TURBOMACHINE INCLUDING A MIXING TUBE ELEMENT HAVING A VORTEX GENERATOR

A turbomachine includes a compressor section, a combustor operatively connected to the compressor section, an end cover mounted to the combustor, and an injection nozzle assembly operatively connected to the combustor. The injection nozzle assembly includes a plurality of mixing tube elements. Each of the plurality of mixing tube elements includes a conduit having a first fluid inlet, a second fluid inlet arranged downstream from the first fluid inlet, a discharge end arranged downstream from the first and second fluid inlets, and a vortex generator arranged between the first and second fluid inlets. The vortex generator is configured and disposed to create multiple vortices within the conduit to mix first and second fluids passing through each of the plurality of mixing tube elements.

Combustor with a Lean Pre-Nozzle Fuel Injection System

The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air. 1. A combustor for combusting a flow of fuel and a flow of air , comprising:a plurality of fuel nozzles;a lean pre-nozzle fuel injection system positioned upstream of the plurality of fuel nozzles; anda premixing annulus positioned between the plurality of fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air.2. The combustor of claim 1 , wherein each of the plurality of fuel nozzles comprises a fuel injector and a swirler.3. The combustor of claim 1 , wherein each of the plurality of fuel nozzles comprises a plurality of outer fuel nozzles.4. The combustor of claim 1 , wherein the plurality of fuel nozzles comprises a bellmouth.5. The combustor of claim 1 , further comprising a cap baffle and a casing and wherein the cap baffle and the casing define the premixing annulus.6. The combustor of claim 5 , wherein the cap baffle and the casing comprise a flared shape that expands towards the plurality of fuel nozzles.7. The combustor of claim 1 , wherein the premixing annulus comprises a smooth turning portion adjacent to the plurality of fuel nozzles.8. The combustor of claim 1 , wherein the lean pre-nozzle fuel injection system comprises a plurality of fuel injectors.9. The combustor of claim 8 , wherein each of the plurality of fuel injectors comprises a streamlined wing-like shape.10. The combustor of claim 8 , wherein each of the plurality of fuel injectors comprises a plurality of injector holes.11. A method providing a number of flows of fuel and a flow of air in a combustor claim 8 , comprising:injecting a flow of a premix fuel into a ...

APPARATUS AND METHOD FOR COOLING A COMBUSTOR CAP

A combustor includes an end cap having a perforated downstream plate and a combustion chamber downstream of the downstream plate. A plenum is in fluid communication with the downstream plate and supplies a cooling medium to the combustion chamber through the perforations in the downstream plate. A method for cooling a combustor includes flowing a cooling medium into a combustor end cap and impinging the cooling medium on a downstream plate in the combustor end cap. The method further includes flowing the cooling medium into a combustion chamber through perforations in the downstream plate.

FUEL INJECTION ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME

A fuel injection assembly for use in a turbine engine is provided. The fuel injection assembly includes a plurality of tube assemblies wherein each of the plurality of tube assemblies includes a plurality of tubes. At least one injection system is coupled to at least one tube assembly of the plurality of tube assemblies. The injection system includes a fuel delivery pipe and a fluid supply member coupled to the fuel delivery pipe, wherein the fluid supply member is positioned a predefined distance upstream from the tube assembly and includes at least one first portion having an annular end portion. The annular end portion includes at least one opening for delivering fluid toward the tube assembly for reducing dynamic pressure oscillations and/or reducing the temperature within a combustor during operation of the turbine engine. 1. A fuel injection assembly for use in a turbine engine , said fuel injection assembly comprising:a plurality of tube assemblies wherein each of said plurality of tube assemblies comprises a plurality of tubes; andat least one injection system coupled to at least one tube assembly of said plurality of tube assemblies, wherein said at least one injection system comprises a fuel delivery pipe and a fluid supply member coupled to said fuel delivery pipe, wherein said fluid supply member is positioned a predefined distance upstream from said at least one tube assembly and comprises at least one first portion comprising an annular end portion, wherein said annular end portion comprises at least one opening for delivering fluid toward said at least one tube assembly for reducing at least one of dynamic pressure oscillations and temperature within a combustor during operation of the turbine engine.2. A fuel injection assembly in accordance with claim 1 , wherein said fuel delivery pipe comprises a first end portion coupled within said at least one tube assembly.3. A fuel injection assembly in accordance with claim 1 , wherein said fluid supply ...

Combustor with a lean pre-nozzle fuel injection system

The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air.

Annular ring-manifold quaternary fuel distributor

A combustor section is provided and includes one or more annular quaternary fuel manifolds mounted within an annular passage defined between a casing and a cap assembly of a combustor through which air and/or a fuel/air mixture flows upstream from a fuel nozzle support, the manifold including a body to accommodate quaternary fuel therein, the body defining injection holes through which the quaternary fuel is injected into a section of the passage at a location upstream from the fuel nozzle support.

Flame tolerant secondary fuel nozzle

A combustor for a gas turbine engine includes a plurality of primary nozzles configured to diffuse or premix fuel into an air flow through the combustor; and a secondary nozzle configured to premix fuel with the air flow. Each premixing nozzle includes a center body, at least one vane, a burner tube provided around the center body, at least two cooling passages, a fuel cooling passage to cool surfaces of the center body and the at least one vane, and an air cooling passage to cool a wall of the burner tube. The cooling passages prevent the walls of the center body, the vane(s), and the burner tube from overheating during flame holding events.

Efficient memory transformer based acoustic model for low latency streaming speech recognition

In one embodiment, a method includes accessing a machine-learning model configured to generate an encoding for an utterance by using a module to process data associated with each segment of the utterance in a series of iterations, performing operations associated with an i-th segment during an n-th iteration by the module, which include receiving an input comprising input contextual embeddings generated for the i-th segment in a preceding iteration and a memory bank storing memory vectors generated in the preceding iteration for segments preceding the i-th segment, generating attention outputs and a memory vector based on keys, values, and queries generated using the input, and generating output contextual embeddings for the i-th segment based on the attention outputs, providing the memory vector to the module for performing operations associated with the i-th segment in a next iteration, and performing speech recognition by decoding the encoding of the utterance.

Premixing apparatus for gas turbine system

A premixing apparatus for a gas turbine system includes non-swirl elements around a periphery of a face of a premixing apparatus and a swirl assembly located substantially at a center of the face. The non-swirl elements premix a premixture prior to the premixture being delivered to a combustor of the gas turbine system. The swirl assembly disturbs a flow of fluid prior to the fluid being delivered to the combustor. The premixture includes fuel and oxidant, and the fluid disturbed by the swirl assembly includes the oxidant or the premixture.

Combustor and method for conditioning flow through a combustor

A combustor includes an end cap that extends radially across a portion of the combustor and includes an upstream surface axially separated from a downstream surface. A combustion chamber is downstream of the end cap. Premixer tubes extend from a premixer tube inlet proximate to the upstream surface through the downstream surface to provide fluid communication through the end cap and include means for conditioning flow through the plurality of premixer tubes. A method for conditioning flow through a combustor includes flowing a working fluid through a first and second set of premixer tubes that extend axially through an end cap, wherein the second set of premixer tubes includes means for conditioning flow through the second set of premixer tubes, and flowing a fuel through the first or second set of premixer tubes.

PRE-MIXING BASED FUEL NOZZLE FOR USE IN A COMBUSTION TURBINE ENGINE

A pre-mixing type of fuel nozzle () for use in a combustion turbine engine is provided. The nozzle includes an array of pre-mixing conduits () that extends between an inlet end () and an outlet end () of a body of the nozzle. The nozzle may further include an array of air flow conduits () disposed radially inwardly relative to the array of pre-mixing conduits. The nozzle may include an inter-conduit passageway arranged to aerodynamically reduce flow recirculation in the array of pre-mixing conduits. A fuel-directing structure () may include non-swirl elements () to direct fuel flow along a radial direction, each non-swirl element including at least one orifice () to inject the fuel flow directed along the radial direction into a respective pre-mixing conduit to pre-mix air and fuel. 21. A fuel nozzle comprising:a body having an inlet end and an outlet end and defining a central axis that extends between the inlet end and the outlet end along an axial direction of the fuel nozzle;an array of pre-mixing conduits extending between the inlet end and the outlet end of the body, the array of pre-mixing conduits circumferentially disposed about the central axis of the body, each pre-mixing conduit fluidly coupled to receive air at a respective inlet;an array of air flow conduits disposed radially inwardly relative to the array of pre-mixing conduits;means to aerodynamically reduce flow recirculation in the array of air/fuel pre-mixing conduits, wherein the means to aerodynamically reduce the flow recirculation in a respective pre-mixing conduit comprises an inter-conduit passageway arranged to provide fluid communication between the respective pre-mixing conduit and a corresponding air flow conduit; anda fuel-directing structure in the body comprising a plurality of non-swirl elements, each non-swirl element including a radially-extending passageway to direct fuel flow along a radial direction, each non-swirl element including at least one orifice to inject the fuel flow ...

Turbomachine including a mixing tube element having a vortex generator

A turbomachine includes a compressor section, a combustor operatively connected to the compressor section, an end cover mounted to the combustor, and an injection nozzle assembly operatively connected to the combustor. The injection nozzle assembly includes a plurality of mixing tube elements. Each of the plurality of mixing tube elements includes a conduit having a first fluid inlet, a second fluid inlet arranged downstream from the first fluid inlet, a discharge end arranged downstream from the first and second fluid inlets, and a vortex generator arranged between the first and second fluid inlets. The vortex generator is configured and disposed to create multiple vortices within the conduit to mix first and second fluids passing through each of the plurality of mixing tube elements.

SEGMENTED ANNULAR RING-MANIFOLD QUATERNARY FUEL DISTRIBUTOR

A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.

ANNULAR RING-MANIFOLD QUATERNARY FUEL DISTRIBUTOR

A combustor section is provided and includes one or more annular quaternary fuel manifolds mounted within an annular passage defined between a casing and a cap assembly of a combustor through which air and/or a fuel/air mixture flows upstream from a fuel nozzle support, the manifold including a body to accommodate quaternary fuel therein, the body defining injection holes through which the quaternary fuel is injected into a section of the passage at a location upstream from the fuel nozzle support.

Segmented annular ring-manifold quaternary fuel distributor

A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.

Method for preparing ultrathin two-dimensional nanosheets and applications thereof

A method for preparing an ultrathin two-dimensional (2D) monocrystalline nanosheet, the method including: 1) placing BiX 3 powder where X=I, Br, or Cl in a crucible, and putting the crucible on a first heating zone of a furnace disposed at a gas inlet of a quartz tube; placing substrates covered with metal sheets on a second heating zone of the furnace disposed at a gas outlet of the quartz tube; 2) vacuumizing the quartz tube; pumping Ar gas into the quartz tube until the air pressure is 101.325 kPa; pumping a carrier gas into the quartz tube; and 3) heating and maintaining the second heating zone; heating the first heating zone for BiX 3 evaporation until producing chemical reaction between BiX 3 and the metal sheets, and preparing ultrathin 2D nanosheets on the substrates simultaneously; and cooling the substrate naturally to 15-30° C.

Apparatus and method for cooling a combustor cap

A combustor includes an end cap having a perforated downstream plate and a combustion chamber downstream of the downstream plate. A plenum is in fluid communication with the downstream plate and supplies a cooling medium to the combustion chamber through the perforations in the downstream plate. A method for cooling a combustor includes flowing a cooling medium into a combustor end cap and impinging the cooling medium on a downstream plate in the combustor end cap. The method further includes flowing the cooling medium into a combustion chamber through perforations in the downstream plate.

COMBUSTOR AND METHOD FOR CONDITIONING FLOW THROUGH A COMBUSTOR

A combustor includes an end cap that extends radially across a portion of the combustor and includes an upstream surface axially separated from a downstream surface. A combustion chamber is downstream of the end cap. Premixer tubes extend from a premixer tube inlet proximate to the upstream surface through the downstream surface to provide fluid communication through the end cap and include means for conditioning flow through the plurality of premixer tubes. A method for conditioning flow through a combustor includes flowing a working fluid through a first and second set of premixer tubes that extend axially through an end cap, wherein the second set of premixer tubes includes means for conditioning flow through the second set of premixer tubes, and flowing a fuel through the first or second set of premixer tubes. 1. A combustor , comprising:a. an end cap that extends radially across at least a portion of the combustor, wherein the end cap comprises an upstream surface axially separated from a downstream surface;b. a combustion chamber downstream of the end cap;c. a plurality of premixer tubes that extend from a premixer tube inlet proximate to the upstream surface through the downstream surface of the end cap, wherein each premixer tube provides fluid communication through the end cap to the combustion chamber;d. means for conditioning flow through the plurality of premixer tubes.2. The combustor as in claim 1 , wherein the means for conditioning flow through the plurality of premixer tubes comprises one or more slots in one or more premixer tube inlets.3. The combustor as in claim 2 , wherein the slots have at least one of a rounded claim 2 , pointed claim 2 , or flat shape.4. The combustor as in claim 1 , wherein the means for conditioning flow through the plurality of premixer tubes comprises one or more apertures proximate to one or more premixer tube inlets.5. The combustor as in claim 4 , wherein the apertures have at least one of an arcuate or polygonal ...

FLAME TOLERANT SECONDARY FUEL NOZZLE

A combustor for a gas turbine engine includes a plurality of primary nozzles configured to diffuse or premix fuel into an air flow through the combustor; and a secondary nozzle configured to premix fuel with the air flow. Each premixing nozzle includes a center body, at least one vane, a burner tube provided around the center body, at least two cooling passages, a fuel cooling passage to cool surfaces of the center body and the at least one vane, and an air cooling passage to cool a wall of the burner tube. The cooling passages prevent the walls of the center body, the vane(s), and the burner tube from overheating during flame holding events.

DLN DUAL FUEL PRIMARY NOZZLE

The primary nozzles of a Dry Low NOx (DLN) combustor are configured to alternatively burn a first gas fuel or a second gas fuel, where the two gas fuels may have widely disparate energy content. Natural gas may be the first gas fuel and syngas may be the second gas fuel. An inner fuel circuit and an outer fuel circuit are provided to allow effective control of fuel/air mixing profiles, dynamics, primary pre-ignition and emission control by changing the fuel split between the two fuel circuits. The inner fuel circuit may be run in a diffusion combustion mode on many gas fuels.

Premixing apparatus for gas turbine system

A premixing apparatus for a gas turbine system includes non-swirl elements around a periphery of a face of a premixing apparatus and a swirl assembly located substantially at a center of the face. The non-swirl elements premix a premixture prior to the premixture being delivered to a combustor of the gas turbine system. The swirl assembly disturbs a flow of fluid prior to the fluid being delivered to the combustor. The premixture includes fuel and oxidant, and the fluid disturbed by the swirl assembly includes the oxidant or the premixture.

METHOD FOR PREPARING ULTRATHIN TWO-DIMENSIONAL NANOSHEETS AND APPLICATIONS THEREOF

A method for preparing an ultrathin two-dimensional (2D) monocrystalline nanosheet, the method including: 1) placing BiXpowder where X=I, Br, or Cl in a crucible, and putting the crucible on a first heating zone of a furnace disposed at a gas inlet of a quartz tube; placing substrates covered with metal sheets on a second heating zone of the furnace disposed at a gas outlet of the quartz tube; 2) vacuumizing the quartz tube; pumping Ar gas into the quartz tube until the air pressure is 101.325 kPa; pumping a carrier gas into the quartz tube; and 3) heating and maintaining the second heating zone; heating the first heating zone for BiXevaporation until producing chemical reaction between BiXand the metal sheets, and preparing ultrathin 2D nanosheets on the substrates simultaneously; and cooling the substrate naturally to 15-30° C. 1. A method , comprising:{'sub': '3', 'placing BiXpowder where X=I, Br, or Cl in a crucible, and putting the crucible on a first heating zone of a furnace disposed at a gas inlet of a quartz tube; placing substrates covered with metal sheets on a second heating zone of the furnace disposed at a gas outlet of the quartz tube;'}vacuumizing the quartz tube by a mechanical pump; pumping Ar gas into the quartz tube until a gas pressure is equal to 101.325 kPa; pumping a carrier gas into the quartz tube and adjusting and maintaining a steady flow rate of the carrier gas; and{'sub': '3', 'heating and maintaining the second heating zone; heating the first heating zone to evaporate BiXuntil the ultrathin 2D nanosheets are formed on the substrate; and cooling the substrate naturally to 15-30° C.'}2. The method of claim 1 , wherein the metal sheets are unoxidized transition or naturally oxidized transition; the metal sheets and the substrates construct micro-nano scale confined space claim 1 , and a gap distance between the metal sheets and the substrates is 0-100 microns.3. The method of claim 2 , wherein the transition metal sheets are copper sheets ...

FLAME RETENTION INHIBITOR FOR FUEL INJECTION DIFFUSER IN GAS TURBINE

A flame holding inhibitor includes a base portion and an upstanding support extending away from the base portion; at least one delta-wing-shaped flap on the upstanding support, each having a relatively pointed end and a relatively broad end.

TURBOMACHINE INCLUDING A MIXTURE TUBE ELEMENT COMPRISING A WHEATBOARD GENERATOR

Une turbomachine (2) comporte une section de compresseur (4), une chambre de combustion (8, 30, 47, 50) reliée fonctionnellement à la section de compresseur (4), un capot d'extrémité (10) monté sur la chambre de combustion (8, 30, 47, 50), et un ensemble de buses d'injection (20, 21, 22) reliées fonctionnellement à la chambre de combustion (8, 30, 47, 50). L'ensemble de buses d'injection (20, 21, 22) comporte une pluralité d'éléments de tube de mélange (100). Chaque élément de la pluralité d'éléments de tube de mélange (100) comporte une conduite (130) ayant une première entrée de fluide (132), une seconde entrée de fluide (134) agencée en aval de la première entrée de fluide (132), une extrémité d'évacuation (137) agencée en aval des première et seconde entrées de fluide (132, 134) et un générateur de tourbillons (144, 170, 184, 193, 194, 195, 220, 222) agencé entre les première et seconde entrées de fluide (132, 134). Le générateur de tourbillons (144, 170, 184, 193, 194, 195, 220, 222) est configuré et disposé de manière à créer des tourbillons multiples dans la conduite (130), destinés à mélanger des premier et second fluides (132, 134) traversant chaque élément de la pluralité d'éléments de tube de mélange (100). A turbomachine (2) has a compressor section (4), a combustion chamber (8, 30, 47, 50) operably connected to the compressor section (4), an end cap (10) mounted to the chamber combustion apparatus (8, 30, 47, 50), and a set of injection nozzles (20, 21, 22) operably connected to the combustion chamber (8, 30, 47, 50). The injection nozzle assembly (20, 21, 22) includes a plurality of mixing tube members (100). Each of the plurality of mixing tube elements (100) has a conduit (130) having a first fluid inlet (132), a second fluid inlet (134) arranged downstream of the first fluid inlet (132) ), a discharge end (137) arranged downstream of the first and second fluid inlets (132, 134) and a vortex generator (144, 170, 184, ...

TURBOMACHINE INCLUDING A MIXTURE TUBE MEMBER COMPRISING A WHEAT GENERATOR

COMBUSTION DEVICE HAVING A POOR FUEL INJECTION SYSTEM UPSIDE NOZZLES

Dispositif de combustion (100) pour brûler un flux de combustible et un flux d'air. Le dispositif de combustion (100) peut comprendre un certain nombre de buses (120) de combustible, un système d'injection (270) de combustible pauvre en amont des buses, placé en amont des buses (120) de combustible, et un volume annulaire de prémélange (250) placé entre les buses (120) de combustible et le système d'injection (270) de combustible pauvre en amont des buses, pour prémélanger le flux de combustible et le flux d'air. Combustion device (100) for burning a fuel flow and an air flow. The combustion device (100) may include a number of fuel nozzles (120), a lean fuel injection system (270) upstream of the nozzles, located upstream of the fuel nozzles (120), and a volume premix annulus (250) positioned between the fuel nozzles (120) and the lean fuel injection system (270) upstream of the nozzles for premixing the fuel flow and the air flow.

Segmented annular ring-manifold quaternary fuel distributor

Premixing apparatus for gas turbine system

Brennkammer und Verfahren zur Kühlung einer Brennkammer.

Eine Brennkammer (10) enthält eine Endkappe (14), die eine gelochte stromabwärtige Platte und einen Brennraum (18) stromabwärts von der stromabwärtigen Platte aufweist. Ein Plenum (36) steht in Strömungsverbindung mit der stromabwärtigen Platte und führt dem Brennraum (18) durch die Löcher in der stromabwärtigen Platte ein Kühlmedium zu. Ein Verfahren zum Kühlen einer Brennkammer (10) enthält ein Einleiten eines Kühlmediums in eine Endkappe (14) einer Brennkammer (10) und Beaufschlagen einer stromabwärtigen Platte in der Endkappe (14) der Brennkammer (10) mit dem Kühlmedium. Das Verfahren enthält ferner ein Einleiten des Kühlmediums in die Brennkammer (18) hinein durch Löcher in der stromabwärtigen Platte hindurch.

Optical signal detection apparatus and method and related device

Optical signal detection apparatus and method and related device

This application provides an optical signal detection apparatus and method and a related device. The apparatus may be configured to process an optical signal detected in a detection cycle of the optical signal, and the apparatus includes an optical-to-electrical conversion module, a control module, a gain adjustment module, and an analog-to-digital conversion module. The optical-to-electrical conversion module is configured to receive an optical signal, and convert a received optical signal into an electrical signal; the control module is configured to obtain a first gain value corresponding to a first detection time period, the first detection time period is a detection time period in the detection cycle, different detection time periods in the detection cycle correspond to different gain values, and the first gain value is used for controlling the gain adjustment module to adjust an amplitude of the electrical signal; and the analog-to-digital conversion module is configured to perform sampling on an adjusted electrical signal, where the adjusted electrical signal is in a sampling range of the analog-to-digital conversion module. The apparatus can improve measurement accuracy of an optical fiber measurement device and an actual dynamic range of the optical fiber measurement device.

Method and system for forecasting agricultural product price based on signal decomposition and deep learning

Disclosed are a method and a system for forecasting an agricultural product price based on signal decomposition and deep learning. The method includes: S 1, obtaining price subsequences by performing a complementary ensemble empirical mode decomposition (CEEMD) on an original price sequence of agricultural products; S 2, obtaining a reconstructed sequence based on the price subsequences; S 3, obtaining data features of the reconstructed sequence based on the reconstructed sequence; and S 4, constructing a Bi-directional Sequence to Sequence (BiSeq2seq) model, and inputting the data features of the reconstructed sequence into a CCS-Bi-directional Sequence to Sequence (CCS-BiSeq2seq) model to obtain a forecasting result.

Pre-mixing based fuel nozzle for use in a combustion turbine engine

A pre-mixing type of fuel nozzle (10) for use in a combustion turbine engine is provided. The nozzle includes an array of pre-mixing conduits (20) that extends between an inlet end (14) and an outlet end (16) of a body (12) of the nozzle. The nozzle may further include an array of air flow conduits (22) disposed radially inwardly relative to the array of pre-mixing conduits. The nozzle may include an inter-conduit passageway 24 arranged to aerodynamically reduce flow recirculation in the array of pre-mixing conduits. A fuel-directing structure (26) may include non-swirl elements (28) to direct fuel flow along a radial direction, each non-swirl element including at least one orifice (32) to inject the fuel flow directed along the radial direction into a respective pre-mixing conduit to pre-mix air and fuel.

Optical signal detection apparatus and method and related device

An optical signal detection apparatus. The apparatus includes an optical-to-electrical conversion module, a control module, a gain adjustment module, and an analog-to-digital conversion module. The optical-to-electrical conversion module is configured to receive an optical signal, and convert a received optical signal into an electrical signal; the control module is configured to obtain a first gain value corresponding to a first detection time period, the first detection time period is a detection time period in the detection cycle, different detection time periods in the detection cycle correspond to different gain values, and the first gain value is used for controlling the gain adjustment module to adjust an amplitude of the electrical signal; and the analog-to-digital conversion module is configured to perform sampling on an adjusted electrical signal, where the adjusted electrical signal is in a sampling range of the analog-to-digital conversion module.

Turbomaschine mit einem Mischrohrelement mit einem Wirbelgenerator

Turbomaschine (2), die aufweist:einen Verdichterabschnitt (4);eine Brennkammer (8, 30, 147, 50), die mit dem Verdichterabschnitt (4) betriebsmäßig verbunden ist;eine Endabdeckung (10), die an der Brennkammer (8, 30, 47, 50) montiert ist; undeine Einspritzdüsenanordnung (20, 21, 22), die mit der Brennkammer (8, 30, 47, 50) betriebsmäßig verbunden ist, wobei die Einspritzdüsenanordnung (20, 21, 22) mehrere Mischrohrelemente (100) enthält, die von einem Gehäuse (82) umgeben sind, und eine erste Fluidplenumkammer (95) und eine zweite Fluidplenumkammer (95) innerhalb des Gehäuses (82) definiert, wobei die zweite Fluidplenumkammer von der ersten Fluidplenumkammer (84) verschieden und stromabwärts der ersten Fluidplenumkammer (84) angeordnet ist, wobei jedes der mehreren Mischrohrelemente (100) eine Leitung (130) enthält, die einen ersten Fluideinlass (132), der mit der ersten Fluidplenumkammer (84) fluidmäßig verbunden ist, einen zweiten Fluideinlass (134), der mit der zweiten Fluidplenumkammer (95) fluidmäßig verbunden und stromabwärts von dem ersten Fluideinlass (132) angeordnet ist, ein Auslassende (137), das stromabwärts von dem ersten und dem zweiten Fluideinlass (132, 134) angeordnet ist, und einen Wirbelgenerator (144, 170, 184, 193, 194, 195, 220, 222) aufweist, der zwischen dem ersten und dem zweiten Fluideinlass (132, 134) angeordnet und mit der ersten Fluidplenumkammer (84) fluidmäßig verbunden ist, wobei der Wirbelgenerator (144, 170, 184, 193, 194, 195, 220, 222) eingerichtet und angeordnet ist, um mehrere Wirbel im Inneren der Leitung (130) zu erzeugen, um das erste und das zweite Fluid (132, 134), die durch jedes der mehreren Mischrohrelemente (100) hindurchtreten, miteinander zu vermischen.