actuator and Jet Engine Nacelle Thrust Reverser

Linear telescopic actuator for moving a first and a second element relative to a stationary element

La présente invention se rapporte à un actionneur linéaire télescopique pour déplacer un premier (10b) et un second (10a) éléments relativement à un élément fixe (102), comprenant une base (101), destinée à être rattachée à l'élément fixe (102), et servant de logement à une première tige (106) bloquée en rotation et apte à être entraînée en translation par l'intermédiaire d'un arbre (104) d' entraînement destiné à être relié à des moyens d' entraînement (107) en rotation, la première tige étant destinée à être rattachée par une extrémité (108) au premier élément à déplacer, caractérisé en ce que la première tige (106) supporte deuxième tige (117) disposée dans le prolongement de celle-ci et destinée à être rattachée par une extrémité (118) au deuxième élément à déplacer, ladite deuxième tige (117) étant apte à être bloquée en rotation et entraînée en translation par l'intermédiaire d'un deuxième arbre d' entraînement (112, 115) traversant la base et relié à des moyens d' entraînement en rotation (113, 111).

Linear telescopic actuator for moving a first and a second element relative to a stationary element

本发明涉及一种用于将第一元件(10b)和第二元件(10a)相对于固定元件(102)移动的伸缩式线性致动器。所述致动器包括底座(101)，该底座用来与固定元件(102)相接附，并用作转动被锁定的第一杆(106)的容座，转动被锁定的第一杆能够通过用来与转动驱动装置(107)相连接的驱动轴(104)被平移驱动，所述第一杆用来通过其一端(108)与要被移动的第一元件相接附，该致动器的特征在于，第一杆(106)支承第二杆(117)，第二杆与第一杆对准，并通过其一端(118)与要被移动的第二元件相接附，所述第二杆(117)的转动锁定，并能够通过穿过底座并与转动驱动装置(113、111)相连接的第二驱动轴(112)被平移驱动。

Linear telescopic actuator for moving a first and a second element relative to a stationary element

La présente invention se rapporte à un actionneur linéaire télescopique pour déplacer un premier (10b) et un second (10a) éléments relativement à un élément fixe (102), comprenant une base (101), destinée à être rattachée à l'élément fixe (102), et servant de logement à une première tige (106) bloquée en rotation et apte à être entraînée en translation par l'intermédiaire d'un arbre (104) d' entraînement destiné à être relié à des moyens d' entraînement (107) en rotation, la première tige étant destinée à être rattachée par une extrémité (108) au premier élément à déplacer, caractérisé en ce que la première tige (106) supporte deuxième tige (117) disposée dans le prolongement de celle-ci et destinée à être rattachée par une extrémité (118) au deuxième élément à déplacer, ladite deuxième tige (117) étant apte à être bloquée en rotation et entraînée en translation par l'intermédiaire d'un deuxième arbre d' entraînement (112, 115) traversant la base et relié à des moyens d' entraînement en rotation (113, 111). The present invention relates to a telescopic linear actuator for moving a first (10b) and a second (10a) element relative to a fixed element (102), comprising a base (101), intended to be attached to the fixed element ( 102), and serving as a housing for a first rod (106) locked in rotation and adapted to be driven in translation by means of a drive shaft (104) intended to be connected to drive means (107). ) in rotation, the first rod being intended to be attached by one end (108) to the first element to move, characterized in that the first rod (106) supports second rod (117) arranged in the extension thereof and intended to be attached by one end (118) to the second element to be displaced, said second rod (117) being able to be locked in rotation and driven in translation via a second drive shaft (112, 115) passing through the base and connected to rotating drive means (113, 111).

Linear telescopic actuator for moving a first and a second element relative to a stationary element

The invention relates to a linear telescopic actuator for moving a first (10b) and a second (10a) element relative to a stationary element (102). Said actuator comprises a base (101) that is to be connected to the stationary element (102) and is used as a cavity for a first rotationally locked rod (106) which can be translated by a drive shaft (104) that is to be connected to rotational driving means (107). One end (108) of said first rod is to be connected to the first element that is to be moved. The actuator is characterized in that the first rod (106) supports a second rod (117) which is aligned therewith and one end (118) of which is to be connected to the second element that is to be moved. Said second rod (117) can be rotationally locked and can be translated by a second drive shaft (112, 115) which extends through the base and is connected to rotational driving means (113, 111).

TELESCOPIC LINEAR ACTUATOR FOR MOVING A FIRST AND A SECOND ELEMENTS RELATIVELY TO A FIXED ELEMENT

La présente invention se rapporte à un actionneur linéaire télescopique pour déplacer un premier et un second éléments relativement à un élément fixe (102), comprenant une base (101), destinée à être rattachée à l'élément fixe (102), et servant de logement à une première tige (106) bloquée en rotation et apte à être entraînée en translation par l'intermédiaire d'un arbre (104) d'entraînement destiné à être relié à des moyens d'entraînement (107) en rotation, la première tige étant destinée à être rattachée par une extrémité (108) au premier élément à déplacer,caractérisé en ce que la première tige supporte deuxième tige (117) disposée dans le prolongement de celle-ci et destinée à être rattachée par une extrémité (118) au deuxième élément à déplacer, ladite deuxième tige étant apte à être bloquée en rotation et entraînée en translation par l'intermédiaire d'un deuxième arbre d'entraînement (112, 115) traversant la base et relié à des moyens d'entraînement en rotation (113, 111). The present invention relates to a telescopic linear actuator for moving a first and a second element relative to a fixed element (102), comprising a base (101), intended to be attached to the fixed element (102), and serving as a housing to a first rod (106) locked in rotation and adapted to be driven in translation by means of a drive shaft (104) intended to be connected to rotating drive means (107), the first rod being intended to be attached by one end (108) to the first element to be displaced, characterized in that the first rod supports second rod (117) arranged in the extension thereof and intended to be attached by one end (118). to the second element to be displaced, said second rod being able to be locked in rotation and driven in translation by means of a second drive shaft (112, 115) passing through the base and connected to rotating drive means (113, 111).

Linear telescopic actuator for moving a first and a second element relative to a stationary element

The invention relates to a linear telescopic actuator for moving a first ( 10 b ) and a second ( 10 a ) element relative to a stationary element ( 102 ). Said actuator comprises a base ( 101 ) that is to be connected to the stationary element ( 102 ) and is used as a cavity for a first rotationally locked rod ( 106 ) which can be translated by a drive shaft ( 104 ) that is to be connected to rotational driving means ( 107 ). One end ( 108 ) of said first rod is to be connected to the first element that is to be moved. The actuator is characterized in that the first rod ( 106 ) supports a second rod ( 117 ) which is aligned therewith and one end ( 118 ) of which is to be connected to the second element that is to be moved. Said second rod ( 117 ) can be rotationally locked and can be translated by a second drive shaft ( 112, 115 ) which extends through the base and is connected to rotational driving means ( 113, 111 ).

Gas turbine engine

FIELD: engines and pumps. SUBSTANCE: gas turbine engine comprises outlet device with inner circuit discharge system and axial displacement mechanism. Inner circuit discharge system comprises shaped body, inner circuit outlet nozzle around said shaped central body making the cannel there between and plane of displacement at outlet nozzle peripheral end. Axial shift mechanism can vary shift plane area owing to inner circuit outlet nozzle shift. In compliance with second version, gas turbine engine comprises inner circuit outlet nozzle with strip mixer, taper shaped central body and combined outlet nozzle. Strip mixer can displace in axis between first and second positions. Peripheral end of outlet nozzle features inner circuit channel cross-section of maximum area at first position and minimum area at second position. Outer circuit channel cross-section has minimum area at first position and maximum area at second position. EFFECT: decreased noise at takeoff and losses at cruising regime. 20 cl, 5 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 504 681 (13) C2 (51) МПК F02K 1/08 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2008129647/06, 23.01.2007 (24) Дата начала отсчета срока действия патента: 23.01.2007 (73) Патентообладатель(и): РОЛЛС-РОЙС Пи-Эл-Си (GB) (43) Дата публикации заявки: 27.03.2010 Бюл. № 9 2 5 0 4 6 8 1 (45) Опубликовано: 20.01.2014 Бюл. № 2 (56) Список документов, цитированных в отчете о поиске: US 4527388 А, 09.07.1985. ЕР 1344928 А2, 17.09.2003. US 5771681 А, 30.06.1998. US 3273345 А, 20.09.1966. US 3829020 А, 13.08.1974. SU 422301 A1, 24.08.1978. 2 5 0 4 6 8 1 R U (86) Заявка PCT: GB 2007/000202 (23.01.2007) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 18.09.2008 (87) Публикация заявки РСТ: WO 2007/093760 (23.08.2007) Адрес для переписки: 107061, Москва, Преображенская пл., 6, ООО "Вахнина и Партнеры" (54) ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ (57) Реферат: Газотурбинный ...

Variable area nozzle for gas turbine engine

A variable area fan nozzle comprises an actuator flap and a follower flap. The actuator flap has a portion in contact with a portion of the follower flap. A bias member biases the follower flap outwardly. An actuator actuates the actuator flap inwardly and outwardly to, in turn, move the follower flap against the bias member and to vary an area of an exhaust nozzle. The flap actuator is operable to drive the actuator flap out of contact with the follower flap into a thrust reverser position.

NACELLE OF A TURBOREACTOR COMPRISING A REVERSING SHUTTER AND A DELAYED DEPLOYMENT SYSTEM

NACELLE D’UN TURBOREACTEUR COMPORTANT UN VOLET INVERSEUR ET UN SYSTEME DE DEPLOIEMENT A RETARDEMENT L’invention concerne une nacelle (102) d’un turboréacteur double flux (100) et qui comporte une structure fixe (201), un capot fixe (206) et un capot mobile (207) qui est mobile en translation entre une position avancée et une position reculée, un vérin (209) pour déplacer le capot mobile (207), un volet inverseur (104) mobile sur le capot mobile (207), et un système de déploiement (150) comportant un premier coulisseau (156) solidaire du capot mobile (207) et mobile en translation, une première rainure (154) comportant une première partie (154a) et une deuxième partie (154b) courbe et solidaire de la structure fixe (201), un deuxième coulisseau (158) mobile en translation dans la première rainure (154), une première bielle (160) mobile en rotation sur le premier coulisseau (156) et sur le deuxième coulisseau (158) entre le premier coulisseau (156) et une première extrémité, et une deuxième bielle (162) articulée sur la première extrémité de la première bielle (160), et articulée sur le volet inverseur (104), où la tige du vérin (209) est articulée sur la première bielle (160), et où lorsque le premier coulisseau (156) se déplace de la position avancée à la position reculée, le deuxième coulisseau (158) se déplace le long de la première partie (154a) et à partir du moment où le premier coulisseau (156) atteint la position reculée, le deuxième coulisseau (158) se déplace le long de la deuxième partie (154b). Un tel agencement permet un décalage entre la translation du capot mobile et la rotation du volet inverseur. Fig. 5 The invention relates to a nacelle (102) of a double-flow turbojet engine (100) and which comprises a fixed structure (201), a fixed cover (206). and a movable cover (207) which is movable in translation between an advanced position and a retracted position, a jack (209) for moving the movable cover (207), a reversing flap (104) movable on the movable ...

Controlling the aerodynamic drag of a gas turbine engine during a shutdown state

Nacelle for propulsion assembly for accommodating turbojet of aircraft, has controlling unit controlling movement of parts between possible moving positions so as to generate asymmetric configuration of parts with respect to plane

The nacelle has two moving parts (20, 21) i.e. deployable covers, arranged on a side of a vertical symmetry plane of the nacelle, where the parts are moved into discrete positions. The parts contain or release a secondary flow portion based on the moved position. A controlling unit controls movement of each moving part between possible moving positions so as to generate an asymmetric configuration of the moving parts with respect to the plane of the nacelle. The parts are arranged within rear part of a secondary flow path and opposite to a variable-section nozzle. An independent claim is also included for a method for optimizing engine speed of a propulsion unit of an aircraft.

A gas turbine engine exhaust nozzle

Variable nozzle adapting to series turbine/rocket combined power and method

本发明公开了一种适应串联式涡轮/火箭组合动力的可变喷管及方法，包括：中心塞式喷管；所述中心塞式喷管具有轴对称发动机燃烧室，在轴对称发动机燃烧室中心沿轴向布置移动导轨，在移动导轨末端安装有中心塞，且中心塞能沿所述移动导轨滑动。该可变喷管有效保证飞行器在亚音速飞行时的涡轮发动机与超音速飞行时的火箭发动机燃烧室内的亚音速气体膨胀至音速并形成推力。

Expandable nozzle of rocket engine

FIELD: rocket construction. SUBSTANCE: invention relates to the field of rocket construction and can be used in the development and manufacture of rocket engines with nozzles of a large degree of expansion for the upper stages of rockets and spacecraft. Sliding nozzle of the rocket engine contains a stationary bell and a shiftable nozzle, mounted on the shifted nozzle, spring-loaded fasteners of the extended position, the nozzle with the profiled end part and the corresponding annular groove on the outer surface of the stationary bell. Fixators are made in the form of plates, installed in a plane perpendicular to the axis of the nozzle, in the corresponding grooves of the shifted nozzle. Profile of the end part of the fasteners is made in the form of two conical surfaces intersecting along a small diameter. Angle of the half-solution of the conical surface facing the wide end towards the cutoff side of the nozzle satisfies the condition protected by the present invention. Second tapered surface coincides with the corresponding surface of the annular groove on the outer surface of the fixed bell and the angle of its half-solution satisfies the condition protected by the present invention. EFFECT: invention makes it possible to reduce the mass of the nozzle and increase its reliability. 1 cl, 4 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 660 978 C1 (51) МПК F02K 9/97 (2006.01) F02K 1/09 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F02K 9/976 (2017.08); F02K 1/09 (2017.08) (21)(22) Заявка: 2017100770, 10.01.2017 (24) Дата начала отсчета срока действия патента: Дата регистрации: 11.07.2018 (45) Опубликовано: 11.07.2018 Бюл. № 20 2 6 6 0 9 7 8 R U (54) Раздвижное сопло ракетного двигателя (57) Реферат: Изобретение относится к области ракетостроения и может быть использовано при разработке и изготовлении ракетных двигателей с соплами большой степени расширения для верхних ступеней ракет и космических ...

Gas exhaust cone for an aircraft turbojet, corresponding turbojet and engine plant

AIRCRAFT ENGINE ASSEMBLY COMPRISING AT LEAST TWO REAR ENGINE FASTENERS AXIALLY SHIFTED FROM EACH OTHER

Afin de réduire la largeur des moyens d'accrochage entre la partie arrière d'un moteur d'aéronef et son mât d'accrochage, l'invention prévoit un ensemble moteur dont les moyens d'accrochage comportent un ensemble d'attaches moteur arrière (7a) comprenant : - une première manille (7a1) agencée dans un plan longitudinal et vertical médian ; - une seconde manille (7a2) agencée sensiblement tangentiellement au carter inter-turbine (46) ; et - une attache moteur arrière (7a3) de reprise transversale des efforts, décalée axialement vers l'arrière par rapport aux première et seconde manilles (7a1, 7a2), et comprenant un pion de cisaillement (64) orienté selon une direction verticale (Z) de l'ensemble moteur.

GONDOLA WITH ADJUSTABLE EXHAUST SECTION

1. Гондола (1) турбореактивного двигателя, содержащая заднюю секцию (5) с внутренней неподвижной конструкцией (9), расположенной вокруг хвостовой части двигательного отсека и образующей совместно с реактивным соплом (6) откалиброванную выпускную секцию (10) для вентиляции двигательного отсека с помощью расположенных в выпускной секции разделительных средств, отличающаяся тем, что разделительные средства подразделены на жесткие разделители (11, 12), предназначенные для обеспечения постоянного интервала, и компенсирующие элементы (13), которые компенсируют взаимные перемещения турбореактивного двигателя и гондолы. ! 2. Гондола (1) по п.1, отличающаяся тем, что компенсирующие элементы (13) прикреплены к жестким разделителям (11, 12). ! 3. Гондола (1) по п.1, отличающаяся тем, что компенсирующие элементы (13) образуют клапан. ! 4. Гондола (1) по любому из пп.1-3, отличающаяся тем, что жесткие разделители (11, 12) установлены во внутренней неподвижной конструкции (9). ! 5. Гондола по любому из пп.1-3, отличающаяся тем, что жесткие разделители установлены в реактивном сопле. ! 6. Гондола (1) по любому из пп.1-3, отличающаяся тем, что жесткие разделители (11, 12) состоят из совокупности U-образных элементов, образующих разделители, распределенные по периферии выпускной секции (10). ! 7. Гондола (1) по любому из пп.1-3, отличающаяся тем, что компенсирующие элементы (13) состоят из совокупности элементов, первый конец которых прикреплен к жестким разделителям (11), а второй конец свободен. ! 8. Гондола (1) по п.7, отличающаяся тем, что компенсирующие элементы (13) выполнены в форме кольца (15), содержащего ряд продольных пазов (16), образующих продольные пальцы (17). ! 9. Гондола (1) по РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2010 109 801 (13) A (51) МПК B64D 33/04 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2010109801/11, 19.06.2008 (71) Заявитель(и): ЭРСЕЛЬ (FR) Приоритет(ы): (30) ...

INTERNAL DESIGN OF THE AIRCRAFT GONDOLA

1. Внутренняя конструкция (8) гондолы (1) турбореактивного двигателя (8) воздушного судна, концентрически расположенная вдоль продольной оси (Δ'), проходящей через центр указанной внутренней конструкции (8), и содержащая активные подвижные элементы (103) и пассивные подвижные элементы (101), причем каждый активный подвижный элемент (103) выполнен из одной или нескольких подвижных частей (103a, 103b, 103c), при этом каждый активный подвижный элемент (103) выполнен так, чтобы приводить в движение смежные с ним пассивные подвижные элементы (101), при этом внутренняя конструкция (8) имеет первое номинальное положение, в котором между активными подвижными элементами (103) и пассивными подвижными элементами (101) имеется аэродинамическая непрерывность, второе положение, в котором активные подвижные элементы (103) выступают за пассивные подвижные элементы (101) в направлении наружу от внутренней конструкции относительно центра внутренней конструкции (8) после перемещения пассивных подвижных элементов (101) посредством активных подвижных элементов (103), и третье положение, в котором активные подвижные элементы (103) выступают за пассивные подвижные элементы (101) в направлении внутрь внутренней конструкции (8) относительно центра внутренней конструкции (8) после перемещения пассивных подвижных элементов (101) посредством активных подвижных элементов (103).2. Внутренняя конструкция (8) гондолы по п.1, в которой по меньшей мере две подвижных части (103a, 103b, 103c) взаимодействуют друг с другом через ведущее звено (111, 121, 131), имеющееся в ведущей подвижной части (103b), подлежащей приведению в движение, и ведомое звено (110, 120, 130), имеющееся в одной или нескольких подвижных ча РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК B64D 33/04 (13) 2013 132 646 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2013132646/11, 30.11.2011 (71) Заявитель(и): ЭРСЕЛЬ (FR) Приоритет(ы): (30) Конвенционный приоритет: 20.12. ...

Gas ejecting nozzle for ducted-fan turbine engine, has slot displaced between closed position in which slot blocks openings to reproduce form of external surface and deployed position in which slot projects in channel to modify sections

L'invention concerne une tuyère (32) d'éjection des gaz pour turbomachine à double flux, comportant un corps central (34), un capot primaire (36) entourant le corps central pour délimiter un canal primaire (38), et un capot secondaire (40) entourant le capot primaire pour délimiter un canal secondaire (42). Le capot primaire (36) comporte une pluralité d'ouvertures longitudinales (48) réparties sur la circonférence de sa surface externe, disposées en regard de la section de col (44) et/ou d'éjection (46) de la tuyère et à l'intérieur de chacune desquelles est logé un créneau (50) de forme complémentaire, chaque créneau étant apte à être déplacé entre deux positions extrêmes, une position fermée dans laquelle il obstrue l'ouverture considérée de façon à reproduire la forme de la surface externe du capot primaire, et une position déployée dans laquelle il fait saillie radialement dans le canal secondaire (42) de façon à faire varier la section de col et/ou d'éjection de la tuyère.

INSTALLATION FOR RELEASING OR CLOSING THE INTAKE AIR INLET OR THE EXHAUST GAS EXHAUST FROM A TURBINE.

CENTRAL BODY FOR EXHAUST CHANNEL OF A TURBOJET, TURBOREACTOR

AIRCRAFT ENGINE ASSEMBLY COMPRISING AT LEAST TWO REAR ENGINE FASTENERS AXIALLY SHIFTED FROM EACH OTHER

DOUBLE FLOW TURBOJET PIPE ASSEMBLY

Variable section end-nozzle propulsion system for aircraft

Improvements to the discharge nozzles of thruster jets

GUIDED FOLDING BLOWER HOOD, FOR AIRCRAFT ENGINE ASSEMBLY

EJECTION TUBE FOR AIRBORNE AIR TURBOREACTOR WITH TWO SEPARATE FLOWS WITH DEPLOYABLE SECONDARY COVER AND RETRACTABLE CENTRAL BODY

L'invention concerne une tuyère d'éjection (36) pour turboréacteur d'avion à double flux séparés comprenant un corps central annulaire (32), un capot primaire annulaire (28) entourant le corps central pour délimiter un canal d'écoulement de flux chaud (26), et un capot secondaire annulaire (30) entourant le capot primaire pour délimiter un canal d'écoulement de flux froid (24), le corps central et le capot secondaire comprenant chacun une partie fixe (32a, 30a) et une partie mobile (32b, 30b) raccordée à une extrémité aval de la partie fixe, la partie mobile (32b) du corps central étant apte à se rétracter longitudinalement vers l'amont par rapport à la partie fixe (32a), la partie mobile (30b) du capot secondaire étant apte à se déployer longitudinalement vers l'aval par rapport à la partie fixe (30a). An exhaust nozzle (36) for a split-flow aircraft turbojet engine includes an annular central body (32), an annular primary shroud (28) surrounding the central body for delimiting a flow channel. a secondary annular hood (30) surrounding the primary hood to define a cold flow flow channel (24), the central body and the secondary hood each comprising a fixed portion (32a, 30a) and a mobile part (32b, 30b) connected to a downstream end of the fixed part, the movable part (32b) of the central body being able to retract longitudinally upstream with respect to the fixed part (32a), the movable part ( 30b) of the secondary cover being adapted to extend longitudinally downstream relative to the fixed portion (30a).

DOUBLE FLOW REACTOR DISTRIBUTOR ASSEMBLY AND METHOD FOR OPERATING THE SAME

Ensemble de distributeur (11) pour réacteur d'aéronef à turbine à gaz, l'ensemble de distributeur comprenant une nacelle (24), un capot (22) de bloc réacteur placé au moins partiellement dans la nacelle de façon qu'une canalisation annulaire de dérivation (26) de soufflante soit définie entre eux, le capot de bloc réacteur et la nacelle étant alignés de manière sensiblement concentrique l'un par rapport à l'autre. Le capot de bloc réacteur comporte une première partie de capot placée dans la nacelle et un ensemble de capot (23) en deux parties s'étendant en aval de la première partie de capot, l'ensemble de capot en deux parties comportant une paire de parties arquées (68, 70), chacune des parties arquées étant repositionnable à l'intérieur de la canalisation de dérivation de soufflante afin de modifier une section du conduit de dérivation de soufflante. A distributor assembly (11) for a gas turbine engine aircraft, the manifold assembly comprising a nacelle (24), a reactor block cover (22) at least partially located in the nacelle such that an annular pipeline blower bypass (26) is defined between them, the reactor block cover and the nacelle being aligned substantially concentrically with respect to each other. The engine block cover has a first bonnet portion in the nacelle and a two-part bonnet assembly (23) extending downstream of the first bonnet portion, the two-piece bonnet assembly having a pair of baffles. arcuate portions (68,70), each of the arcuate portions being repositionable within the fan bypass line to modify a section of the fan bypass duct.

Improvements made to variable section conduits for a fluid

THREADED ROD OF A SYSTEM FOR DEPLOYING A DEPLOYABLE DIVERGENT OF PROPELLER

Le divergent comprend une partie de divergent fixe (10) et une partie de divergent mobile (12) aptes à occuper une position rétractée et une position déployée. La tige filetée (22) a une tête apte à être supportée par un support solidaire de la partie de divergent fixe en coopérant avec des moyens d'entraînement en rotation de la tige filetée, et une queue (22A) apte à être insérée dans un manchon de maintien (34) solidaire de la partie de divergent fixe (10). La tige filetée est apte à coopérer avec un écrou (36) solidaire de la partie de divergent mobile (12) de sorte que la rotation de la tige provoque le déplacement de la partie de divergent mobile. La queue (22A) présente un renflement (42) ayant au moins une gorge (44A) axialement traversante. The divergent comprises a fixed divergent portion (10) and a movable diverging portion (12) adapted to occupy a retracted position and an extended position. The threaded rod (22) has a head adapted to be supported by a support integral with the fixed divergent portion cooperating with means for driving the threaded rod in rotation, and a tail (22A) adapted to be inserted into a holding sleeve (34) secured to the fixed diverging portion (10). The threaded rod is adapted to cooperate with a nut (36) integral with the movable diverging portion (12) so that rotation of the rod causes displacement of the movable diverging portion. The tail (22A) has a bulge (42) having at least one groove (44A) axially through.

Reactor nozzle opening regulator

NACELLE WITH ADAPTABLE OUTPUT SECTION

La présente invention de rapporte à une nacelle (1) pour turboréacteur comprenant une section arrière (5) présentant une structure interne (9) destinée à entourer une partie arrière d'une chambre de combustion du turboréacteur et à délimiter, avec une tuyère d'éjection (6), une section de sortie calibrée de la ventilation de la chambre de combustion du turboréacteur à l'aide de moyens d'écartement disposés dans la section de sortie, caractérisée en ce que les moyens d'écartement se décomposent en des moyens d'écartement rigides (11) conçus pour assurer un écartement constant, et en des moyens de compensation (13) conçus de façon à pouvoir s'adapter aux mouvements relatifs du turboréacteur par rapport à la nacelle. The present invention relates to a nacelle (1) for a turbojet comprising a rear section (5) having an internal structure (9) intended to surround a rear part of a combustion chamber of the turbojet and to delimit, with a nozzle of ejection (6), a calibrated output section of the ventilation of the combustion chamber of the turbojet engine by means of spacing means arranged in the outlet section, characterized in that the spacing means are decomposed into means rigid spacers (11) designed to ensure a constant spacing, and compensation means (13) designed to be able to adapt to the relative movements of the turbojet relative to the nacelle.

DOUBLE FLOW TURBOREACTOR HOOD.

Convergent-Divergent Nozzle

NACELLE WITH ADAPTABLE OUTPUT SECTION

GAS EJECTION NOZZLE FOR A REACTION ENGINE AND A REACTION ENGINE EQUIPPED WITH SUCH A NOZZLE, PARTICULARLY A SEPARATE FLOW TYPE ENGINE.

STATOREACTOR FOR AIRCRAFT WITH SUPERSONIC AND HYPERSONIC FLIGHT

Turbogenerator

本发明提供了一种涡轮发动机，其包括：第一壳体，具有进气口；第二壳体；第三壳体，固定连接于第一壳体和第二壳体且连通于第一壳体和第二壳体；中心体，设置于第三壳体内，且中心体的外壁面与第三壳体的内壁面形成旋转爆震燃烧室；油路组件，受控连通于旋转爆震燃烧室；点火器，用于对进入旋转爆震燃烧室内的燃料和空气形成的燃气进行点火，进而燃气旋转爆震燃烧；压气机，对经由进气口进入第一壳体内的空气进行压缩处理；涡轮机，在第二壳体内的气体的驱动下旋转运动；以及主轴，用于连接压气机和涡轮机，以使涡轮机带动压气机运动。本发明的涡轮发动机的结构紧凑、燃烧效率高，降低了发动机的耗油率，提升了发动机的推重比和整体性能。

Variable area fan nozzle stiffeners and placement

A nacelle assembly for a high-bypass gas turbine engine is disclosed and includes a variable area fan nozzle (VAFN) (45) including at least one second fan nacelle section (42) movable relative to the first fan nacelle section (40) to modify an area of the bypass flow path (50). At least one stiffener (64) is mounted between the first fan nacelle section (40) and the second fan nacelle section (42). The stiffeners (64) modify mode shapes and natural frequencies to substantially reduce or eliminate flutter within operating ranges that are produced by unsteady aerodynamic loads.

Inner structure for an aircraft nacelle

本发明涉及一种用于飞行器涡轮风扇发动机的机舱（1）的内部结构（8），其包括多个主动（103）和被动（101）活动元件。每个主动活动元件（103）由一个或多个活动部分（103a，103b）组成，每个主动活动元件（103）被配置以驱动相邻被动活动元件（101），使得内部结构（103）具有第一额定位置，第二位置和第三位置，其中，在第二位置主动可活动元件（103）从被动可活动元件（101）朝向内部结构（8）的外部突出，其中在第三位置主动可活动元件（103）从被动可活动元件（101）朝向内部结构（8）的内部突出。本发明还涉及一种机舱，包括外部结构和这种内部结构。

MOBILE POINT FOR TUYERE WITH VARIABLE COLLAR SECTION OF AEROSPATIAL ENGINE PROPELLER AND TUYERE EQUIPPED WITH SUCH A POINTEAU.

THREADED ROD OF A DEPLOYING SYSTEM OF A DEPLOYABLE PROPELLANT DIVERGENT

Variable area nozzle orifices

Nacelle with an adaptable outlet section

The present invention relates to a jet engine nacelle (1) comprising an aft section (5) having an internal structure (9) intended to surround an aft portion of an engine compartment and to define, with an exhaust nozzle (6), a calibrated outlet section for the ventilation of the engine compartment by way of spacing means arranged in the outlet section, characterized in that the spacing means are divided into rigid spacing means (11) designed to provide a constant spacing and into compensating means (13) designed so as to be able to adapt to the relative movements of the jet engine with respect to the nacelle.

GAS EJECTION NOZZLE FOR A REACTION ENGINE AND A REACTION ENGINE EQUIPPED WITH SUCH A NOZZLE, PARTICULARLY A SEPARATE FLOW TYPE ENGINE.

L'invention concerne une tuyère d'éjection à section de sortie variable pour moteur à réaction. Une jupe annulaire (4) mobile axialement est disposée autour de la paroi fixe de tuyère (2) de façon à pouvoir être déplacée axialement entre une position amont où ladite jupe est située en retrait autour de la paroi fixe (2), et une position aval où elle se prolonge à l'arrière de la section de sortie de cette paroi. Une couronne semi-flexible (8) peut être prévue pour assurer la jonction entre la jupe mobile (4) et la paroi fixe (2), cette couronne venant en appui élastique autour de la paroi (2). L'invention permet en particulier d'augementer la section de sortie d'une tuyère centrale à gaz chaud afin d'assurer une réduction de la poussée du jet chaud lorsque les inverseurs de poussée sont mis en œuvre sur le jet froid. Elle permet également dans certaines conditions de vol, notamment par temps chaud en phase de décollage, de réduire la température des gaz chauds de sortie et de permettre ainsi d'accroître la vitesse du générateur de gaz et d'augmenter la poussée en jet direct. The invention relates to an ejection nozzle with variable outlet section for a jet engine. An axially movable annular skirt (4) is arranged around the fixed nozzle wall (2) so as to be able to be displaced axially between an upstream position where said skirt is set back around the fixed wall (2), and a position downstream where it extends to the rear of the outlet section of this wall. A semi-flexible ring (8) can be provided to provide the junction between the movable skirt (4) and the fixed wall (2), this ring coming to bear resiliently around the wall (2). The invention makes it possible in particular to increase the outlet section of a central hot gas nozzle in order to ensure a reduction in the thrust of the hot jet when the thrust reversers are implemented on the cold jet. It also makes it possible, under certain flight conditions, in particular in hot ...

Nozzle with yaw vectoring vane

Rotary detonation combustion chamber with adjustable combustion chamber width

本发明提出了一种可调节燃烧室宽度的旋转爆震燃烧室，包括旋转爆震燃烧室本体和燃烧室宽度调节系统。利用供气孔射流在燃烧室内部形成一个包裹弧形鳞片的气膜，其中，气膜厚度可通过改变供气通道内的气流流量进行调节，即利用供气气流实现了燃烧室内柱直径的改变，进而达到燃烧室宽度可调节这一目的。此外，气膜还可以有效地减小弧形鳞片和燃烧室内柱的热负荷，提高使用寿命。本发明可以用于爆震推进和地面发电等领域。

Process for the preparation of 1-cyano-3-alkyl- [1, 1, 0] bicyclobutanes

Method of operating a turbofan engine cowl assembly

An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.

Nacelle with adjustable outlet section

Гондола (1) турбореактивного двигателя содержит заднюю секцию (5) с внутренней неподвижной конструкцией (9), расположенной вокруг хвостовой части двигательного отсека и образующей совместно с реактивным соплом (6) откалиброванную выпускную секцию (10) для вентиляции двигательного отсека с помощью расположенных в выпускной секции разделительных средств. Указанные разделительные средства подразделены на жесткие разделители (11, 12), предназначенные для обеспечения постоянного интервала, и компенсирующие элементы (13), которые компенсируют взаимные перемещения турбореактивного двигателя и гондолы. Компенсирующие элементы состоят из совокупности элементов, первый конец которых прикреплен к жестким разделителям, а второй конец свободен. Снижается нагрузка на гондолу, возникающая в результате относительного перемещения и деформирования турбореактивного двигателя. 2 н. и 8 з.п. ф-лы, 6 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 469 923 (13) C2 (51) МПК B64D 33/04 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2010109801/11, 19.06.2008 (24) Дата начала отсчета срока действия патента: 19.06.2008 (73) Патентообладатель(и): ЭРСЕЛЬ (FR) R U Приоритет(ы): (30) Конвенционный приоритет: 20.08.2007 FR 0705920 (72) Автор(ы): ЛЕ ДОКТ Тьерри Жак Альбер (FR) (43) Дата публикации заявки: 27.09.2011 Бюл. № 27 2 4 6 9 9 2 3 (45) Опубликовано: 20.12.2012 Бюл. № 35 (56) Список документов, цитированных в отчете о поиске: ЕР 0867366 А, 30.09.1998. US 5906097 А, 25.05.1999. RU 2000129519 А, 10.11.2002. US 2005188676 A1, 01.09.2005. US 5704207 A, 06.01.1998. 2 4 6 9 9 2 3 R U (86) Заявка PCT: FR 2008/000859 (19.06.2008) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 22.03.2010 (87) Публикация заявки РСТ: WO 2009/024660 (26.02.2009) Адрес для переписки: 191002, Санкт-Петербург, а/я 5, ООО "Ляпунов и партнеры" (54) ГОНДОЛА С РЕГУЛИРУЕМОЙ ВЫПУСКНОЙ СЕКЦИЕЙ (57) Реферат: Гондола (1) турбореактивного двигателя ...

Variable geometry jet for jet drive

The jet has an outer jet (5) through the casing of the jet drive, and a variable-geometry jet with one or more jets in the interior which can be moved axially relative to the outer jet. The form of the cross section of the inner jets in the rest position corresponds to the run of the flow lines, so that resistance is only increased by friction against the inner jets.

Variable area fan nozzle

A gas turbine engine

Variation in the available mixing plane areas (5a, 5b) in an exhaust arrangement of a gas turbine engine (1, 21) enables alteration and configuration for better thermal cycle performance of that engine (1, 21). A shaped centre fairing (6) is associated with an exit nozzle (7) and a bypass duct (9) such that channels ( 2, 3) between the fairing (6), nozzle exit (7) and duct (9) can be adjusted to change the available areas (5a, 5b). Such variation is achieved by relative axial displacement, typically of the exit nozzle (7) using an appropriate mechanism (10).

Gas ejection cone for an aircraft turbojet equipped with a device for generating turbulence in a primary flow limiting jet noise

The present invention relates to a gas ejection cone (8) for an aircraft turbojet, the cone having a hollow main body (30) defining, on the outside, a radially inner skin (36) of an annular primary flow channel. According to the invention, it also comprises a device (34) for generating turbulence in the primary flow limiting the jet noise, mounted so as to move on the main body so as to be able to be displaced from an extracted position in which it projects toward the downstream in relation to a downstream end of the hollow main body, and a retracted position in which it is retracted into this hollow main body, and vice versa. Furthermore, the device (34) comprises a cylindrical support body (42) having an axis parallel to an axis (32) of the ejection cone, as well as at least one fin (46) supported by the body (42).