Поиск патентов

Настройки

Глубина выборки

Укажите год

Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

Подробнее

Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

Подробнее

Форма поиска

Ключевые слова. Может быть несколько по одной на строку

Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка

Автор

Ведите корректный номера.

Владелец

Ведите корректный номера.

Классы IPC

Ведите корректный номера.

Классы CPC

Ведите корректный номера.

Начиная с года

Укажите год

Заканчивая годом

Укажите год

Применить Всего найдено 13099. Отображено 103.

08-01-2013 дата публикации

Air-blast fuel-injector with shield-cone upstream of fuel orifices

Номер: US0008347630B2

Автор: Jeffery A. Lovett, Frederick C. Padget, John W. Mordosky, Shawn M. McMahon, LOVETT JEFFERY A, PADGET FREDERICK C, MORDOSKY JOHN W, MCMAHON SHAWN M, LOVETT JEFFERY A., PADGET FREDERICK C., MORDOSKY JOHN W., MCMAHON SHAWN M.

Принадлежит: United Technologies Corp, UNITED TECHNOLOGIES CORP, LOVETT JEFFERY A, PADGET FREDERICK C, MORDOSKY JOHN W, MCMAHON SHAWN M, LOVETT JEFFERY A., PADGET FREDERICK C., MORDOSKY JOHN W., MCMAHON SHAWN M.

An air-blast fuel nozzle assembly includes a housing having an inner surface defining an interior chamber around a central axis. The inner surface terminates in an exit aperture. An air swirler pneumatically communicates with the interior chamber and has vanes operative to impart a swirling motion to air passing across the vanes and into the interior chamber. A fuel injection assembly includes a nozzle portion extending along the central axis and having a plurality of outlets circumferentially-arranged around the central axis that are directed into the interior chamber toward the inner surface of the housing. A shield extends radially outwardly from the nozzle portion upstream of the plurality of outlets. The shield extends between a base at the nozzle section and a free tip end such that the shield extends partially across the interior chamber toward the inner surface.

Подробнее

Номер записи: 1

06-06-2006 дата публикации

Apparatus for driving an accessory gearbox in a gas turbine engine

Номер: US0007055330B2

Автор: Guy Wallace Miller, MILLER GUY WALLACE

Принадлежит: United Technologies Corp, UNITED TECHNOLOGIES CORP

A mechanical drive system for an accessory gearbox of a gas turbine engine is provided. The gas turbine engine includes a high-pressure drive shaft and a low-pressure drive shaft. The mechanical drive system includes a tower shaft and a lay shaft. The tower shaft is connected by a first gear arrangement to the low-pressure drive shaft of the gas turbine engine. The lay shaft is connected by a second gear arrangement to the first tower shaft, and connected to the accessory gearbox.

Подробнее

Номер записи: 2

22-01-2013 дата публикации

Gas turbine engine systems involving variable nozzles with sliding doors

Номер: US0008356483B2

Автор: Dale William Petty, Shawn M. McMahon, Michael Joseph Murphy, Sean P. Zamora, Timothy A. Swanson, PETTY DALE WILLIAM, MCMAHON SHAWN M, MURPHY MICHAEL JOSEPH, ZAMORA SEAN P, SWANSON TIMOTHY A, MCMAHON SHAWN M., ZAMORA SEAN P., SWANSON TIMOTHY A.

Принадлежит: United Technologies Corp, UNITED TECHNOLOGIES CORP, PETTY DALE WILLIAM, MCMAHON SHAWN M, MURPHY MICHAEL JOSEPH, ZAMORA SEAN P, SWANSON TIMOTHY A, MCMAHON SHAWN M., ZAMORA SEAN P., SWANSON TIMOTHY A.

A nozzle assembly for a gas turbine engine includes a door axially slidable relative to a passage in communication with a secondary flow path to regulate the secondary flow though the passage.

Подробнее

Номер записи: 3

02-02-2012 дата публикации

Blade outer air seal and repair method

Номер: US20120027574A1

Автор: Philip R. Belanger, Susan M. Tholen

Принадлежит: United Technologies Corp

An article of manufacture has a body formed in part of a first metal alloy and in part of a second metal alloy, the second metal alloy having a thermal coefficient of expansion that is less than the thermal coefficient of expansion of the first metal alloy. A BOAS segment for a gas turbine engine is disclosed wherein the formation of cracks due to thermal mechanical fatigue in the body of the disclosed BOAS segment is minimized, if not eliminated, through a unique construction of the disclosed BOAS segment, whether original equipment manufacture or a repaired blade outer air seal. A method for manufacture of a BOAS segment and a method for modifying a BOAS segment are disclosed.

Подробнее

Номер записи: 4

15-03-2012 дата публикации

Air-oil heat exchanger

Номер: US20120060466A1

Автор: Frederick L. Elsaesser, Frederick M. Schwarz

Принадлежит: United Technologies Corp

A heat exchange system for use in fluid operated equipment to provide air and working fluid heat exchanges to cool the working fluid in airstreams on a stream side of a wall. An actuator is mounted to be substantially located on a side of the wall opposite the stream side thereof having a positionable motion effector. A heat exchanger core having a plurality of passageway structures therein to enable providing the working fluid to, and removal therefrom. The heat exchanger core is mounted on the motion effector so as to be extendable and retractable thereby through the opening for selected distances into that region to be occupied by the airstreams.

Подробнее

Номер записи: 5

15-03-2012 дата публикации

Adaptive control for a gas turbine engine

Номер: US20120060505A1

Автор: James W. Fuller, Ramesh Rajagopalan

Принадлежит: United Technologies Corp

A method for controlling a gas turbine engine includes: generating model parameter data as a function of prediction error data, which model parameter data includes at least one model parameter that accounts for off-nominal operation of the engine; at least partially compensating an on-board model for the prediction error data using the model parameter data; generating model term data using the on-board model, wherein the on-board model includes at least one model term that accounts for the off-nominal operation of the engine; respectively updating one or more model parameters and one or more model terms of a model-based control algorithm with the model parameter data and model term data; and generating one or more effector signals using the model-based control algorithm.

Подробнее

Номер записи: 6

22-03-2012 дата публикации

Wireless sensor for an aircraft propulsion system

Номер: US20120068003A1

Автор: Nicholas Charles Soldner, Peter G. Smith, Sanjay Bajekal, Vijaya Ramaraju Lakamraju

Принадлежит: United Technologies Corp

A method is provided for wirelessly monitoring an aircraft propulsion system having a plurality of rotor blades, at least some of which rotor blades have an internal compartment. The method includes: providing a primary transducer having a primary coil, and one or more secondary transducers, each secondary transducer having a secondary coil connected to a sensor, wherein the secondary transducers are respectively disposed within the internal compartments; wirelessly powering the secondary transducers using a magnetic field generated by the primary transducer; monitoring at least one operational parameter from within each internal compartment using a respective sensor; and transmitting output signals from the secondary transducers to the primary transducer through the magnetic field, wherein the output signals are indicative of the monitored parameters.

Подробнее

Номер записи: 7

22-03-2012 дата публикации

Turbine shroud thermal distortion control

Номер: US20120070276A1

Автор: Gajawalli V. Srinivasan, Glenn N. Levasseur, Jun Shi, Kevin E. Green, Shaoluo L. Butler

Принадлежит: United Technologies Corp

A shroud suitable for use in combination with an adjacent rotor blade includes a leading portion comprising a first thickness, and a trailing portion adjacent to the leading portion and comprising a second thickness, wherein the second thickness is less than the first thickness so that stiffness in the leading portion is greater than in the trailing portion and radial expansion by thermal growth of the leading portion of the shroud is constrained.

Подробнее

Номер записи: 8

05-04-2012 дата публикации

Reduced gulp fluid reservoir

Номер: US20120080272A1

Автор: Larry W. Spires, Paul A. Dickie

Принадлежит: United Technologies Corp

An assembly includes a reservoir for holding a fluid, and a scavenge passage connected to the reservoir at a reservoir inlet. The scavenge passage returns the fluid from a delivery location to the reservoir. A bleed passage is connected in fluid communication between the reservoir and the scavenge passage.

Подробнее

Номер записи: 9

10-05-2012 дата публикации

Igniter with integral pressure sensing line

Номер: US20120110975A1

Автор: Hannes A. Alholm

Принадлежит: United Technologies Corp

An igniter device for a combustor system includes an igniter housing and a pressure sense passage. The igniter housing surrounds an electrode and an insulating body. The igniter has a tip to be positioned within a chamber for combustion. The pressure sense passage is attached to an exterior surface of the igniter housing. The pressure sense passage is configured to direct fluid to a pressure sensor.

Подробнее

Номер записи: 10

17-05-2012 дата публикации

Gas turbine engine with pylon mounted accessory drive

Номер: US20120117940A1

Автор: Michael Winter

Принадлежит: United Technologies Corp

A gas turbine engine includes an accessory gearbox within an engine pylon. The accessory components may be mounted within the engine pylon to save weight and space within the core nacelle as well as provide a relatively lower temperature operating environment.

Подробнее

Номер записи: 11

28-06-2012 дата публикации

Gearbox assembly

Номер: US20120159966A1

Автор: Brian D. Merry, Christopher M. Dye, Gabriel L. Suciu

Принадлежит: United Technologies Corp

An assembly for a gas turbine engine includes an intermediate case and a gearbox. The intermediate case defines an annular transition duct. The gearbox comprises a plurality of lobes and is integrally formed with the annular transition duct.

Подробнее

Номер записи: 12

05-07-2012 дата публикации

Wire Feed Pressure Lock System

Номер: US20120171382A1

Автор: Igor V. Belousov, Igor V. Gulyayev, Oleg G. Pankov, Richard S. Mullin

Принадлежит: United Technologies Corp

A pressure lock system passes a wire along a wire path from a wire source at a high pressure first region to a destination at a low pressure second region. The pressure lock system includes a pressure lock chamber. A first conduit has an interior positioned to pass the wire along the path and is mounted for rotation. A second conduit has an interior positioned to pass the wire from the pressure lock chamber and is also mounted for rotation. A motor may drive rotation of the first conduit and the second conduit. Pumps may maintain a pressure of the pressure lock chamber lower than a pressure of the first region.

Подробнее

Номер записи: 13

26-07-2012 дата публикации

Fuel injector assembly

Номер: US20120186259A1

Автор: James B. Hoke

Принадлежит: United Technologies Corp

A fuel injector assembly for a combustor is provided, including a fuel nozzle having an axial inflow swirler and one or more radial inflow swirlers spaced radially outward of the downstream end of the fuel nozzle and mounted to the combustor, wherein the airstreams produced by the swirlers airblast atomize fuel films produced by the fuel nozzle.

Подробнее

Номер записи: 14

02-08-2012 дата публикации

Continuous supply fluid reservoir

Номер: US20120192974A1

Автор: David L. Motto, Robert D. Szolomayer

Принадлежит: United Technologies Corp

An assembly for holding a fluid includes an auxiliary reservoir inside a main reservoir. The auxiliary reservoir includes an auxiliary reservoir shell with a fill passage at or near its bottom. The auxiliary reservoir shell also has a vent passage at or near its top. The fill passage and the vent passage fluidically connect the auxiliary reservoir to the main reservoir. A fluid inlet is located inside the main reservoir and outside of the auxiliary reservoir. A fluid outlet located inside the auxiliary reservoir between the fill passage and the vent passage.

Подробнее

Номер записи: 15

30-08-2012 дата публикации

Method and system for controlling a multivariable system with limits

Номер: US20120221156A1

Автор: James W. Fuller, Richard P. Meisner

Принадлежит: United Technologies Corp

A method and system for controlling a multivariable system. The method includes: (a) generating bias data as a function of model error in an on-board model; (b) updating a dynamic inversion algorithm with one or more model terms generated by the on-board model; (c) generating effector equation data by processing reference value data with the updated dynamic inversion algorithm, which effector equation data is indicative of one or more goal equations and one or more limit equations, and which reference value data is indicative of one or more goal values and one or more limit values and is determined as a function of predicted parameter data; (d) at least partially adjusting at least one of the reference value data and predicted parameter data for the model error using the bias data; and (e) generating one or more effector signals by processing the effector equation data with an optimization algorithm.

Подробнее

Номер записи: 16

20-09-2012 дата публикации

Damper pin

Номер: US20120237348A1

Автор: Christopher Corcoran, Seth J. Thomen

Принадлежит: United Technologies Corp

A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions.

Подробнее

Номер записи: 17

11-10-2012 дата публикации

Guided non-line of sight coating

Номер: US20120258256A1

Автор: Benjamin J. Zimmerman, Michael D. Greenberg

Принадлежит: United Technologies Corp

A method for applying a vapor deposition coating onto a substrate with a non line of sight or limited line of sight is disclosed. A vapor stream is provided in a chamber that is below atmospheric pressure. The vapor stream is impinged with a working gas that provides a flow that transports the vapor stream. The flow of the working gas is modified with a physical object that directs the flow to achieve a desired coating on the substrate.

Подробнее

Номер записи: 18

01-11-2012 дата публикации

Multiple core variable cycle gas turbine engine and method of operation

Номер: US20120272656A1

Автор: James W. Norris

Принадлежит: United Technologies Corp

A gas turbine engine system includes a fan assembly, a low pressure compressor, a low pressure turbine, a plurality of engine cores including a first engine core and a second engine core, and a control assembly. A primary flowpath is defined through the fan assembly, the low pressure compressor, the low pressure turbine, and the active engine cores. Each engine core includes a high pressure compressor, a combustor downstream from the high pressure compressor, and a high pressure turbine downstream from the combustor. The control assembly is configured to control operation of the plurality of engine cores such that in a first operational mode the first and the second engine cores are active to generate combustion products and in a second operational mode the first engine core is active to generate combustion products while the second engine core is idle.

Подробнее

Номер записи: 19

01-11-2012 дата публикации

Moisture monitoring system for gas turbine engines

Номер: US20120277968A1

Автор: Edris Raji, James F. Hyland, Jr.

Принадлежит: United Technologies Corp

A moisture monitoring system includes a control in communication with a sensor system to determine moisture data from a moisture level in a composite material structure.

Подробнее

Номер записи: 20

13-12-2012 дата публикации

Gas turbine systems involving rotor bayonet coverplates and tools for installing such coverplates

Номер: US20120311835A1

Автор: Daniel J. Griffin, Joseph T. Caprario

Принадлежит: United Technologies Corp

Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk.

Подробнее

Номер записи: 21

03-01-2013 дата публикации

Fuel deoxygenation using surface-modified porous membranes

Номер: US20130000180A1

Автор: Haralambos Cordatos, Louis J. Spadaccini, Thomas G. Tillman

Принадлежит: United Technologies Corp

A fuel deoxygenation system includes an oxygen permeable membrane having a porous membrane and an oleophobic layer. The porous membrane has pores that create a passage extending from a first side to an opposite second side of the porous membrane. The pores have an average pore diameter less than or equal to about 0.06 microns. The oleophobic layer and the porous membrane allow oxygen to cross the oxygen permeable membrane but substantially prevent fuel from crossing the oxygen permeable membrane. A method for removing dissolved oxygen from a fuel includes delivering fuel to an oxygen permeable membrane and removing oxygen from the fuel using the oxygen permeable membrane. A method for modifying a surface of a porous membrane includes depositing an oleophobic treatment agent on the porous membrane, removing solvent and heating the porous membrane to form an oleophobic layer on the porous membrane.

Подробнее

Номер записи: 22

03-01-2013 дата публикации

Flowpath insert and assembly

Номер: US20130000769A1

Автор: Darren M. Smith

Принадлежит: United Technologies Corp

A flowpath assembly for a gas turbine engine includes a plurality of flowpath insert ducts arranged in a cascade configuration. Each flowpath duct includes a radially inward wall, a radially outward wall, a first side wall, and a second side wall. A flowpath volume is defined between the inward, outward, first side and second side walls. The first side wall of a given one of the plurality of flowpath insert ducts is positioned adjacent to the second sidewall of an adjacent one of the plurality of flowpath insert ducts in the cascade configuration.

Подробнее

Номер записи: 23

03-01-2013 дата публикации

Rivet and rivet removal method thereof

Номер: US20130004263A1

Автор: Leonard Paul Palmisano

Принадлежит: United Technologies Corp

A shaft, a factory head, and a conical recess form a rivet. The shaft is cylindrical and includes a diameter, a first end, and a second end, the second end having a deformable portion to form a shop head. The factory head is connected to the first end of the shaft and has a diameter greater than the diameter of the shaft. The conical recess is preformed in the factory head coaxial with the shaft and narrows while extending into the factory head towards the shaft. The conical recess has an angle between 100 degrees and 135 degrees and a depth between 0.0254 centimeters and 0.1016 centimeters.

Подробнее

Номер записи: 24

03-01-2013 дата публикации

Nano-structured fan airfoil sheath

Номер: US20130004324A1

Автор: James O. Hansen, Joseph Parkos

Принадлежит: United Technologies Corp

A method of forming a sheath for a fan airfoil having a leading edge, a trailing edge, a tip, a root, a suction side and a pressure side includes electroplating a nano-structured material to form a sheath with a solid portion to wrap around the leading edge and first and second flanks to secure the solid portion to the pressure side and the suction side of the airfoil.

Подробнее

Номер записи: 25

10-01-2013 дата публикации

Gas turbine shroud arrangement

Номер: US20130008176A1

Автор: Jun Shi, Kevin E. Green, Paul F. Croteau

Принадлежит: United Technologies Corp

A system for supporting a shroud used in an engine has a shroud positioned radially outboard of a rotor, which shroud has a plurality of circumferentially spaced slots; a forward support ring for supporting the shroud; the forward support ring having a plurality of spaced apart first tabs on a first side for functioning as anti-rotation devices; the forward support ring having a plurality of spaced apart second tabs on a second side; and the second tabs engaging the slots in the shroud and circumferentially supporting the shroud.

Подробнее

Номер записи: 26

10-01-2013 дата публикации

Reduction in thermal stresses in monolithic ceramic or ceramic matrix composite shroud

Номер: US20130011248A1

Автор: Jun Shi, Kevin E. Green, Paul F. Croteau

Принадлежит: United Technologies Corp

A shroud for use in a gas turbine engine has a ring with a plurality of protrusions and a plurality of slots and each of the protrusions having an arc length and parallel sides.

Подробнее

Номер записи: 27

17-01-2013 дата публикации

Ceramic Matrix Composite Combustor Vane Ring Assembly

Номер: US20130014512A1

Автор: David C. Jarmon, Peter G. Smith

Принадлежит: United Technologies Corp

A vane assembly has an outer support ring, an inner support ring, an outer liner ring, an inner liner ring, and a circumferential array of vanes. Each vane has a shell extending from an inboard end to an outboard end and at least partially through an associated aperture in the inner liner ring and an associated aperture in the outer liner ring. There is at least one of: an outer compliant member compliantly radially positioning the vane; and an inner compliant member compliantly radially positioning the vane.

Подробнее

Номер записи: 28

28-02-2013 дата публикации

Ejector-driven fuel stabilization system

Номер: US20130047845A1

Автор: PARTHASARATHY SAMPATH

Принадлежит: United Technologies Corp

A fuel stabilization unit includes a fuel inlet and outlet, an oxygen permeable membrane and a vacuum source. The vacuum source employs an ejector and a high pressure fluid to generate an oxygen partial pressure differential across the membrane. A fuel deoxygenation system includes a fuel stabilization unit and a vacuum source. The fuel stabilization unit has a fuel flow path, a vacuum chamber and an oxygen permeable membrane separating the fuel flow path and the vacuum chamber. The vacuum source employs an ejector and a high pressure fluid to reduce pressure in the vacuum chamber to generate an oxygen partial pressure differential across the oxygen permeable membrane. A method for deoxygenating a fuel includes delivering a high pressure fluid to an ejector, generating an oxygen partial pressure differential across an oxygen permeable membrane using only the ejector and removing oxygen from the fuel using the oxygen partial pressure differential.

Подробнее

Номер записи: 29

28-03-2013 дата публикации

Systems and methods involving improved fuel atomization in air blast fuel nozzles of gas turbine engines

Номер: US20130074514A1

Автор: Frederick C. Padget, Jeffery A. Lovett, John W. Mordosky, Shawn M. McMahon

Принадлежит: United Technologies Corp

Systems and methods involving improved fuel atomization in air-blast fuel nozzles of gas turbine engines are provided. In this regard, a representative method includes: providing fuel to a chamber defined by an inner surface; and continuously atomizing a portion of the fuel via interaction of the fuel with the inner surface.

Подробнее

Номер записи: 30

28-03-2013 дата публикации

Gas turbine engine mount assembly

Номер: US20130074517A1

Автор: Brian D. Merry, Christopher M. Dye, Gabriel L. Suciu

Принадлежит: United Technologies Corp

A forward mount assembly for connecting a pylon to an intermediate case of a gas turbine engine, the forward mount assembly includes a forward mount platform, a wiffle tree assembly, and first and second A-arms. The platform is connected to the pylon and is disposed adjacent the intermediate case. The wiffle tree assembly is connected to the forward mount platform through a first ball joint. The first A-arm is connected to a first side of the intermediate case and the second A-arm is connected to a second opposing side of the intermediate case. The first and second A-arms are mounted to the forward mount platform and are mounted to opposing ends of the wiffle tree. The aforementioned arrangement allows the first and second A-arms to react a thrust load at the intermediate case substantially parallel to a centerline axis of the gas turbine engine.

Подробнее

Номер записи: 31

28-03-2013 дата публикации

Seal plate with cooling passage

Номер: US20130078079A1

Автор: Eric Charles Mundell, Todd M. Lapierre

Принадлежит: United Technologies Corp

A seal assembly for a gas turbine engine includes a carbon seal and a seal plate. The seal plate has a contact face configured to slidably engage the carbon seal. The seal plate has a surface disposed on an opposing side of the seal plate from the contact face. The surface forms a portion of a single passage that extends an entire length of the seal plate. The continuous cooling provided by single passage along the seal plate allows for a more uniform temperature profile along the contact face of seal plate.

Подробнее

Номер записи: 32

28-03-2013 дата публикации

High temperature refractory coatings for ceramic substrates

Номер: US20130079214A1

Автор: David C. Jarmon, Owen B. Donahue, JR., Tania Bhatia Kashyap, Wayde R. Schmidt, Xia Tang

Принадлежит: United Technologies Corp

A method of manufacturing a composite article includes pyrolyzing a preceramic polymer to form a non-oxide ceramic matrix and a byproduct, and reacting the refractory material with the byproduct to form a refractory phase within the non-oxide ceramic matrix.

Подробнее

Номер записи: 33

25-04-2013 дата публикации

Split accessory drive system

Номер: US20130098058A1

Автор: William G. Sheridan

Принадлежит: United Technologies Corp

A gas turbine engine includes a spool, a first accessory gearbox, a second accessory gearbox, and a scavenge pump. The first accessory gearbox is connected to and driven by the spool. The second accessory gearbox is connected to and driven by the first accessory gearbox. The scavenge pump is connected between the first accessory gearbox and the second accessory gearbox. The first accessory gearbox drives the second accessory gearbox through the scavenge pump.

Подробнее

Номер записи: 34

02-05-2013 дата публикации

Non axis-symmetric stator vane endwall contour

Номер: US20130108433A1

Автор: Brian Green, Sean Nolan

Принадлежит: United Technologies Corp

An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, defining a mean span therebetween. An inner endwall defines an inner endwall contour extending axially and circumferentially from the root section, and an outer endwall defines an outer endwall contour extending axially and circumferentially from the tip section. The inner and outer endwall contours are defined by varying radial deviations from circumferentially uniform nominal inner and outer radii, where one of the radial deviations varies axially and circumferentially by at least three percent of a mean span of the airfoil.

Подробнее

Номер записи: 35

16-05-2013 дата публикации

Flexible seal system for a gas turbine engine

Номер: US20130121813A1

Автор: Jocelyn C. Damgaard, Steven D. Roberts, Timothy Dale

Принадлежит: United Technologies Corp

A flexible seal system for a gas turbine engine includes an annular mounting bracket, an annular support bracket, an annular flexible seal and a plurality of mounting spacers. The flexible seal extends axially between a first mounting segment and a second mounting segment. The first mounting segment is connected axially between the mounting bracket and the support bracket, and includes a plurality of mounting apertures that extend axially through the first mounting segment. Each of the mounting spacers is arranged within a respective one of the mounting apertures, and extends axially between the mounting bracket and the support bracket.

Подробнее

Номер записи: 36

06-06-2013 дата публикации

Alternate shroud width to provide mistuning on compressor stator clusters

Номер: US20130142640A1

Автор: David P. Houston, Richard A. Lomenzo, Robert J. Morris

Принадлежит: United Technologies Corp

A stator for a turbo-machine having a plurality of airfoils extending radially therefrom has a base from which the airfoils depend, and slits disposed in the base, each slit disposed adjacent a pair of airfoils, wherein a first set of adjacent slits and a distance between a second set of adjacent slits varies

Подробнее

Номер записи: 37

06-06-2013 дата публикации

Structural joint for connecting a first component to a segmented second component

Номер: US20130142643A1

Автор: Eric W. Malmborg

Принадлежит: United Technologies Corp

A structural joint includes a first flange, a second flange and a fastener with a head and a shaft. The first flange extends out from a first component to a distal first flange end. The second flange extends out from a segmented second component to a distal second flange end. The second flange includes a first lateral flange segment that extends laterally to a first flange sidewall, and a second lateral flange segment that extends laterally to a second flange sidewall, which is engaged with the first flange sidewall. The head is encased in the second flange and extends laterally into the first flange sidewall and the second flange sidewall. The shaft extends longitudinally out from the second flange and through the first flange.

Подробнее

Номер записи: 38

13-06-2013 дата публикации

Ferrule

Номер: US20130147182A1

Автор: Billie W. Bunting, David W. Anderson, Fungayi Mutsengi, Richard M. Murphy, Robert J. Derosa

Принадлежит: United Technologies Corp

A ferrule for use with a nut with an internal locking mechanism includes a first tubular portion with a first end and a first outer diameter for connecting to a first object; a second tubular portion with a second end and a second outer diameter for connecting to a second object; a transition portion connecting the first tubular portion and the second tubular portion; and a plurality of pockets spaced circumferentially around the second portion to engage the internal locking mechanism of the nut.

Подробнее

Номер записи: 39

20-06-2013 дата публикации

Energy absorbent fan blade spacer

Номер: US20130156591A1

Автор: Phillip Alexander

Принадлежит: United Technologies Corp

A gas turbine engine fan assembly includes a rotor disk, a fan blade and a spacer. The rotor disk includes a longitudinally extending slot with a first spacer contact surface. The fan blade includes a root with a second spacer contact surface arranged within the slot. The spacer includes a leaf spring backbone and a compliant member. The leaf spring backbone includes one or more root contact segments connected longitudinally to one or more slot contact segments. A first of the root contact segments contacts the second spacer contact surface, and a first of the slot contact segments contacts the first spacer contact surface. The compliant member is radially between the first spacer contact surface and the first root contact segment, and radially between the second spacer contact surface and the first slot contact segment.

Подробнее

Номер записи: 40

27-06-2013 дата публикации

Airflow Testing Method and System for Multiple Cavity Blades and Vanes

Номер: US20130160535A1

Автор: Edward Pietraszkiewicz, Richard Varsell, Sergey Mironets, Thomas R. DAVIS

Принадлежит: United Technologies Corp

A system for airflow testing a turbine engine component having multiple cavities has a test fixture with a module for supporting a turbine engine component to be tested and a sliding element for sequentially allowing a pressurized fluid to flow through each of the multiple cavities in the turbine engine component. A method for performing the airflow testing is also described.

Подробнее

Номер записи: 41

11-07-2013 дата публикации

High gliding fluid power generation system with fluid component separation and multiple condensers

Номер: US20130174551A1

Автор: Ahmad M. Mahmoud, Jaeseon Lee, Thomas D. Radcliff

Принадлежит: United Technologies Corp

An example power generation system includes a vapor generator, a turbine, a separator and a pump. In the separator, the multiple components of the working fluid are separated from each other and sent to separate condensers. Each of the separate condensers is configured for condensing a single component of the working fluid. Once each of the components condense back into a liquid form they are recombined and exhausted to a pump that in turn drives the working fluid back to the vapor generator.

Подробнее

Номер записи: 42

11-07-2013 дата публикации

Coupling system for a star gear train in a gas turbine engine

Номер: US20130178327A1

Автор: Alessio Pescosolido, Michael E. McCune, William G. Sheridan

Принадлежит: United Technologies Corp

A star gear train for use in a gas turbine engine includes a sun gear, a ring gear, a plurality of star gears and a coupling system. The sun gear is rotatable by a shaft. The ring gear is secured to a ring gear shaft. Each of the plurality of star gears is rotatably mounted in a star carrier and meshes with the sun gear and the ring gear. The coupling system comprises a sun gear flexible coupling, a carrier flexible coupling and a deflection limiter. The sun gear flexible coupling connects the sun gear to the shaft. The carrier flexible coupling connects the carrier to a non-rotating mechanical ground. The deflection limiter is connected to the star carrier to limit excessive radial and circumferential displacement of the star gear train.

Подробнее

Номер записи: 43

18-07-2013 дата публикации

Method for reducing coke deposition

Номер: US20130184510A1

Автор: HE Huang, Martin Haas

Принадлежит: United Technologies Corp

A method for reducing coke deposits includes heating an alcohol-fuel mixture to decompose alcohol and form water to produce a fuel-water mixture and delivering the fuel-water mixture to a carbon-steam gasification catalyst. The fuel-water mixture reacts with the carbon-steam gasification catalyst such that coke deposits are prevented from remaining in a space near the carbon-steam gasification catalyst.

Подробнее

Номер записи: 44

25-07-2013 дата публикации

Gas Turbine Combustor

Номер: US20130186099A1

Автор: James B. Hoke

Принадлежит: United Technologies Corp

A combustor for a gas turbine engine having an annular combustion chamber includes a plurality of main fuel injection and air swirler assemblies and a plurality of pilot fuel injection and air swirler assemblies disposed in a circumferential ring extending about the circumferential expanse of a forward bulkhead. The plurality of pilot fuel injection and air swirler assemblies are interspersed amongst and disposed in the circumferential ring of main fuel injection and air swirler assemblies. Fuel being supplied to the combustor is selectively distributed between the plurality of main fuel injection and air swirler assemblies and the plurality of pilot fuel injection and air swirler assemblies in response to the level of power demand on the gas turbine engine.

Подробнее

Номер записи: 45

01-08-2013 дата публикации

Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine

Номер: US20130192251A1

Автор: Peter M. Munsell, Philip S. Stripinis

Принадлежит: United Technologies Corp

A gas turbine engine includes a buffer system that can communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine.

Подробнее

Номер записи: 46

01-08-2013 дата публикации

Geared turbofan engine with counter-rotating shafts

Номер: US20130195624A1

Автор: Daniel Bernard Kupratis, Frederick M. Schwarz, Gabriel L. Suclu

Принадлежит: United Technologies Corp

A mid-turbine frame is incorporated into a turbine section of a gas turbine engine intermediate a high pressure turbine and a low pressure turbine. The high pressure and low pressure turbines rotate in opposite directions. A plurality of vanes redirect the flow downstream of the high pressure turbine as it approaches the low pressure turbine.

Подробнее

Номер записи: 47

08-08-2013 дата публикации

Turbine engine shaft coupling

Номер: US20130202349A1

Автор: James B. Coffin

Принадлежит: United Technologies Corp

A turbine engine shaft includes a first sub-shaft, a second sub-shaft and a tie shaft. A first bearing surface of the first sub-shaft axially engages a second bearing surface of the second sub-shaft. The tie shaft includes an intermediate tie shaft segment connected axially between a first tie shaft segment and a second tie shaft segment. The first tie shaft segment includes a first threaded tie shaft surface that is mated with a first threaded shaft surface of the first sub-shaft. The second tie shaft segment includes a second threaded tie shaft surface that is mated with a second threaded shaft surface of the second sub-shaft. The tie shaft also includes a sub-shaft bumper stop extending radially from the intermediate tie shaft segment to a bumper stop distal end, which has a radius that is greater than a radius the first and/or second threaded shaft surfaces.

Подробнее

Номер записи: 48

08-08-2013 дата публикации

Gas turbine engine thermal management system

Номер: US20130202406A1

Автор: Ethan K. Stearns, Federico Papa, Justin W. Heiss, Kathleen R. Phillips, Thomas G. Phillips

Принадлежит: United Technologies Corp

A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid. A positioning of the valve is based on at least one of the first characteristic and the second characteristic.

Подробнее

Номер записи: 49

15-08-2013 дата публикации

Method of manufacturing an airfoil

Номер: US20130209262A1

Автор: Clifford C. Bampton, Daniel Edward Matejczyk, John R. Wooten

Принадлежит: Aerojet Rocketdyne of DE Inc, CalRAM Inc, United Technologies Corp

Disclosed is a method of manufacturing an airfoil. The method includes establishing an Argon (Ar)-free environment, providing a bed within the Argon free environment, providing a set of data instructions for manufacturing the airfoil, and providing a powdered Nickel (Ni)-based alloy on the bed. In one example, the powdered Nickel (Ni)-based alloy consists essentially of about 4.8 wt. % Iron (Fe), about 21 wt. % Chromium (Cr), about 8.6 wt. % Molybdenum (Mo), about 0.07 wt. % Titanium (Ti), about 0.40% Aluminum (Al), about 5.01 wt. % Niobium (Nb), about 0.03 wt. % Carbon (C), about 0.14 wt. % Silicon (Si), and a balance Nickel (Ni). The method further includes fusing the powdered Nickel (Ni)-based alloy with an electron beam with reference to the data instructions to form the airfoil.

Подробнее

Номер записи: 50

22-08-2013 дата публикации

Accurate machine tool inspection of turbine airfoil

Номер: US20130215260A1

Автор: Erik M. PEDERSEN, Joseph D. Drescher

Принадлежит: United Technologies Corp

Inspecting features of an object including measuring features of the master part that represents a desired nominal dimensions to obtain a preliminary set of dimensional data. The preliminary set of data becomes a master data set. The same master part is measured on a second machine to obtain another set of data on the master part. The two data sets are compared and correction data is generated representing differences between the different data sets for the same master part measured on different machines. Subsequent parts are then measured on the second machine to obtain measurement data that is corrected based on the correction data. The application of the correction information provides for the use of 5-axis machines within a desired measurement capability.

Подробнее

Номер записи: 51

29-08-2013 дата публикации

Geared turbofan architecture for improved thrust density

Номер: US20130219907A1

Автор: Daniel Bernard Kupratis, Frederick M. Schwarz, Gabriel L. Suciu

Принадлежит: United Technologies Corp

A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction.

Подробнее

Номер записи: 52

12-09-2013 дата публикации

Turbine engine case mount and dismount

Номер: US20130232768A1

Автор: Brian D. Merry, Gabriel L. Suciu, Ioannis Alvanos

Принадлежит: United Technologies Corp

A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.

Подробнее

Номер записи: 53

12-09-2013 дата публикации

Pressure balanced area control of high aspect ratio nozzle

Номер: US20130232949A1

Автор: Gary J. Dillard

Принадлежит: United Technologies Corp

An apparatus for minimizing signature of an engine having an exhaust gas path and a fan gas path includes a casing, and a liner disposed within the casing. The exhaust gas path passes within the liner and the fan gas path passes between the liner and the casing. The casing is disconnected into an upstream portion and a downstream portion, each portion in registration with the liner, such that there are minimum pressure imbalances caused by the exhaust gas path, the fan gas path and ambient on the downstream portion.

Подробнее

Номер записи: 54

12-09-2013 дата публикации

Airfoil with improved internal cooling channel pedestals

Номер: US20130232991A1

Автор: Edwin Otero

Принадлежит: United Technologies Corp

An airfoil for a turbine engine, the airfoil including a first side wall, a second side wall spaced apart from the first side wall, and an internal cooling channel formed between the first side wall and the second side wall. The internal cooling channel includes at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to the second side wall. The internal cooling channel also includes a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal end; and a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal end. At least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery of the corresponding pedestal end.

Подробнее

Номер записи: 55

19-09-2013 дата публикации

Pump system for tms aoc reduction

Номер: US20130239588A1

Автор: Brian D. Merry, Christopher M. Dye, Gabriel L. Suciu, Jorn A. Glahn

Принадлежит: United Technologies Corp

An engine includes a duct containing a flow of cool air and a pump system having an impeller with an inlet for receiving air from the duct and an outlet for discharging air into a discharge manifold. The discharge manifold containing at least one heat exchanger which forms part of a thermal management system.

Подробнее

Номер записи: 56

03-10-2013 дата публикации

Geared turbofan engine with power density range

Номер: US20130255275A1

Автор: Daniel Bernard Kupratis, Frederick M. Schwarz

Принадлежит: United Technologies Corp

A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.

Подробнее

Номер записи: 57

10-10-2013 дата публикации

Engine hot section vane with tapered flame holder surface

Номер: US20130263572A1

Автор: Christopher A. Eckett, Donald J. Hautman, Jeffery A. Lovett, Meredith B. Colket, III, Torence P. Brogan

Принадлежит: United Technologies Corp

A gas turbine or rocket engine hot section includes a first duct case, a second duct case, a plurality of vanes arranged about an axial centerline, and an igniter located with a first of the plurality of vanes. The first of the plurality of vanes extends axially between a leading edge and a flame holder surface at a trailing edge. The flame holder surface extends radially between a first vane end connected to the first duct case and a second vane end connected to the second duct case. The flame holder surface includes a first section that tapers towards the first vane end, and a second section that tapers away from the first section and towards the second vane end.

Подробнее

Номер записи: 58

24-10-2013 дата публикации

Compact fuel cell system

Номер: US20130280640A1

Автор: Jonathan Daniel O'NEILL

Принадлежит: United Technologies Corp

An example fuel cell system includes a fuel cell power plant and a tank providing a volume that is configured to hold a fuel cell fluid. The fuel cell power plant is at least partially disposed within the volume.

Подробнее

Номер записи: 59

31-10-2013 дата публикации

Gas turbine engine thermal management system

Номер: US20130284398A1

Автор: Federico Papa, Kathleen R. Phillips, Thomas G. Phillips

Принадлежит: United Technologies Corp

A thermal management system according to an exemplary aspect of the present disclosure includes, among other things, a first fluid circuit that selectively communicates a first portion of a first conditioned fluid having a first temperature to a first gas turbine engine system and a second portion of the first conditioned fluid having a second temperature to a second gas turbine engine system. The second temperature is a greater temperature than the first temperature. A second fluid circuit circulates a second conditioned fluid that is different from the first conditioned fluid to a third gas turbine engine system.

Подробнее

Номер записи: 60

31-10-2013 дата публикации

Geared Architecture for High Speed and Small Volume Fan Drive Turbine

Номер: US20130287575A1

Автор: Daniel Bernard Kupratis, Frederick M. Schwarz, Gabriel L. Suciu, Jason Husband, Michael E. McCune, William K. Ackermann

Принадлежит: United Technologies Corp

A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.

Подробнее

Номер записи: 61

31-10-2013 дата публикации

Integrated maintenance management system

Номер: US20130288210A1

Автор: Andrew James Stewart, Don Reynolds, Eric G. Anderson, Ghazi A. Saleem, II Donald L. Reeves, James H. Stewart, Lawrence P. Crochet, Robert Stanley Koresky, Stephen Foster, William E. Puetz

Принадлежит: United Technologies Corp

A semi-automated maintenance management system instructs a technician to disassemble a component into parts, compare each part to a reference entry and identify any discrepancies between the part and the reference entry, repair or replace the component according to instructions automatically provided for the discrepancy when a known discrepancy is found, create a disposition when an unknown discrepancy is found, and reassemble the component.

Подробнее

Номер записи: 62

07-11-2013 дата публикации

Shaped rim cavity wing surface

Номер: US20130294897A1

Автор: Eric A. Grover

Принадлежит: United Technologies Corp

A shaped rim cavity wing includes an upper surface and a lower surface. The lower surface has a geometric shape to control the separation of airflow as it passes around the lower surface to the top surface. A point of maximum extent defines the boundary between the upper surface and the lower surface, wherein the point of maximum extent defines a corner that that separates airflow from the shaped rim cavity rim and creates a flow re-circulation adjacent to the top surface of the shaped rim cavity wing.

Подробнее

Номер записи: 63

14-11-2013 дата публикации

Gas turbine engine systems and related methods involving multiple gas turbine cores

Номер: US20130298565A1

Автор: Gary D. Roberge

Принадлежит: United Technologies Corp

Gas turbine engine systems and related methods involving multiple gas turbine cores are provided. In this regard, a representative gas turbine engine includes: an inlet; a blade assembly mounted to receive intake air via the inlet; and multiple gas turbine cores located downstream of the blade assembly, each of the multiple gas turbine cores being independently operative in a first state, in which rotational energy is provided to rotate the blade assembly, and a second state, in which rotational energy is not provided to rotate the blade assembly.

Подробнее

Номер записи: 64

28-11-2013 дата публикации

Airfoil mateface sealing

Номер: US20130315745A1

Автор: Andrew S. Aggarwala

Принадлежит: United Technologies Corp

An airfoil includes an airfoil working portion and an adjoining endwall. The endwall has a leading edge, a trailing edge, a first mateface, and a second mateface that collectively define a perimeter of the endwall, with the first and second matefaces arranged opposite one another. A forward zone is defined by the endwall that extends to the leading edge. The first and second matefaces are each oriented at an angle α II relative to radial in the forward zone. An aft zone is defined by the endwall that extends to the trailing edge. The first and second matefaces are each oriented at an angle α II relative to radial in the aft zone. The angles α II and α II are not equal. A middle zone is defined in between the forward and aft zones, and the first and second matefaces transition between the angles α II and α I in the middle zone.

Подробнее

Номер записи: 65

05-12-2013 дата публикации

Airfoil and disk interface system for gas turbine engines

Номер: US20130323064A1

Автор: Kimberly Pash Boyington

Принадлежит: United Technologies Corp

A gas turbine engine system includes a disk and an airfoil. The disk includes a first rail, a second rail, a retention slot located between the first and second rails, and a ridge extending radially outward from the second rail. The airfoil is engaged with the retention slot, and includes a platform with an upstream angled portion, a downstream angled portion, and a notch defined in the platform. The ridge of the disk extends at least partially into the notch of the platform.

Подробнее

Номер записи: 66

05-12-2013 дата публикации

Aerial vehicle with mission duration capability determination

Номер: US20130325212A1

Автор: David L. Wickman

Принадлежит: United Technologies Corp

An aerial vehicle can include oil sensors connected to a lubrication system and a computer connected to the oil sensors. The computer can be programmed to determine mission duration for the unmanned aerial vehicle, determine a maximum oil system duration for the unmanned aerial vehicle based upon data from the oil sensors, perform a comparison of the mission duration to the maximum oil system duration, and output a signal based upon the comparison.

Подробнее

Номер записи: 67

19-12-2013 дата публикации

Turbine compressor blade tip resistant to metal transfer

Номер: US20130333392A1

Автор: Christopher W. STROCK, Matthew E. Bintz

Принадлежит: United Technologies Corp

A gas turbine engine having an engine casing extending circumferentially about an engine centerline axis; and a compressor section, a combustor section, and a turbine section within said engine casing. At least one of said compressor section and said turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil, wherein a tip of the at least one airfoil is metal having a thin film ceramic coating and the at least one seal member is coated with an abrasive.

Подробнее

Номер записи: 68

19-12-2013 дата публикации

Metallic rails on composite fan case

Номер: US20130336773A1

Автор: Darin S. Lussier, Mark W. Costa, Thomas J. Robertson

Принадлежит: United Technologies Corp

A composite fan case has a generally cylindrical composite shell, at least one band of sacrificial composite material circumscribing an outer surface of the composite shell, and a metallic rail mounted on the band of sacrificial material. Also disclosed is a method of construction the aforementioned case.

Подробнее

Номер записи: 69

26-12-2013 дата публикации

Turbine engine variable area vane

Номер: US20130343873A1

Автор: Brandon W. Spangler, Tracy A. Propheter-Hinckley

Принадлежит: United Technologies Corp

A turbine engine stator vane is provided that rotates about an axis, and includes an airfoil, a flange and a shaft. The airfoil extends axially between a first airfoil end and a second airfoil end. The airfoil includes a concave side surface, a convex side surface and a cavity. The concave and the convex side surfaces extend between an airfoil leading edge and an airfoil trailing edge. The cavity extends axially into the airfoil from a cavity inlet in an end surface at the second airfoil end. The flange is connected to the second airfoil end. The flange extends circumferentially around at least a portion of the cavity inlet, and radially away from the concave and the convex side surfaces to a distal flange edge. The shaft extends along the axis, and is connected to the second airfoil end.

Подробнее

Номер записи: 70

26-12-2013 дата публикации

Spherical-link end damper system with near constant engagement

Номер: US20130343876A1

Автор: Kevin J. Cummings, Ryan Edward LeBlanc

Принадлежит: United Technologies Corp

A link includes a link body with two ends, a ring bore with a ring bore axis and a bearing, a mount bore with a mount bore axis and a bearing. The link also has an end curvature at the end having the ring bore wherein the curvature axis is substantially perpendicular to the ring bore axis.

Подробнее

Номер записи: 71

09-01-2014 дата публикации

Gas turbine engine fan blade tip treatment

Номер: US20140010663A1

Автор: James O. Hansen, Joseph Parkos, JR.

Принадлежит: United Technologies Corp

A method of manufacturing a fan blade includes providing a metallic fan blade body, and applying at least a 200 volt potential to the fan blade body in a solution to produce a crystalline oxidation layer. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a crystalline oxidation layer. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a titanium dioxide layer.

Подробнее

Номер записи: 72

09-01-2014 дата публикации

Fuel cell seal

Номер: US20140011114A1

Автор: Jason B. PARSONS

Принадлежит: United Technologies Corp

An example fuel cell seal assembly includes a seal configured to restrict flow of a fuel cell fluid through at least one of an outer lateral edge of a first gas diffusion layer, an outer lateral edge of a membrane electrode assembly, and an outer lateral edge of a second gas diffusion layer. The outer lateral edge of the first gas diffusion layer is laterally spaced from the outer lateral edge of the second gas diffusion layer. An example method of sealing a fuel cell interface includes limiting flow of a fuel cell fluid using a seal configured to restrict flow through an outwardly facing edge of at least one of a first gas diffusion layer and an outwardly facing edge of a second gas diffusion layer. The outwardly facing edge of the first gas diffusion layer is spaced from the outwardly facing edge of the second gas diffusion layer.

Подробнее

Номер записи: 73

13-02-2014 дата публикации

Blade outer air seal having anti-rotation feature

Номер: US20140044528A1

Автор: Brian Ellis Clouse

Принадлежит: United Technologies Corp

A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. At least one of the leading edge portion and the trailing edge portion includes a solid wall and a perforated wall. At least a portion of the perforated wall is spaced from the solid wall such that a passage extends between the solid wall and the perforated wall.

Подробнее

Номер записи: 74

20-02-2014 дата публикации

Fuel cell component including a vapor permeable layer

Номер: US20140051011A1

Автор: Siddique Ali Khateeb Razack

Принадлежит: United Technologies Corp

An exemplary fuel cell component comprises a porous plate. A vapor permeable layer is provided on at least one portion of the porous plate. The vapor permeable layer is configured to permit vapor to pass through the layer while resisting liquid passage through the layer.

Подробнее

Номер записи: 75

27-02-2014 дата публикации

Spring carrier and removable seal carrier

Номер: US20140054862A1

Автор: David Joseph HIERL, Todd A. Davis

Принадлежит: United Technologies Corp

A seal assembly includes a seal support, a spring carrier, a plurality of springs, and a seal carrier. The spring carrier is connected to the seal support by a guide assembly. The plurality of springs are disposed between the seal support and the spring carrier. The seal carrier is connected to the spring carrier and is removable therefrom.

Подробнее

Номер записи: 76

06-03-2014 дата публикации

Fuel delivery system with a cavity coupled fuel injector

Номер: US20140060059A1

Автор: Christopher A. Eckett, Jeffery A. Lovett, May L. Corn, Torence P. Brogan

Принадлежит: United Technologies Corp

A fuel injection system for a gas turbine engine includes a fuel delivery conduit, a nozzle block with a nozzle aperture, and a cavity block with a cavity. The nozzle aperture has a first cross sectional area, and injects fuel received from the fuel delivery conduit into the cavity. The cavity has a second cross sectional area that is greater than the first cross sectional area.

Подробнее

Номер записи: 77

20-03-2014 дата публикации

System method for machining aircraft components

Номер: US20140075754A1

Автор: Alan C. Barron, Aleah J. Edwards, Allan J. Brockett, Bartolomeo Palmieri, Charles A. Blizzard, Gregory A. Gilbert, James Masloski, Jeffrey P. Smith, Mark F. Zelesky

Принадлежит: United Technologies Corp

A method for manufacturing an aircraft component according to one embodiment of this disclosure includes providing a machining system including a controller, at least one sensor, and a tool for machining. The method further includes providing an aircraft component, and machining the aircraft component with the tool based on feedback from the at least one sensor.

Подробнее

Номер записи: 78

20-03-2014 дата публикации

Torque Adapter With Ratchet Reverse Feature

Номер: US20140076111A1

Автор: Bruce H. Layton

Принадлежит: United Technologies Corp

A torque transmittal tool has an input socket to receive a drive input from a drive tool. The input socket causes a first link to rotate through a range of rotation upon rotation of the input socket. The first link is fixed to rotate with an extension link. The extension link is fixed to rotate with an output link. The output link includes an output ratchet for transmitting rotation, and has a torque reversal button which may be actuated to change the direction of rotation of the output ratchet. An actuator has an unactuated position where a contact surface is spaced away from the torque reversal button, and an actuated position at which it actuates the torque reversal button. A method is also disclosed

Подробнее

Номер записи: 79

20-03-2014 дата публикации

Lubrication system having porous feature

Номер: US20140076661A1

Автор: Jinquan Xu

Принадлежит: United Technologies Corp

A lubricant tank includes a lubricant tank discharge passageway at least partially within the lubricant tank body, a porous media mounted within the lubricant tank body.

Подробнее

Номер записи: 80

20-03-2014 дата публикации

Casting of thin wall hollow airfoil sections

Номер: US20140079542A1

Автор: Carl R. Verner, James B. Park, Steven D. PORTER, Steven J. Bullied

Принадлежит: United Technologies Corp

A casting mold assembly comprises an airfoil defining section and a casting core. The airfoil defining section includes an outer mold wall and a direct-shelled inner mold wall. The direct-shelled inner mold wall is disposed within a forward chordwise portion of the airfoil defining section. The direct-shelled inner mold wall includes an aft end having an external radius measuring more than about 0.075 in. (1.9 mm). The casting core is secured within an aft chordwise portion of the airfoil defining section, and includes an aft end with an external radius measuring less than about 0.075 in. (1.9 mm). A cast component and a method for making the casting mold assembly are also disclosed.

Подробнее

Номер записи: 81

27-03-2014 дата публикации

Method and fixture for airfoil array assembly

Номер: US20140082940A1

Автор: Dennis R. Tremblay, Michael E. Mcmahon, Nathan Johnson, Steven J. Feigleson

Принадлежит: United Technologies Corp

An example method of assembling a turbomachine airfoil array includes, among other things, securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner and an outer fairing and an open area where at least one existing airfoil has been removed. The method includes mounting a positioning saddle relative to a base of the fixture, the positioning saddle aligned with the open area, holding a replacement airfoil using the positioning saddle, applying a curable material at an interface between the replacement airfoil and the inner and outer fairing, and curing the curable material while maintaining a relative position between the replacement airfoil and the inner and outer fairing.

Подробнее

Номер записи: 82

27-03-2014 дата публикации

Wicking layer for managing moisture distribution in a fuel cell

Номер: US20140087277A1

Автор: Paravastu Badrinarayanan, Robert Mason Darling

Принадлежит: United Technologies Corp

An exemplary device for managing moisture content within a fuel cell includes a reactant distribution plate having a plurality of members that establish reactant flow channels that are open on at least one side of the plate. A wicking layer is against the one side of the plate. The wicking layer includes a first portion that is uninterrupted and covers over at least some of the channels. A second portion of the wicking layer extends along ends of at least some of the members such that sections of the channels coextensive with the second portion are open toward the one side.

Подробнее

Номер записи: 83

10-04-2014 дата публикации

Bi-Directional Compression Fan Rotor for a Gas Turbine Engine

Номер: US20140096507A1

Автор: Sohail Mohammed

Принадлежит: United Technologies Corp

A fan rotor has a hub, and a plurality of axial flow fan blades extending radially outwardly of the hub. A radial compressor impeller is positioned radially inwardly of the fan blades. The radial compressor impeller has an upstream inlet which extends generally in an axial direction defined by an axis of rotation of the hub. The radial flow compressor impeller has an outlet that extends radially outwardly of the inlet, and into a supply passage for supplying air to a core engine. An engine is also disclosed.

Подробнее

Номер записи: 84

10-04-2014 дата публикации

Geared Turbofan Engine With Increased Bypass Ratio and Compressor Ratio ...

Номер: US20140096509A1

Автор: Karl L. Hasel

Принадлежит: United Technologies Corp

A gas turbine engine is typically comprised of a fan stage, multiple compressor stages, and multiple turbine stages. These stages are made up of alternating rotating blade rows and static vane rows. The total number of blades and vanes is the airfoil count. An overall pressure ratio is greater than 30. A bypass ratio is greater than 8. A stage ratio is the product of the bypass ratio and the overall pressure ratio divided by the number of stages. An airfoil ratio is that product divided by the airfoil count. The stage ratio is greater than or equal to 22 and/or the airfoil ratio is greater than or equal to 0.12.

Подробнее

Номер записи: 85

10-04-2014 дата публикации

Cooling for Combustor Liners with Accelerating Channels

Номер: US20140096528A1

Автор: Alexander W. Williams, Frank J. Cunha, James P. Bangerter, Nicholas Mule, Nurhak Erbas-Sen, Timothy S. Snyder

Принадлежит: United Technologies Corp

A combustor liner which reduces cooling flow to a combustion chamber and augments pressure drop split between impingement holes and effusion holes is disclosed. The combustor liner may further include accelerating channels, trip strips, pedestals, and cone-shaped effusion holes to provide further cooling of the liner. The combustor liner may reduce NOx production and the temperature of the combustion chamber of a gas turbine engine or the like.

Подробнее

Номер записи: 86

02-01-2020 дата публикации

Cooling system for rotating cutting tools

Номер: US20200001381A1

Автор: Changsheng Guo, Zhigang Wang

Принадлежит: United Technologies Corp

A rotary tool includes a shank, cutting portion, coolant inlet, coolant outlet, and channel system. The cutting portion is connected to and extends from the shank. The cutting portion includes a cutting edge. The coolant inlet and the coolant outlet are disposed in the shank. The channel system is contained in the rotary tool and is a closed circulation loop system such that the coolant is contained within the channel system as the coolant is circulated within the rotary tool. The channel system includes a delivery path and a return path. The delivery path is fluidly connected to the coolant inlet and includes a shape corresponding to a shape of the cutting edge. The return path is fluidly connected to the coolant outlet and to the delivery path at a location in the cutting portion of the rotary tool.

Подробнее

Номер записи: 87

02-01-2020 дата публикации

Processes and tooling associated with diffusion bonding the periphery of a cavity-back airfoil

Номер: US20200001411A1

Автор: Daniel A. Bales, Thomas DeMichael

Принадлежит: United Technologies Corp

A fixture assembly includes a first fixture portion, a second fixture portion that interfaces with the first fixture portion, and a sub-fixture movably mounted to the first fixture portion. A multiple of actuators selectively move the sub-fixture toward the second fixture portion. A method of manufacturing a fan blade includes deploying the sub-fixture from the first fixture portion to effectuate a peripheral diffusion bond to join the blade body and the cover of the fan blade.

Подробнее

Номер записи: 88

05-01-2017 дата публикации

Gas turbine engine airfoil with bi-axial skin core

Номер: US20170002662A1

Автор: Benjamin F. Hagan, Matthew A. Devore, Ryan Alan WAITE

Принадлежит: United Technologies Corp

An airfoil for a gas turbine engine includes a body that extends in a radial direction that provides an exterior airfoil surface. The body includes pressure and suction side walls that extend from a leading edge to a trailing edge in a chord-wise direction. A core cooling passage is provided between the pressure and suction side walls and extends in the radial direction. A skin passage is arranged in one of the pressure and suction side walls between the core cooling passage and the exterior airfoil surface. The skin passage includes a first passageway that extends in the radial direction. The first passageway turns to a second passageway that extends in the chord-wise direction to terminate at an exit arranged near the trailing edge.

Подробнее

Номер записи: 89

05-01-2017 дата публикации

Break-in system for gapping and leakage control

Номер: US20170002677A1

Автор: Paul M. Lutjen, Richard K. Hayford

Принадлежит: United Technologies Corp

A blade outer air seal for use in a gas turbine engine having an axis of rotation includes a main body having a mating face configured to face, be positioned radially outward from, and be positioned adjacent to a rotor blade of the gas turbine engine. The blade outer air seal also includes an axial member extending aft from the main body, having a first radial face configured to face a second radial face of an outer diameter platform of a stator of the gas turbine engine, and having a first abradable material coupled to the first radial face.

Подробнее

Номер записи: 90

05-01-2017 дата публикации

Advanced distributed engine architechture - design alternative

Номер: US20170002735A1

Автор: Frederick M. Schwarz, Gabriel L. Suciu, James D. Hill, Jeffery F. PERLAK, Joseph B. Staubach

Принадлежит: United Technologies Corp

A gas turbine engine according to the present disclosure includes a first compressor and a first turbine for driving the first compressor. A core section includes a second compressor and a second turbine for driving the second compressor. A third turbine is arranged fluidly downstream of the first turbine and the second turbine and configured to drive a power take-off. A first duct system is arranged fluidly between the low-pressure compressor and the core section. The first duct system is arranged to reverse fluid flow before entry into the core section.

Подробнее

Номер записи: 91

05-01-2017 дата публикации

Seals for gas turbine engine nacelle cowlings

Номер: US20170002746A1

Автор: Gregory E. Reinhardt, Nigel D. Sawyers-Abbott

Принадлежит: United Technologies Corp

A gas turbine engine includes an engine core and core nacelle cowling coupled to the engine core. The engine core has a core member that extends radially outward from the engine core. The core nacelle cowling has a cowling member that extends radially inward towards the engine core. The cowling member is offset axially from the core member to form a labyrinth seal that bounds a coolant inlet, thereby fluidly coupling the fan duct flow of the gas turbine engine with a core compartment defined between the engine core and core nacelle cowling.

Подробнее

Номер записи: 92

07-01-2016 дата публикации

Fan Blades with Protective Sheaths and Galvanic Shields

Номер: US20160003062A1

Автор: James R. Murdock

Принадлежит: United Technologies Corp

Light weight fan blades for turbofan jet engines are disclosed. The fan blades may be fabricated from an aluminum alloy. To enhance the hardness of the leading edge of the fan blade, a titanium sheath may be attached to the leading edges of the fan blades. To prevent galvanic coupling between the titanium and the aluminum, a polymeric liner may be disposed between the protective titanium sheath and the aluminum fan blade. The liner may be fabricated from a polymer material, such as a polyimide or another high performance polymer.

Подробнее

Номер записи: 93

07-01-2016 дата публикации

Gas turbine engine component having variable width feather seal slot

Номер: US20160003079A1

Автор: Allison Mainelli, Jeffrey J. Degray, Kevin RAJCHEL, Mark A. Boeke, Richard M. Salzillo

Принадлежит: United Technologies Corp

A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a mate face and a feather seal slot axially extending along the mate face, the feather seal slot having a variable width along a portion of its axial length.

Подробнее

Номер записи: 94

07-01-2016 дата публикации

Rolling element bearing configured with a gutter and one or more fluid passages

Номер: US20160003100A1

Автор: Brady Walker, Ronnie K. KOVACIK

Принадлежит: United Technologies Corp

A rolling element bearing includes a plurality of rolling elements that are arranged circumferentially around an axis, and radially between a bearing inner ring and a bearing outer ring. The inner ring extends axially between a first end and a second end, and includes a plurality of passages that are fluidly coupled with a channel. The passages are arranged circumferentially around the axis. The channel extends axially into the inner ring from the second end, and includes a gutter that extends radially into and axially within the inner ring.

Подробнее

Номер записи: 95

07-01-2016 дата публикации

Gas turbine engine attachment structure and method therefor

Номер: US20160003104A1

Автор: David J. Sander, Shelton O. Duelm

Принадлежит: United Technologies Corp

An attachment structure for a gas turbine engine includes a frame that has a first annular case. A second annular case extends around the frame. The first annular case and the second annular case include a plurality of interlocks. Each of the interlocks includes a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second case. The first member is received in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case.

Подробнее

Номер записи: 96

07-01-2016 дата публикации

Exhaust system having a flow path liner supported by structural duct segments

Номер: US20160003192A1

Автор: Gary D Roberge

Принадлежит: United Technologies Corp

The exhaust system ( 60 ) includes an exhaust flow path liner ( 62 ) surrounded and supported by a plurality of structural duct segments ( 64, 70 ). Pluralities of links ( 84 ) are secured to and extend between the duct segments ( 64, 70 ) and the liner ( 62 ). A duct end ( 88 ) of the link includes a lock member ( 96 ) having a diameter greater than a width of the stem ( 86 ). The lock member ( 96 ) is configured to be secured within a capture nest ( 98 ) defined between and within adjacent junction flanges ( 76, 80 } of the structural duct segments { 64, 70 ) when the segments ( 64, 70 ) are secured to each other to secure the segments ( 64, 70 ) together. A catch member ( 100 ) at an opposed end of the link ( 84 ) is secured to a capture node ( 102 ) at the exhaust liner ( 62 ).

Подробнее

Номер записи: 97

05-01-2017 дата публикации

Gas turbine engine combustor liner panel with synergistic cooling features

Номер: US20170003027A1

Автор: Albert K. Cheung, Christos Adamopoulos, Frank J. Cunha, James B. Hoke, Stanislav KOSTKA, Timothy S. Snyder

Принадлежит: United Technologies Corp

A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a cone shaped pin.

Подробнее

Номер записи: 98

02-01-2020 дата публикации

Chemistry based methods of manufacture for maxmet composite powders

Номер: US20200003125A1

Автор: Christopher W. STROCK, Shahram Amini, Weina Li

Принадлежит: United Technologies Corp

A method of manufacturing a gas turbine engine air seal comprising forming at least one MAX phase particle. The method includes coating the at least one MAX phase particle with a metallic shell. The method includes applying the at least one MAX phase metallic coated particle to a surface of a substrate of the air seal to form an abradable layer of a MAXMET composite abradable material from the at least on MAX phase metallic coated particle.

Подробнее

Номер записи: 99

02-01-2020 дата публикации

Fan blades with abrasive tips

Номер: US20200003225A1

Автор: Changsheng Guo, Christopher W. STROCK

Принадлежит: United Technologies Corp

A fan blade for a gas turbine engine is disclosed. The disclosed fan blade includes an airfoil having a leading edge, a trailing ling edge, a convex side, a concave side and a distal tip. The leading edge, trailing edge, convex side and concave side of the airfoil is at least partially coated with an erosion resistant coating. The distal tip of the airfoil is coated with a bonded abrasive coating. The bonded abrasive coating engages the abradable coating disposed on the fan liner and, because of its low thermal conductivity, reduces heat transfer to the distal tip of the fan blade. The reduction in heat transfer to the distal tip of the fan blade preserves the integrity of erosion resistant coatings that may be applied to the body or the airfoil of the fan blade.

Подробнее

Номер записи: 100

02-01-2020 дата публикации

Harmonic Drive for Shaft Driving Multiple Stages of Vanes via Gears

Номер: US20200003228A1

Автор: Gabriel L. Suciu, Jesse M. Chandler

Принадлежит: United Technologies Corp

A gas turbine engine includes a harmonic drive driven by an actuator, a drive shaft driven by the harmonic drive, the drive shaft with a first drive gear and a second drive gear. A first variable vane stage with a first actuator gear to direct drive one of a multiple of variable vanes, the first actuator gear meshed with the first drive gear; and a second variable vane stage with a second actuator gear to direct drive one of a multiple of variable vanes, the second actuator gear meshed with the second drive gear.

Подробнее

Номер записи: 101

03-01-2019 дата публикации

Helical skin cooling passages for turbine airfoils

Номер: US20190003316A1

Автор: Jeffrey T. Morton, San Quach

Принадлежит: United Technologies Corp

An airfoil for a gas turbine engine may comprise an airfoil body having an outer diameter (OD) end extending between a leading edge and a trailing edge and having an ID end located opposite the airfoil body from the OD end. The airfoil body defines a helical skin cooling passage extending between the ID end of the airfoil and the OD end of the airfoil. The airfoil body may further define a main body core. The helical skin cooling passage may thermally shield the main body core.

Подробнее

Номер записи: 102

03-01-2019 дата публикации

Aircraft thermal management system

Номер: US20190003391A1

Автор: Brian Merry, Gabriel L. Suciu, James D. Hill, Nathan Snape

Принадлежит: United Technologies Corp

An aircraft thermal management system includes a first fluid system containing a first fluid, a fluid loop containing a thermally neutral heat transfer fluid, a second fluid system containing a second fluid, a first heat exchanger configured to transfer heat from the first fluid to the thermally neutral heat transfer fluid, and a second heat exchanger configured to transfer heat from the thermally neutral heat transfer fluid to the second fluid. The fluid loop is configured to provide the thermally neutral heat transfer fluid to the first heat exchanger at a pressure that matches the pressure of the first fluid.

Подробнее

Номер записи: 103