CN203835539U - Gas turbine engine with central axis - Google Patents
Gas turbine engine with central axis Download PDFInfo
- Publication number
- CN203835539U CN203835539U CN201420230761.1U CN201420230761U CN203835539U CN 203835539 U CN203835539 U CN 203835539U CN 201420230761 U CN201420230761 U CN 201420230761U CN 203835539 U CN203835539 U CN 203835539U
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- Prior art keywords
- air
- prediffusion
- turbine engine
- gas turbine
- central tube
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The utility model discloses a gas turbine engine with a central axis. The gas turbine engine with the central axis comprises an air flow separator and a central pipeline. The gas turbine engine is constructed to be used for separating and receiving compressed air from an outlet of a pre-diffuser, and guiding the separated air flows of compressed air to individual downstream parts, and is used for combustion reaction and cooling. The gas turbine engine also comprises an axial mixer, and is constructed to be used for axially receiving air flows of the compressed air and guiding air flows and fuel oil provided by an ejector to be mixed. According to the gas turbine engine, compressed air is diffused in a combustor; a pipeline network with reduced loss is formed in the combustion chamber, so that the gas turbine engine is improved, and also the performances and the efficiency can be improved, and maintenance and reparation and/or reducing expense can be reduced.
Description
Technical field
The utility model relates to the firing chamber in a kind of gas turbine engine, is specifically related to a kind ofly for spread compressed-air actuated system at gas turbine combustors, more particularly, relates to a kind of gas turbine engine with central axis.
Background technique
Typical case's gas turbine engine comprises compressor downstream diffuser.The object of diffuser is to reduce from the high speed of compressor to discharge air-flow to the speed that is suitable for burning, as far as possible velocity head is regenerated as to static pressure simultaneously.After the prediffusion device of flowing through, pressurized air is dumped in burner inner liner rapid extended region around.
Current, the U. S. Patent 4,527,385 that Markowski proposed on July 9th, 1985 shows a kind of diffuser system for gas turbine engine, comprises prediffusion device and airflow diversion is become to the pipe-line system of two.Article one, air-flow is caught prediffusion device exhausting air in total pressure in the gas path center of highest level, and by its around burner sudden expansion with provide lining cooling-air, turbine cooling air and if necessary diluent air in a small amount with before regulating radial temperature profile, extra diffusion phase is provided, another air-flow is directly delivered to burner by pipeline, avoids typical sudden expansion diffuser losses.
Summary of the invention
The purpose of this utility model is to provide a kind of gas turbine engine with central axis, to reduce losses of compressed air.
It is a kind of for spread compressed-air actuated system in firing chamber that the utility model provides, it is applicable to use, operation, maintenance, repairing and the improvement of gas turbine engine, and can be used to improve performance and efficiency, minimizing maintenance and repair and/or reduction expense.
In one aspect, the utility model provides a kind of gas turbine engine with central axis, and described gas turbine engine comprises compressor, prediffusion device, and described prediffusion device is pneumatically connected to compressor; Described prediffusion device comprises the outlet of prediffusion device, outer wall and inwall, and for the system of blended fuel oil and air; Described system comprises: fluid separator, be positioned at the position of closing on the outlet of prediffusion device, and be configured to shunting from the pressurized air of prediffusion device outlet, by central gas stream and outer air-flow and interior airflow breakaway, central gas stream has than outer air-flow and the higher mean velocity of interior air-flow; Central tube, comprise central tube entrance and central tube outlet, described central tube is configured to pneumatically connect in central tube ingress a part for prediffusion device outlet, this part departs from from outer wall and inwall, the firing chamber that the central gas stream that central tube reception exports from prediffusion device and direction center air-flow enter gas turbine engine; And the axial mixer that is arranged in central tube, described axial mixer is configured to the fuel mix that direction center air-flow and sparger provide.
Wherein, effective flow region of central tube increases between central tube entrance and central tube outlet.
Further, described axial mixer comprises blade mixer, and described blade mixer has a plurality of alternately blades around sparger axle circle distribution.
Further again, effective flow region of central tube increases at central tube entrance and a plurality of replacing between blade; Effective flow region of central tube remains unchanged or reduces effective flow region between a plurality of alternately blades and central tube outlet.
Wherein, described central tube is configured to extend to and pneumatically connect the burning cavity of gas turbine engine.
Wherein, described axial mixer is configured to direction center air-flow and mixes in the burning cavity of gas turbine engine with fuel.
Wherein, described axial mixer is configured to direction center air-flow and fuel in the combined upstream of the burning cavity of gas turbine engine.
Wherein, described fluid separator extends into prediffusion device in the upstream of prediffusion device outlet, and fluid separator in prediffusion device by central gas stream and outer air-flow and interior airflow breakaway.
Wherein, described central tube is configured so that central gas stream only comprises the pressurized air that has certain speed, leaves the outlet of prediffusion device along radial velocity profile, and this speed is more than or equal to the whole compressed-air actuated mean velocity that leaves the outlet of prediffusion device along radial velocity profile.
Further, described gas turbine engine also comprises intermediate conduit, and described intermediate conduit comprises intermediate conduit entrance and intermediate conduit outlet, and described intermediate conduit is configured to discharge the air from central tube by intermediate conduit entrance, and guiding exhaust air to burning cavity, in order to cooling.
On the other hand, it is a kind of for the system at gas turbine engine fuel combination and air that the utility model provides, described system comprises: the central tube with intermediate conduit entrance, this central tube is configured to connect at intermediate conduit entrance, for example pneumatically be connected to the outlet of prediffusion device and extend prediffusion device outlet downstream, central tube is further configured to receive compressed-air actuated central gas stream from the outlet of prediffusion device, outer air-flow and the interior airflow breakaway of this central gas stream and air from prediffusion device outlet, outer air-flow is radially inside with respect to central axis radially outward and interior air-flow from central gas stream, central tube is further configured to direction center air-flow to the firing chamber of gas turbine engine, described system also comprises axial mixer, and the fuel oil that being configured to axially to receive compressed-air actuated central gas stream and direction center air-flow provides with sparger mixes.
Technique scheme spreads pressurized air in firing chamber, has formed the piping network that loss reduces in firing chamber.
Accompanying drawing explanation
Accompanying drawing 1 is the schematic diagram of typical gas turbine engine;
Accompanying drawing 2 is side cross-sectional view of the firing chamber in the gas turbine engine of accompanying drawing 1;
Accompanying drawing 3 is the sectional axis views along the 3-3 line of accompanying drawing 2;
Accompanying drawing 4 is the isometric maps of a kind of mode of execution of pipeline module of a part of prediffusion device that are connected to the firing chamber of accompanying drawing 2;
Accompanying drawing 5 is the isometric maps that form the right lobate mixer of plane of whirlpool.
Embodiment
The present embodiment discloses a kind of for spread compressed-air actuated method in firing chamber, and its high-speed core that selectively extracts prediffusion device exit flow is in order to burning, and provide prediffusion device exit flow compared with extra diffusion and the pressure recovery of low speed exterior domain.Piping network is positioned at the outlet of prediffusion device, makes high-speed core separated and guiding as required by low speed exterior domain of required part.
Accompanying drawing 1 is the schematic diagram of typical gas turbine engine.For clear and be easy to explain, ignored or expanded some surfaces.The present embodiment can be with reference to the running shaft (" central axis " 95) of gas turbine engine, and its longitudinal axis that conventionally passes through the axle 120 of himself is determined.Central axis 95 can be common or share with a plurality of other motor concentric parts.About radially, axially and whole references and the measurement of circumferencial direction be reference center axis 95, unless defined especially, and for example the therefrom smaller or greater radial distance of axle line 95 indicated conventionally in the term of " interior " and " outward ", wherein, radially 96 can be perpendicular to and from the outside any directions of radiation of central axis 95.
In addition, the present embodiment is with reference to forward and backward directions.Conventionally, the flow direction about whole references of " forward " and " backward " about main air flow (namely, being used in the air in flame mechanism), unless defined especially.For example,, forward with respect to mobile " upstream " (namely, the entering the point of system towards air) of main air flow; Backward with respect to mobile " downstream " (namely, the leaving the point of system towards air) of main air flow.
Conventionally, gas turbine engine 100 comprises that entrance 110, axle 120(are supported by bearing 150), compressor 200, firing chamber 300, turbine 400, exhaust unit 500 and power output linkage unit 600.Compressor 200 comprises one or more compressor drum assemblies 220.Turbine 400 comprises one or more turbine rotor assemblies 420.
Firing chamber 300 comprises combustion chamber shell 310, inner bearing shell 311, a plurality of pillar 312, outer shield 314, interior guard shield 316, a plurality of sparger 350 and burning cavity 390.Combustion chamber shell 310 and inner bearing shell 311 can be coaxial clamshell style housings, form substantially ring cavity and extend to turbine 400 from compressor 200 between them.Combustion chamber shell 310 and inner bearing shell 311 can combine by a plurality of pillars 312.Burning cavity 390 or " lining " are arranged in ring cavity and are configured to bear and relevant high pressure and the high temperature of burning.
Outer shield 314 and interior guard shield 316 have been determined the region in burning cavity 390 outsides, at this, can guide air in order to cooling.Especially, outer shield 314 can be from burning cavity 390 radially outwards, and interior guard shield 316 can be radially inside from burning cavity 390.For example, outer shield 314 and/or interior guard shield 316 can comprise the pipeline of pressurized air being brought into burning cavity 390, and can be applicable to heat exchange.According to a mode of execution, outer shield 314 can comprise the part of combustion chamber shell 310, and interior guard shield 316 can comprise the part of inner bearing shell 311, for example, the two one of inner wall structure for pressurized air is guided to burning cavity 390 in order to cooling position.
In operation, enter the air of entrance 110 as " operation fluid ", and compress by compressor 200.In compressor 200, operation fluid is compressed in annular flow passage by a series of compressor disc assemblies 220.Once pressurized air leaves compressor 200, enter firing chamber 300, it is diffused and mixes with fuel oil at this.Fuel oil and some air are injected into burning cavity 390 and are lighted by sparger 350.Some air are directed in order to cooling.After combustion reaction, by turbine 400, via a series of turbine rotor assemblies 420, from the fuel/air mixture of lighting, obtain energy.Exhausting air is by exhaust unit 500 discharge systems.
The fuel oil that transfers to firing chamber 300 can comprise the liquid or gaseous fuel based on hydrocarbon of any known type.Liquid fuel can comprise diesel oil, heating oil, JP5, jet propulsion fuel or kerosene.In some embodiments, liquid fuel can comprise natural gas liquids (for example, as example, ethane, propane, butane etc.), paraffinic base oil (for example JET-A) and gasoline.Vaporized fuel can comprise rock gas.In some embodiments, vaporized fuel can also comprise alternative vaporized fuel, for example, as example, and liquefied petroleum gas (LPG) (LPG), ethene, landfill refuse gas, biogas, ammoniacal liquor, biogas, coal gas, refinery's waste gas, etc.Liquid and the above-mentioned of vaporized fuel do not mean it is exhaustive list for example, is only example.Conventionally, any liquid or gaseous fuel as known in the art can be transported to firing chamber 300 through sparger 350.
Similarly, one or more above-mentioned parts (or their subassembly) can be by stainless steel and/or the material or the multiple ceramic structure that are known as the born high temperature of " superalloy " make.Superalloy or high performance alloys are to be presented on mechanical strength fabulous in high temperature and creep resistance, good surface stability and corrosion protection and anti-oxidation alloy.Superalloy can comprise for example hastelloy, inconel, WASPALOY, RENE alloy, HAYNES alloy, INCOLOY, MP98T, TMS alloy and CMSX single crystal alloy.Ceramic structure can comprise whole composition and/or pottery/pottery and ceramic/metal matrix components.
Accompanying drawing 2 is side cross-sectional view of the firing chamber in the gas turbine engine of accompanying drawing 1.For object clear and signal, special characteristic/parts are increased, remove and/or revise.As shown in the figure, compressor 200 stops at compressor discharge 290 places that are positioned at its downstream end.Compressor discharge 290 can form annular pass, and high-speed compressed air can be discharged compressor 200 through compressor discharge 290.Compressor discharge 290 connects (being for example fluidly connected to) prediffusion device 320.
Prediffusion device 320 comprises prediffusion device entrance 321 and prediffusion device outlet 322.Prediffusion device entrance 321 is fluidly connected to compressor discharge 290.Prediffusion device 320 is configured to stablize the high-speed compressed air that spreads the compression of leaving compressor 200 with controlled mode.Prediffusion device outlet 322 is fluidly connected to compressor air piping network 330.Firing chamber air conduit network 330 is positioned at the outlet port of prediffusion device 320.
Compressor air piping network 330 comprises a plurality of pipelines that form discrete air flue or passage.Especially, the air-flow of each pipeline from other outer gas stream separating pipe.Firing chamber air conduit network 330 is configured to receive pressurized air and it is guided to precalculated position from prediffusion device 320.Firing chamber air conduit network 330 can be divided compressed-air actuated part and maybe can is received in independent air flows and be received pressurized air by downstream fluid separator.Each air passageways of any convenient cross section is smooth, and is shaped in guiding and reduces (for example, from airflow breakaway) loss.Pipeline can form separator jointly, is configured to separated and spreads the pressurized air that leaves prediffusion device 320, is reduced in simultaneously and leaves prediffusion device 320 loss (for example, dumping loss) afterwards.
According to a mode of execution, firing chamber air conduit network 330 can comprise one or more fluid separators or divide device.Fluid separator or division device can radially and/or circumferentially be located.For example, the fluid separator of radial location can be constructed to divide the outlet 322 of prediffusion device for annular sector, and each has radially-arranged pressurized air velocity profile.The radially-arranged velocity profile of each annular sector can for example approach the outer wall 323 of prediffusion device 320 and inwall 324(, owing to setting up that boundary layer, diffusion are reclaimed etc. and slower) for example locate, compared with (central gas stream that, has represented minimal diffusion) between outer wall 323 and inwall 324 obviously slack-off.
Also as example, the fluid separator 337(accompanying drawing 4 of circumferential registration) can be constructed to before entering pipeline separation center air-flow away from outer air-flow and interior air-flow.At this, from central gas stream, with respect to central axis 95, outer air-flow radially outward and interior air-flow are radially inside.For example, when leaving prediffusion device and export 322, central gas stream can comprise a part of pressurized air having higher than outer air-flow and interior air-flow mean velocity.Equally as example, central gas stream can comprise that a part leaves the pressurized air of prediffusion device outlet 322, and at this, the ratio of airspeed/mean velocity is more than or equal to unanimously along radial velocity profile.
Pipeline can be independent tubes or guard shield, has formed air passageways.Alternatively, one or more pipelines can combine with other pipelines, thereby form pipeline manifold road, and pipeline manifold road has a plurality of air passagewayss.Pipeline or pipeline manifold road can be fixed to or be integrated into the inside of firing chamber 300, and/or are connected to other inner member.In addition, pipeline or pipeline manifold road can be continuous or be made by the attachment portion between import and outlet.In addition, the pipeline of one or more parts or pipeline manifold road can be integrated into one or more other parts (for example, sparger 350, outer shield 314 and interior guard shield 316 etc.).
Accompanying drawing 3 is the sectional axis views along the 3-3 line of accompanying drawing 2.According to a mode of execution, firing chamber air conduit network 330 can be made by a plurality of pipeline modules 331.Especially, firing chamber air conduit network 330 can be made by the many groups of pipelines that combine, and every group has formed a pipeline module 331, comprises the part of the total air passageways in firing chamber air conduit network 330.Equally, firing chamber air conduit network 330 can be made by a plurality of pipeline manifolds road, and each pipeline manifold road forms a pipeline module 331, comprises the part of the total air passageways in firing chamber air conduit network 330.
Each pipeline module 331 can be supported in firing chamber 300 by the combination of any mode easily or supporter.For example, every end place of pipeline module 331 each air passageways separately that can be supported on it.As example, pipeline module 331 can be fixed to the interior structural support of combustion chamber shell 310, inner bearing shell 311 and/or pillar 312 equally.As example, pipeline module 311 can support by other inner member equally, for example outer shield 314, interior guard shield 316, sparger 350, burning cavity 390 and/or other pipeline module 331.
According to a mode of execution, pipeline module 331 can be arranged or in addition with other side by side, form and be fluidly connected to prediffusion device and export 322 annular array.As shown in the figure, firing chamber air conduit network 330 can be made by a plurality of pipeline modules 331 around central axis 95 circle distribution.Each pipeline module 331 can occupy an annular sector of firing chamber 300.For example, each pipeline module 331 can be connected or the pneumatic prediffusion device that is connected to exports 322, and isolates an annular sector of leaving the air-flow of prediffusion device 320.Also as example, each pipeline module 331 can pneumatically connect in downstream from burning cavity 390 radially inwardly, radially outward and enter the air flow path here, still equally occupy an annular sector of firing chamber 300.
For example, firing chamber air conduit network 330 can comprise the independent tubes module 331 for each sparger 350.Therefore, have the place of 12 spargers 350 in firing chamber, as shown in the figure, firing chamber air conduit network 330 can comprise 12 pipeline modules 331, and at this, the air-flow that leaves diffuser outlet 322 is disseminated in 12 pipeline modules 331.Equally, the group of pipeline module 331 (right, as illustrated at this) can be installed between the pillar 312 in combustion chamber shell 310 and/or be connected to here.
Accompanying drawing 4 is the isometric maps of exemplary embodiment of pipeline module of a part of prediffusion device that are connected to the firing chamber of accompanying drawing 2.Especially, show a pipeline module 331(single, not diffusion or central tube) pneumatically connect prediffusion device outlet 322, and other pipeline modules 331 are not installed.For clear and illustrate and enter each in separation bubble and flow, only show the track edges (comprising prediffusion device outlet 322) of prediffusion device 320.This view is seen downstream conventionally.
As shown in the figure, the pressurized air that leaves prediffusion device outlet 322 can be divided between pipeline module 331.Especially, air-flow can be divided by the element of prediffusion device outlet 322 and/or the element of pipeline module 331.For example, prediffusion device 320 can comprise inner leg, and it extends to prediffusion device outlet 322 and aligns with the entrance of each pipeline module 331, the separated air-flow leaving in circumferencial direction.
Equally as shown in the figure, leave between independent path that the pressurized air of prediffusion device outlet 322 can be in each pipeline module 331 or pipeline and divide.Especially, for spreading compressed-air actuated system, can comprise fluid separator 337.For example, fluid separator 337 can be constructed to separation center air-flow and leave compressed-air actuated outer air-flow and the interior air-flow from prediffusion device outlet 322, and from central gas stream, with respect to central axis 95, outer air-flow radially outward and interior air-flow are radially inside.
Central gas stream can comprise pressurized air region, has the mean velocity higher than outer and inner air-flow.The position of stand-alone separator in fluid separator 337 can be located to such an extent that the required part (central gas stream) of intercooler core of the high-speed inferior limit diffusion of radial contour is directed in the passage or pipeline of suitable constructions.Equally, the position of separator also can be located to such an extent that interior air-flow and outer air-flow are guided in the passage or pipeline that enters suitable constructions similarly, and these pipelines can be constructed to guide air-flow and/or the extra diffusion of air-flow is provided.The location of multiple separator is determined according to the airflow requirement in region and the device supplied with by the passage of a plurality of pipelines.
Fluid separator 337 is positioned at the position that approaches prediffusion device outlet 322.Especially, fluid separator 337 can be positioned at the jointing of the outlet 322 of prediffusion device and pipeline module 331.In addition, fluid separator 337 can be integrated into prediffusion device outlet 322, pipeline module 331, and/or is individual components.For example, fluid separator 338 can made with the jointing of prediffusion device outlet 322 by a plurality of entrances of pipeline module 331.As example, each pipeline module 331 can comprise the pipeline that a plurality of radial locations are adjacent one another are equally, thus in radial direction 338 and between each pipeline of pipeline module 331 separate discharge air-flow.In addition the upstream that, fluid separator 337 can extend prediffusion device outlet 322 enters prediffusion device 320.In this way, fluid separator 337 can be constructed to, and separation center air-flow is away from outer air-flow and interior air-flow, simultaneously still in prediffusion device 320.
According to a mode of execution, each pipeline module 331 can comprise Outer Tube 332, interior conduit 333 and central tube 334.Common, Outer Tube 332, interior conduit 333 and central tube 334 provide from the flow outlet of the relevant annular sector of prediffusion device 322.In addition, this arrange can guide compressed-air actuated high-speed core with its substantially higher pressure head or higher total pressure leave prediffusion device 320 and enter fuel/air mixture mixing arrangement, it can obtain the more benefit of high-energy stream.This arrange can also be configured to auxiliary control lower speed air-flow prepare cooling blast to the inner and outer wall of burning cavity 390 (also referring to accompanying drawing 3, show downstream or the outlet end of Outer Tube 332, interior conduit 333 and central tube 334, around central axis 95, distribute).
With reference to accompanying drawing 2, Outer Tube 332 can comprise Outer Tube entrance 341 and Outer Tube outlet 342.Outer Tube 332 is configured to connect, for example pneumatic prediffusion device outlet 322 that is connected to Outer Tube entrance 341 places.Outer Tube 332 is further configured to, and receives during operation the compressed-air actuated outer air-flow from prediffusion device 320, and with respect to the outer air-flow of central axis 95 guiding to firing chamber 300 radially outward part.For example, Outer Tube 332 can be constructed to the outer air-flow of relative central axis 95 guiding to the outside of burning cavity 390.As example, Outer Tube 32 can be constructed to the pneumatic outer shield 314 that is connected to of pipe outlet 342 outside equally.
Pneumaticly be connected to prediffusion device outlet 322 and can form by Outer Tube entrance 341 to prediffusion device 320 is installed, or position outer tube road entrance 341 approaches prediffusion device outlet 322 in addition.In addition, pneumatic connection can be combined the pneumatic connection of adjacent channel entrance and/or adjacent channel module 311 and be formed, and at this, the air-flow flowing out from prediffusion device outlet 322 is restricted to Outer Tube entrance 341 and adjacent channel entrance and/or adjacent channel module 331.Pneumatic connection also can be combined and is positioned at prediffusion device and exports the air-flow separator of 322 internal heat upstreams, place and form.
Outer air-flow can be defined as leaving that prediffusion device 320 approaches the outer wall 323 of prediffusion device 320 and with respect to the part of the prediffusion device outlet 322 relevant to pipeline module 331 or the low speed flow area of annular sector.Especially, outer air-flow comprises boundary layer air, associated with the outer wall 323 of prediffusion device 320.In addition, outer air-flow can comprise recovery air-flow.
For example, Outer Tube entrance 341 can be constructed to, and with respect to part or the annular sector of the prediffusion device outlet 322 relevant to pipeline module 331, receives the outermost 1/4th of the radial span of prediffusion device outlet 322.As example, Outer Tube entrance 341 can be constructed to receive the radially outermost 1/4th of the airspeed profile associated with pipeline module 331 equally.Equally as example, Outer Tube entrance 341 can be constructed to receive the radially outward part of the airspeed profile associated with pipeline module 331 lower than its mean velocity.
According to a mode of execution, Outer Tube 332 can be constructed to further spread outer air-flow.Especially, Outer Tube 332 can export from Outer Tube entrance 341 to Outer Tube 342 increases its effective flow area.Effectively the increase of flow area can be gradually, or difference is restricted to and makes during operation, and boundary layer is not from Outer Tube 332 separation.
Interior conduit 333 can comprise interior conduit entrance 343 and interior conduit outlet 344.As mentioned above, interior conduit 333 is configured to the prediffusion device outlet 322 at pneumatic connection interior conduit entrance 343 places.Interior conduit 333 is further configured to, and receives the compressed-air actuated interior air-flow from prediffusion device 320, and with respect to air-flow in central axis 95 guiding to firing chamber 300 radially inside part.For example, interior conduit 333 can be constructed to the interior air-flow of relative central axis 95 guiding to the inner side of burning cavity 390.Equally as example, interior conduit 333 can be constructed to export at interior conduit that 344 places are pneumatic is connected to interior guard shield 316.
Interior air-flow can be defined as leaving that prediffusion device 320 approaches the inwall 324 of prediffusion device 320 and with respect to the part of the prediffusion device outlet 322 relevant to pipeline module 331 or the low speed flow area of annular sector.Especially, interior air-flow comprises boundary layer air, associated with the inwall 324 of prediffusion device 320.In addition, interior air-flow can comprise recovery air-flow.
For example, interior conduit entrance 343 can be constructed to, with respect to part or the annular sector of the prediffusion device outlet 322 relevant to pipeline module 331, and interior 1/4th of the radial span of receiving prediffusion device outlet 322.As example, interior conduit entrance 343 can be constructed to receive radially interior 1/4th of the airspeed profile associated with pipeline module 331 equally.Equally as example, interior conduit entrance 343 can be constructed to receive the radially inside part of the airspeed profile associated with pipeline module 331 lower than its mean velocity.
According to a mode of execution, interior conduit 333 can be constructed to air-flow in further diffusion.Especially, interior conduit 333 can export from interior conduit entrance 343 to interior conduit 344 increases its effective flow area.Effectively the increase of flow area can be gradually, or difference is restricted to and makes during operation, and boundary layer is not from interior conduit 333 separation.
Central tube 334 can comprise central tube entrance 345 and central tube outlet 346.Central tube 334 is configured to, and by a part for the pneumatic connection prediffusion of central tube entrance 345 device outlet 322, and departs from outer wall 323 and inwall 324, and extends downstream.Central tube 334 is further configured to, and receives the compressed-air actuated middle air flow from prediffusion device outlet 322, and between interior air-flow and outer air-flow, guide middle air flow to firing chamber 300 radial center part.For example, central tube 334 can be constructed to direction center air-flow to sparger 350.Each sparger 350 of firing chamber 300 can join with independent central tube 334 and/or be integrated with it.As example, central tube 334 can be constructed to direction center air-flow to burning cavity 390 equally.Equally as example, central tube 334 can be extended to and the injector ports 392 of pneumatic connection burning cavity 390.
According to a mode of execution, central tube 334 can be segmentation.Especially, central tube 334 can be segmented into, and the first portion of central tube 334 comprises central tube entrance 345, and the second portion of central tube 334 comprises central tube outlet 346, and the first and second parts of central tube 334 pneumatically link together.For example, the central tube 334 of first portion can be pipelines element, and the central tube 334 of second portion can be formed or is integrated into here in addition by sparger 350.In addition, central tube 334 can comprise the aggregate of the element in pneumatic connection and formation continuous-flow path.As example, central tube 334 can be segmentation equally, for simplifying manufacture, simplifying and install etc.
Central gas stream can be defined as leaving prediffusion device 320 away from the outer wall 323 of prediffusion device 320 and inwall 324 the two and with respect to the part of the prediffusion device outlet 322 relevant to pipeline module 331 or the high velocity air region of annular sector.Especially, central gas stream comprises boundary layer air, associated with outer wall 323 and the inwall 324 of prediffusion device 320.In addition, central gas stream can comprise high velocity air, and it is only partially recycled air.
For example, intermediate conduit entrance 345 can be constructed to, with respect to part or the annular sector of the prediffusion device relevant to pipeline module 331 outlet 322, receive prediffusion device outlet 322 radial span centre half 1/4th.Equally as example, middle Outer Tube entrance 345 can be constructed to receive the airspeed profile associated with pipeline module 331 the soonest half.Equally as example, central tube entrance 345 can be constructed to receive with in or higher than the part of the associated airspeed profile of the pipeline module 331 of its mean velocity.
According to a mode of execution, central tube 334 can be constructed to further dispersal center air-flow.Especially, central tube 334 can increase its effective flow area at central tube entrance 345 between central tube outlet 346.Effectively the increase of flow area can be gradually, or difference is restricted to and makes during operation, and boundary layer is not from interior conduit 333 separation.According to a mode of execution, central tube 334 can increase from central tube entrance 345 to predetermined downstream position its effective flow region, and the flow region of remaining valid is subsequently constant until central tube outlet 346.
According to a mode of execution, central tube 334 changes shape at central tube entrance 345 between central tube outlet 346.Especially, central tube 334 can have complicated structure, from the quadrilateral air-flow cross section of central tube entrance 345, be smoothly transitioned into circular air-flow cross section that central tube exports 346 places (referring to accompanying drawing 4, the isometric view of pipeline module 331, shows the smooth-going transition between central tube entrance 345 and central tube outlet 345).According to a mode of execution, central tube 334 can keep stable effective flow area in transition.According to another mode of execution, central tube 334 can continue to increase its effective flow area to circular air-flow cross section from central tube entrance 345, is configured to the diffuser for central gas stream as above.
According to a mode of execution, pipeline module 331 may further include intermediate conduit 335.Intermediate conduit 335 can comprise intermediate conduit entrance 347 and intermediate conduit outlet 348.In addition, intermediate conduit 335 can have a wall with at least one of Outer Tube 332, interior conduit 333 and central tube 334.For example, the outer surface of central tube 334 (with respect to sparger axle 359) can form the inwall (with respect to sparger axle 359) of intermediate conduit 335.
Intermediate conduit 335 is configured at least one discharge air from Outer Tube 332, interior conduit 333 and central tube 334 by intermediate conduit entrance 347.For example, intermediate conduit entrance 347 can comprise one or more exhaust ports (or other through hole) through central tube 334 outer walls, and outer wall is with respect to sparger axle 359.For example, intermediate conduit entrance 347 can comprise the exhaust port (or other through hole) of one or more inwalls through Outer Tube 332 and/or interior conduit 333, and inwall is also with respect to sparger axle 359.
Intermediate conduit 335 is further configured to directing exhaust gas to the hot guard shield 393 of a part, for example dome of burning cavity 390, in order to cooling.Especially, burning cavity 390 can be cooling in a conventional manner perpendicular to the part of the outlet (lining dome) of sparger 350, for example, use tension insulating panel, and it forms the part of the hot guard shield 393 of dome and around injector ports 392.For example, intermediate conduit outlet 348 can be constructed to make exhaust to impinge upon on the hot guard shield 393 of dome in order to cooling object.
According to a mode of execution, intermediate conduit 335 can be had a loaded shape.Especially, intermediate conduit 335 can change at circular cross section (quadrature sparger axle 359) substantially between polygonal cross section.For example and as shown in the figure, at upstream extremity (with respect to sparger axle 359), intermediate conduit 335 can have and concentric and integrated round-shaped of central tube 334, and at downstream (with respect to sparger axle 359), intermediate conduit 335 can have polygonal shape substantially, and it is independent of and departs from intermediate conduit 335.Intermediate conduit 335 can smooth-going transition between two shapes.Equally, intermediate conduit 335 can change between single cavity flow path and two or multi-cavity flow path, and for example, discontinuous place is inserted or produced in addition to other structure in flow path.
According to a mode of execution, pipeline module 331 can further comprise axial mixer (" axially eddy generator " or " blade mixer ").Especially, axially mixer 336 is configured to axially receive compressed-air actuated central gas stream (with respect to sparger axle 359, and receiving as faced toward radially).In addition, axially mixer 336 can form the inwall of central tube 334, and compressed-air actuated central gas stream can be moved in the annular flow path of the side around mixer.
Axially mixer 336 can further be configured to, the compressed-air actuated central gas stream that guiding receives, and the fuel flow providing with sparger 350 on the opposite side of the annular space around mixer mixes, and use the fluid function mechanism in outlet port to produce counterrotating whirlpool to (seeing accompanying drawing 5).In addition, central tube 334 can be constructed to reduce loss, makes central gas stream and fuel flow 20 have maximum speed discrepancy, further increases by two kinds of shearings between fluid and thereby mixes.In addition, axially mixer 336 can be constructed to make based on entering burning cavity 390 initially mixing air and fuel.
According to a mode of execution, axially mixer 336 can be constructed to circumference form.In this structure, axially mixer 336 can adapt to existing geometrical shape and the layout of sparger 350 and remaining pipes module 331.For example and as shown in the figure, axially mixer 336 can comprise blade mixer, comprises a plurality of blades 349 that distribute around sparger axle 359 circle alternates.Equally as example, blade mixer can substantially cylindrical or other smooth-going round-shaped with and the fluctuating blade shape of composite character between smooth-going transition.
According to a mode of execution, circumferential vanes mixer can be arranged to such an extent that make it axially around central tube 334, and it can be constant or concentrated effective flow region, supports central gas stream contact and keeps in touch to the surface of blade 349.According to a mode of execution, this central tube 334 can upwards increase its effective flow region from central tube entrance 345 to blade 349, and the flow region of remaining valid is subsequently constant until central tube outlet 346.Alternatively, central tube 334 can upwards increase its effective flow region from central tube entrance 345 to blade 349, and reduces subsequently the effective flow region through blade 349.
Accompanying drawing 5 is the isometric maps that form the right lobate mixer of plane of whirlpool.For the auxiliary axial mixer 336 of describing above, show the plane view of blade mixer.Therefore, plane blade mixer 836 is configured to, and from forming whirlpool, to 813 machinery and viscous force, the two interaction produces and mixes.As shown in the figure, the air-flow of plane blade mixer 836 guiding first fluids 811 and second fluid 812 is through the downstream of plane blade mixer 836, and it produces high level and shears between two fluid stream, and produces the whirlpool for mixing.The high shearing air-flow of these guiding produced mix two fluids whirlpool to 813.Every pair replaces a pair of whirlpool of blade 849 generation, and it interweaves to 813 along with whirlpool substantially, closely mixes the first and second fluids 811,812.
With reference to accompanying drawing 2 and accompanying drawing 3, axially mixer 336 is conceptive is similar to the plane blade mixer 836 shown in accompanying drawing 5.Yet, at this, as axial blade mixer, axially mixer 336 guiding fuel flows and air stream pass the downstream of axial mixer 336 in radial direction, it produces similarly high level and shears between two fluid stream, and it produces the eddy effect for mixing.The high shearing air-flow of these guiding has also produced the whirlpool pair that mixes two fluids.Be similar to the blade 849 of accompanying drawing 5, at this, axially every pair in mixer 336 alternately blade 349 produced a pair of whirlpool, it interweaves subsequently, fuel combination and air be in order to combustion reaction closely.
With reference to accompanying drawing 2, according to another mode of execution, axially mixer 336 can be constructed to make the composite character (for example, blade 349) of axial mixer 336 from burning cavity 390, to be axially positioned at upstream with respect to sparger axle 359.Especially, composite character can be recessed in any other upstream, protected zone of sparger 350, central tube 334 and/or burning cavity 390.For example and as shown in the figure, axially the composite character (being represented by the gable in its downstream) of mixer 336 can extend upwardly to the opening that injection tip 392(enters burning cavity 390).As example, axially mixer 336 can be recessed in the downstream (with respect to sparger axle 359) of injector ports 392 equally, and locates to such an extent that make to present minimum aspect ratio (downstream that for example, is parallel to 359 operations of sparger axle) to hot gas.In addition, axially mixer 336 can be recessed, makes the premixing in center tube 334 before leaving sparger of air and fuel.
According to another mode of execution, pipeline module 331 can be constructed to, and makes the air that leaves intermediate conduit 335 provide Additional Protection to axial mixer 336.Especially, intermediate conduit outlet 348 and/or the hot guard shield 393 of dome can be constructed to make cooling-air in the radially inwardly discharge of edge of clashing into dome hot guard shield 393 after around axial mixer 336.In addition, the cooling-air of discharge can for example, increase air-flow with mixed organization (, the air-treatment blade of the blade mixer) alignment of axial mixer 336, and thereby increases the shearing between fuel and air stream.
According to a mode of execution, pipeline module 331 can be discontinuous, in order to manufacture or other design requirement.Especially, Outer Tube 332, interior conduit 333, central tube 334, intermediate conduit 335 and axially in mixer 336 one or more can with other component integration.For example and as shown in the figure, support arm 352 can pass through Outer Tube 332, interior conduit 333, central tube 334, intermediate conduit 335 and axial mixer 336, in order to locate sparger on sparger axle 359.Equally as example, the first portion of pipeline module 331 is can be with prediffusion device 320 integrated or be fixed in addition here, and the second portion of pipeline module 331 can be integrated with sparger 350 simultaneously.
According to an alternate embodiments, the pipeline of each pipeline module 331 can be with above-described contrary.Especially, the inner and outer wall that the required part of compressed-air actuated high-speed core can be transported to burning cavity 390 is in order to cooling.This setting also can carry low speed flow (approaching the wall of prediffusion device 320) to enter burning cavity 390.
In order to illustrate, interior and Outer Tube can have the entrance that joins with prediffusion device 320 of being configured to as above, but it is incorporated into and is configured to guide the interior and outer air-flow of combination to the independent tubes of burning cavity 390.In addition, central tube can have the entrance that joins with prediffusion device 320 of being configured to as above, but it is divided into two independent tubes subsequently.Two independent tubes can be constructed to guide pressurized air respectively to outer shield 314 and interior guard shield 316, and are similar to Outer Tube 332 as above and interior conduit 333.In addition, guide the independent tubes of this prostheses air-flow can there is the cross-section area increasing gradually and at section start, on the wall at them, only have any or there is no boundary layer, act as and arrange the diffuser stage, and reduce speed and the dynamic pressure head of prostheses air-flow.Therefore, prostheses air-flow can be discharged in lining guard shield subsequently, have substantially reduce dump loss, lower speed (recovery more completely).
Commercial Application
The utility model is conventionally in order to gas turbine engine and the gas turbine engine with prediffusion device.The mode of execution of describing does not limit the use in conjunction with the gas turbine engine of particular type, but also can be used to fixing or motion combustion gas or turbogenerator or its any distortion.The gas turbine engine of the present embodiment can be suitable for very many-sided commercial Application, such as but not limited to oil and natural gas industry (comprising transportation, collection, storage, recovery and the lifting of oil and natural gas), power industry, aerospace and transportation industry etc.In addition, the utility model also can be used to furnace applications.
Conventionally, the mode of execution of current disclosed system is for spreading pressurized air in firing chamber, it is applicable to use, operation, maintenance, repairing and the improvement of gas turbine engine, and can be used to improve performance and efficiency, minimizing maintenance and repair and/or reduction expense.In addition, the mode of execution of current disclosed system for spreading pressurized air in firing chamber, can be used in gas turbine engine any stage in working life, from being designed into prototype and manufacture first and will end-of-life.Therefore, for spread compressed-air actuated system in firing chamber, can be used as upgrading or strengthening existing gas turbine engine, as preventative measurement, or even in response to an event.Correct especially, current disclosedly can be installed in the firing chamber with the interface identical with other firing chamber for spread compressed-air actuated system in firing chamber, thus can exchange with the firing chamber of early stage type.
In use, for spread compressed-air actuated system in firing chamber, in firing chamber, formed the piping network that reduces loss.The front end of pipeline or separator is located to such an extent that make pressurized air leave the high speed of the radial contour of prediffusion device, the required part of the prostheses of bottom line diffusion is directed into firing chamber piping network.Guide the independent tubes of a prostheses air-flow can there is the cross-section area of gradual change, and at section start, on the wall at them, only have any or there is no boundary layer, act as and arrange the diffuser stage, and reduce speed and the dynamic pressure head of prostheses air-flow.This prostheses air-flow can be discharged in sparger subsequently, have substantially reduce dump loss, lower speed (recovery more completely).Alternatively, this prostheses air-flow can be discharged for cooling around burning cavity subsequently.
Model utility has formerly been described multiple technologies and has been incorporated into the unique texture for gas turbine combustion system, has presented the mixing ability of low pressure loss and enhancing.Especially, be used for having spread compressed-air actuated system in combination in firing chamber target and used separation, low loss pipeline, supplement diffusion and axially mix, it can bring the diffuser recyclability of raising, the lower pressure loss, the mixing of enhancing and/or lower discharge.In addition, for spread compressed-air actuated system in firing chamber, can be provided for integrated system, manage fuel and air mixture and prepare, re-use the cooling blast of consumption and increase mixing, and shorten potentially whole system length.By eliminate current be used in tradition in combustion system high loss mixing arrangement and be replaced by low pressure lose more effective mixing arrangement, by the corresponding increase of whole system efficiency, realize the decline of whole system pressure.
By combining above-mentioned technology, the high composite rate blade mixer of improved diffuser recyclability and low loss can mergedly provide improved fuel-air management system.In combustion system, the combination of these technology can be suitable for available engine, particularly industrial nature, because they are often provided for the adequate space of other hardware and do not need to stick to the length of aeroengine and heavily quantitative limitation.
Detailed description is above in fact only example, and is not intended to limit the utility model or application of the present utility model or use.The mode of execution of describing is also not restricted to the use in conjunction with the gas turbine engine of particular type.Therefore, although the present embodiment is indicated and is described as for fixing gas turbine engine for the convenience of explaining, will will be appreciated that, it can be used in the gas turbine engine and multiple other system and environment of multiple other type.In addition, be not intended to here be retrained by any theory representing in aforementioned part.It will also be appreciated that schematic diagram can comprise size and the graphic representation of expansion, better illustrate shownly with reference to project, and do not consider restriction, unless so clear statement.
Claims (10)
1. a gas turbine engine (100) with central axis (95), is characterized in that, comprising:
Compressor (200);
Prediffusion device (320), is pneumatically connected to compressor (200), and described prediffusion device (320) comprises the outlet of prediffusion device (322), outer wall (323) and inwall (324); And
For the system of blended fuel oil and air, described system comprises:
Fluid separator (337), be positioned at the position of closing on prediffusion device outlet (322), and be configured to shunting from the pressurized air of prediffusion device outlet (322), by central gas stream and outer air-flow and interior airflow breakaway, central gas stream has than outer air-flow and the higher mean velocity of interior air-flow;
Central tube (334), comprise central tube entrance (345) and central tube outlet (346), described central tube (334) is configured to locate pneumatically to connect at central tube entrance (345) part that prediffusion device exports (322), this part departs from from outer wall (323) and inwall (324), and central tube (334) receives from the central gas stream of prediffusion device outlet (322) and the burning cavity (390) that direction center air-flow enters gas turbine engine (100); And
Axially mixer (336), is arranged in central tube (334), and described axial mixer (336) is configured to the fuel mix that direction center air-flow and sparger (350) provide.
2. the gas turbine engine (100) with central axis (95) as claimed in claim 1, is characterized in that, effective flow region of central tube (334) increases between central tube entrance (345) and central tube outlet (346).
3. the gas turbine engine (100) with central axis (95) as claimed in claim 1, it is characterized in that, described axial mixer (336) comprises blade mixer, and described blade mixer has a plurality of alternately blades (349) around sparger axle (359) circle distribution.
4. the gas turbine engine (100) with central axis (95) as claimed in claim 3, is characterized in that, effective flow region of central tube (334) is in central tube entrance (345) and a plurality of alternately increase between blade (349); Effective flow region of central tube (334) remains unchanged or reduces effective flow region between a plurality of alternately blades (349) and central tube outlet (346).
5. the gas turbine engine with central axis (95) (100) as described in any one in claim 1 to 4, it is characterized in that, described central tube (334) is configured to extend to and pneumatically connect the burning cavity (390) of gas turbine engine (100).
6. the gas turbine engine with central axis (95) (100) as described in any one in claim 1 to 4, it is characterized in that, described axial mixer (336) is configured to direction center air-flow to be mixed in the burning cavity (390) of gas turbine engine (100) with fuel.
7. the gas turbine engine with central axis (95) (100) as described in any one in claim 1 to 4, it is characterized in that, described axial mixer (336) is configured to direction center air-flow and fuel in the combined upstream of the burning cavity (390) of gas turbine engine (100).
8. the gas turbine engine with central axis (95) (100) as described in any one in claim 1 to 4, it is characterized in that, described fluid separator (337) extends into prediffusion device (320) in the upstream of prediffusion device outlet (322), and fluid separator (337) in prediffusion device (320) by central gas stream and outer air-flow and interior airflow breakaway.
9. the gas turbine engine with central axis (95) (100) as described in any one in claim 1 to 4, it is characterized in that, described central tube (334) is configured so that central gas stream only comprises the pressurized air that has certain speed, leaves prediffusion device outlet (322) along radial velocity profile, and this speed is more than or equal to the whole compressed-air actuated mean velocity that leaves prediffusion device outlet (322) along radial velocity profile.
10. the gas turbine engine with central axis (95) (100) as described in any one in claim 1 to 4, it is characterized in that, also comprise: intermediate conduit (335), described intermediate conduit (335) comprises intermediate conduit entrance (347) and intermediate conduit outlet (348), described intermediate conduit (335) is configured to discharge the air from central tube (334) by intermediate conduit entrance (347), and guiding exhaust air to burning cavity (390), in order to cooling.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/889871 | 2013-05-08 | ||
| US13/889,871 US20140331678A1 (en) | 2013-05-08 | 2013-05-08 | System for distributing compressed air in a combustor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203835539U true CN203835539U (en) | 2014-09-17 |
Family
ID=51513389
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420230761.1U Active CN203835539U (en) | 2013-05-08 | 2014-05-07 | Gas turbine engine with central axis |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US20140331678A1 (en) |
| CN (1) | CN203835539U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107100682A (en) * | 2016-02-22 | 2017-08-29 | 通用电气公司 | The system and method that original place for gas-turbine unit shell space is repaired |
| CN110268197A (en) * | 2017-02-08 | 2019-09-20 | 西门子股份公司 | Minimize the method that the power on turbo blade is acted in particular frequency range |
| CN111316041A (en) * | 2017-09-05 | 2020-06-19 | 西门子股份公司 | Gas turbine combustor assembly with trapped vortex feature |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE112017002620B4 (en) * | 2016-05-23 | 2023-01-26 | Mitsubishi Heavy Industries, Ltd. | combustor and gas turbine |
| US10502425B2 (en) * | 2016-06-03 | 2019-12-10 | General Electric Company | Contoured shroud swirling pre-mix fuel injector assembly |
| JP6772868B2 (en) * | 2017-01-31 | 2020-10-21 | 株式会社Ihi | Combustion equipment and gas turbine |
| CN109373091B (en) * | 2018-10-30 | 2024-01-16 | 中国船舶重工集团公司第七一九研究所 | Pipeline split-flow device |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| NL74196C (en) * | 1947-08-11 | |||
| US2602292A (en) * | 1951-03-31 | 1952-07-08 | Gen Electric | Fuel-air mixing device |
| US3780529A (en) * | 1971-08-05 | 1973-12-25 | Gen Motors Corp | Combustion apparatus |
| US4058977A (en) * | 1974-12-18 | 1977-11-22 | United Technologies Corporation | Low emission combustion chamber |
| US5142858A (en) * | 1990-11-21 | 1992-09-01 | General Electric Company | Compact flameholder type combustor which is staged to reduce emissions |
| US5235813A (en) * | 1990-12-24 | 1993-08-17 | United Technologies Corporation | Mechanism for controlling the rate of mixing in combusting flows |
| CA2089272C (en) * | 1992-03-23 | 2002-09-03 | James Norman Reinhold, Jr. | Impact resistant combustor |
| US5619855A (en) * | 1995-06-07 | 1997-04-15 | General Electric Company | High inlet mach combustor for gas turbine engine |
-
2013
- 2013-05-08 US US13/889,871 patent/US20140331678A1/en not_active Abandoned
-
2014
- 2014-05-07 CN CN201420230761.1U patent/CN203835539U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107100682A (en) * | 2016-02-22 | 2017-08-29 | 通用电气公司 | The system and method that original place for gas-turbine unit shell space is repaired |
| CN107100682B (en) * | 2016-02-22 | 2022-01-07 | 通用电气公司 | System and method for in situ repair of gas turbine engine casing voids |
| CN110268197A (en) * | 2017-02-08 | 2019-09-20 | 西门子股份公司 | Minimize the method that the power on turbo blade is acted in particular frequency range |
| CN110268197B (en) * | 2017-02-08 | 2020-08-14 | 西门子股份公司 | Method for minimizing forces acting on turbine blades in a specific frequency range |
| CN111316041A (en) * | 2017-09-05 | 2020-06-19 | 西门子股份公司 | Gas turbine combustor assembly with trapped vortex feature |
| US11371710B2 (en) | 2017-09-05 | 2022-06-28 | Siemens Energy Global GmbH & Co. KG | Gas turbine combustor assembly with a trapped vortex feature |
Also Published As
| Publication number | Publication date |
|---|---|
| US20140331678A1 (en) | 2014-11-13 |
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