CN114076324B - Combustion chamber capable of automatically adjusting mixed air intake - Google Patents
Combustion chamber capable of automatically adjusting mixed air intake Download PDFInfo
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- CN114076324B CN114076324B CN202210057571.3A CN202210057571A CN114076324B CN 114076324 B CN114076324 B CN 114076324B CN 202210057571 A CN202210057571 A CN 202210057571A CN 114076324 B CN114076324 B CN 114076324B
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- mixing
- combustion chamber
- flame tube
- compressor
- guide vane
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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
- F23R3/26—Controlling the air flow
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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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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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 invention provides a combustion chamber capable of automatically adjusting mixed intake, which is connected with a final stage guide vane of a gas compressor and comprises: the diffuser is arranged at the downstream of the last stage guide vane of the gas compressor; and the inlet end of the mixing gas inlet assembly is communicated with the last stage guide vane of the compressor, the outlet end of the mixing gas inlet assembly is communicated with the flame tube, and the mixing gas inlet assembly can directly introduce gas at the last stage guide vane of the compressor into the flame tube. The invention has the beneficial effects that the embodiment realizes partial flow division of the inlet flow of the combustion chamber by arranging the mixing air inlet assembly, and reduces the Mach number of the inlet of the combustion chamber, thereby reducing the total pressure loss of the diffuser, and improving the total pressure recovery coefficient and the combustion efficiency of the combustion chamber. Meanwhile, the active regulation and control of the outlet temperature field of the combustion chamber are realized, the distribution quality of the outlet temperature field is improved, and the service life of the turbine is further prolonged.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to a combustion chamber capable of automatically adjusting mixed air intake.
Background
The combustor, one of the three largest core components of a gas turbine engine, has reached a fairly high level of basic performance and structure. However, for modern high performance gas turbine engine combustors, a number of challenges and challenges remain, and the development and application of new concepts, new structures, new materials, and new processes is the source of the continuing progress.
Modern civil gas turbine engines develop towards turbofan engines with large bypass ratio, the requirements of low cost, low pollution, low noise and high reliability are continuously improved, and various large aircraft engine companies are researching on reduction of pollution emission and fuel consumption of combustion chambers as important subjects. Since 1994, GE aeroengine companies have employed several improved low pollution combustors on new aero gas turbine engines, including CFM56-5B and-7B staged lean dual annular chamber combustors (DAC), CF6-80 low pollution single annular chamber combustors (LEC), GE90DAC II combustors, and the like. Research on the related art relating to low pollutant emissions and low fuel consumption in industrial gas turbine power plants has also made great progress.
Modern high-performance military fighter generally adopts a small-bypass-ratio turbofan engine, in order to realize high-speed maneuvering, the thrust-weight ratio requirement of the engine is obviously improved, the circulation parameters of the engine are improved accordingly, and for a combustion chamber, the combustion efficiency, temperature rise and outlet temperature distribution indexes of the combustion chamber are improved continuously, so that head cyclone oil-gas mixing and efficient mixing in a flame tube need to be enhanced continuously to obtain high combustion efficiency and uniform outlet temperature distribution, for this reason, Russian 5 th generation (equivalent to Western 4 th generation) fighter engine AL-41F adopts an annular combustion chamber adopting efficient mixing and cooling technology, and a replacement engine F136 of an American F-35 combined attack machine adopts an air atomizing nozzle with double cyclones or a premixing nozzle scheme with cyclones.
Whether military, commercial, or industrial gas turbine engines, the overall pressure recovery coefficient, combustion efficiency, and exit temperature field distribution coefficient of the combustor are important indicators of many performance indicators for combustors. Relevant researches show that the total pressure loss of the combustion chamber directly influences the fuel consumption rate of an engine, the fuel consumption rate can be increased by about 1% for each 1% increase, because the larger the total pressure loss of the combustion chamber is, the lower the total pressure recovery coefficient is, the lower the combustion efficiency is, and especially the total pressure loss of a diffuser which accounts for a larger part of the total pressure loss of the combustion chamber is useless, so the smaller the total pressure loss of the diffuser is, the better the total pressure loss of the diffuser is.
The combustor exit temperature distribution coefficient includes two indicators, OTDF and RTDF. With significant increases in combustor temperature, the OTDF values, if slightly increased, can dramatically increase the hot spot temperature at the combustor exit, which can create significant difficulties and challenges in the design of turbine blades.
Disclosure of Invention
The invention provides a combustion chamber capable of automatically adjusting mixed intake air, thereby achieving the purposes of reducing the total pressure loss of a diffuser, improving the combustion efficiency of the combustion chamber and improving the distribution quality of the temperature field at the outlet of the combustion chamber.
The technical scheme adopted by the invention for solving the technical problems is as follows: a combustion chamber capable of automatically adjusting mixed air inflow is connected with a last stage guide vane of a compressor, and comprises: the diffuser is arranged at the downstream of the last stage guide vane of the gas compressor; and the inlet end of the mixing gas inlet assembly is communicated with the last stage guide vane of the compressor, the outlet end of the mixing gas inlet assembly is communicated with the flame tube, and the mixing gas inlet assembly can directly introduce gas at the last stage guide vane of the compressor into the flame tube.
Further, the blending air intake assembly comprises: the inlet end of the air guide pipe is communicated with a final stage guide vane of the compressor; the inlet end of the intermediate communicating pipe is communicated with the outlet end of the air guide pipe; the inlet end of the strong mixing conduit is communicated with the outlet end of the intermediate communicating pipe, and the outlet end of the strong mixing conduit is communicated with the flame tube; and the self-adaptive adjusting device is arranged between the outlet end of the air guide pipe and the inlet end of the intermediate communicating pipe and can adjust the flow of the mixing air inlet assembly.
Further, the adaptive adjusting device comprises: the throttle valve is arranged at the inlet end of the intermediate communicating pipe; and the driving control assembly is connected with the throttle valve and can control the opening of the throttle valve.
Further, the drive control assembly includes: the data interaction machine is used for carrying out communication signal interaction with the upper end control assembly; the integrated processor is connected with the data interaction machine and used for receiving and processing the communication signals and sending control signals according to the communication signals; the synchronous motor is connected with the integrated processor and can adjust the rotating speed and the rotating direction according to the control signal; and the gear set transmission device is connected with the synchronous motor and the throttle valve, and the synchronous motor can adjust the opening of the throttle valve through the gear set transmission device.
Furthermore, the throttle valve is of a flat plate type, a blade grid type or a rotary blade type.
Furthermore, a plurality of turbulence columns arranged at intervals are arranged on the inner wall of the strong mixing guide pipe.
Further, the outer wall of the strong mixing guide pipe is provided with a plurality of sealing grooves, and a sealing washer is arranged in each sealing groove.
Furthermore, the diffuser is connected with the inner casing, the outer wall of the intermediate communicating pipe is provided with a flange edge, and the flange edge is fixedly connected with the inner casing in a bolt connection mode.
Furthermore, the flame tube comprises a flame tube inner ring and a flame tube outer ring, an inner ring mixing hole is formed in the flame tube inner ring, an outer ring mixing hole is formed in the flame tube outer ring, and the outlet end of the mixing air inlet assembly is connected with the inner ring mixing hole and/or the outer ring mixing hole.
Further, the type of combustion chamber capable of automatically adjusting the blended intake air is an axial flow, baffling or backflow combustion chamber.
The invention has the beneficial effects that the embodiment realizes partial flow division of the inlet flow of the combustion chamber by arranging the mixing air inlet assembly, reduces the Mach number of the inlet of the combustion chamber, thereby reducing the total pressure loss of the diffuser, improving the total pressure recovery coefficient and the combustion efficiency of the combustion chamber, and simultaneously realizes the active regulation and control of the outlet temperature field of the combustion chamber, improving the distribution quality of the outlet temperature field and further prolonging the service life of the turbine by adaptively regulating the flow entering the mixing holes.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a schematic diagram of an adaptive control device;
FIG. 3 is a schematic diagram of a strong blending conduit configuration.
Reference numbers in the figures: 11. last stage guide vanes of the gas compressor; 12. a bleed pipe; 13. a combustion chamber inlet; 14. a diffuser; 15. an adaptive adjustment means; 16. an intermediate communicating pipe; 17. a strong blending conduit; 18. a flame tube; 19. installing a bolt; 20. an inner case; 21. an integrated processor; 22. a synchronous motor; 23. a gear train transmission; 24. a throttle valve; 25. a turbulence column; 26. a sealing gasket; 27. an inner ring runner; 28. an inner ring turbine bleed hole; 29. an outer ring mixing hole; 30. a combustion chamber outlet; 31. and (4) a data interaction machine.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1 to 3, the embodiment of the invention provides a combustion chamber capable of automatically adjusting mixed air, which is connected with a final stage guide vane 11 of a compressor and comprises a flame tube 18, a diffuser 14 and a mixed air inlet assembly. The structure and the position relation of the flame tube 18 and the diffuser 14 are the same as those of the prior art, wherein the diffuser 14 is arranged at the downstream of the final stage guide vane 11 of the compressor; the inlet end of the mixing gas inlet assembly is communicated with the compressor last stage guide vane 11, the outlet end of the mixing gas inlet assembly is communicated with the flame tube 18, and the mixing gas inlet assembly can directly introduce gas at the compressor last stage guide vane 11 into the flame tube 18.
The embodiment has realized the partial reposition of redundant personnel of combustor import flow through setting up the mixing subassembly that admits air, and combustor import mach number reduces to reduced the total pressure loss of diffuser 14, improved the total pressure recovery coefficient and the combustion efficiency of combustor.
Specifically, the blending air intake assembly includes a bleed air pipe 12, an intermediate communicating pipe 16, a strong blending conduit 17, and an adaptive adjusting device 15. The inlet end of the bleed air pipe 12 is communicated with the last stage guide vane 11 of the compressor; the inlet end of the intermediate communicating pipe 16 is communicated with the outlet end of the bleed air pipe 12; the inlet end of the strong mixing conduit 17 is communicated with the outlet end of the intermediate communicating pipe 16, and the outlet end of the strong mixing conduit 17 is communicated with the flame tube 18; an adaptive adjusting device 15 is arranged between the outlet end of the bleed air pipe 12 and the inlet end of the intermediate communicating pipe 16, and the adaptive adjusting device 15 can adjust the flow of the blending air intake component.
The mixing air inlet assembly can realize intelligent regulation and control of local (single head or a plurality of heads) and whole-ring outlet temperature field distribution of the combustion chamber, and the service life of the turbine is prolonged.
As shown in fig. 1, the combustion chamber capable of automatically adjusting the blended intake air includes a bleed air pipe 12, a diffuser 14, an adaptive adjusting device 15, an intermediate communicating pipe 16, a strong blending guide pipe 17, a liner inner ring, an inner casing 20, an inner ring turbine bleed air hole 28, an outer ring blending hole 29, and the like, wherein an inner ring flow passage 27 is formed between the liner inner ring and the inner casing 20. The working condition of the combustor is that a part of high-pressure air from the section of the last stage guide vane 11 of the compressor flows into the bleed air pipe 12, then the part of high-pressure air flows through the adaptive adjusting device 15 positioned at the connection part of the rear end of the bleed air pipe 12 and the intermediate communicating pipe 16, the flow rate of the part of high-pressure air flows is adaptively adjusted in the adaptive adjusting device 15, then the part of high-pressure air finally enters the flame tube 18 from the strong mixing guide pipe 17 through the intermediate communicating pipe 16, the other part of high-pressure air flows into the flame tube 18 of the combustor from the combustor inlet 13 through the diffuser 14, and the adjustment of the temperature field of the combustor outlet 30 is realized by controlling the flow rate of the high-pressure air flowing into the bleed air pipe 12 through the adaptive adjusting device 15 under different working conditions so as to control the penetration depth and the mixing effect of the mixing jet flow required under different working conditions.
It should be noted that the diffuser 14 is connected to the inner casing 20, and the outer wall of the intermediate communication pipe 16 is provided with a flange edge, and the flange edge is fixedly connected to the inner casing 20 through the mounting bolt 19.
Further, the flame tube 18 comprises a flame tube inner ring and a flame tube outer ring, an inner ring mixing hole is formed in the flame tube inner ring, an outer ring mixing hole 29 is formed in the flame tube outer ring, and the outlet end of the mixing air inlet assembly is connected with the inner ring mixing hole and/or the outer ring mixing hole 29.
In the embodiment, the number of the mixing air inlet assemblies may be multiple, which corresponds to the number of the inner ring mixing holes and/or the outer ring mixing holes 29, and the multiple mixing air inlet assemblies should be uniformly distributed along the circumferential direction.
As shown in fig. 1 and 2, the adaptive adjustment device 15 includes a throttle valve 24 and a drive control component. A throttle valve 24 is provided at the inlet end of the intermediate communicating pipe 16; the drive control assembly is connected with the throttle valve 24 and can control the opening size of the throttle valve 24.
In this embodiment, the drive control assembly can adjust the throttle valve 24, and during operation, the drive control assembly can adjust the opening of the throttle valve 24 according to a superior control signal, so as to control the opening of a pipeline formed by the bleed air pipe 12, the intermediate communicating pipe 16 and the strong mixing conduit 17 in the mixing air intake assembly.
Preferably, the drive control assembly includes a data interactor 31, an integrated processor 21, a synchronous motor 22 and a gear train transmission 23. The data interaction machine 31 is used for carrying out communication signal interaction with the upper end control assembly; the integrated processor 21 is connected with the data interaction machine 31 and used for receiving and processing the communication signal and sending a control signal according to the communication signal; the synchronous motor 22 is connected with the integrated processor 21, and the synchronous motor 22 can adjust the rotating speed and the rotating direction according to the control signal; the gear set transmission device 23 is connected with both the synchronous motor 22 and the throttle valve 24, and the synchronous motor 22 can adjust the opening degree of the throttle valve 24 through the gear set transmission device 23.
When in work: the data interaction machine 31 receives the distribution data of the outlet temperature field of the combustion chamber in real time, then transmits the data to the integrated processor 21 for operation, the integrated processor 21 makes an optimization judgment on whether the outlet temperature field needs to be optimized or not, and issues a signal instruction for maintaining the rotating speed of the existing motor or the optimized motor rotating speed to the synchronous motor 22, the synchronous motor 22 controls the opening of the throttle valve 24 through the gear set transmission device 23, so that the self-adaptive regulation of the mixing flow of the downstream strong mixing guide pipe 17 is realized, and the flow regulation range of the throttle valve 24 accounts for 3% -15% of the air inlet flow of the flame tube of the combustion chamber.
It should be noted that the throttle valve 24 may be a flat plate type, a cascade type, or a rotary vane type.
As shown in fig. 1 and 3, the inner wall of the middle portion of the strong mixing conduit 17 is provided with a plurality of turbulence columns 25, and the lower end thereof is provided with a plurality of sealing grooves, and sealing gaskets 26 are mounted in the sealing grooves and used for sealing connection with the tail end of the intermediate communicating pipe 16. The number of rows of turbulence columns 25 is 3-5, 6-12 turbulence columns are uniformly distributed in each row in the circumferential direction, and the adjacent upper row and the lower row are arranged side by side or in a staggered manner, so that the turbulence degree of air flow flowing into the strong mixing guide pipe 17 is enhanced, and the mixing effect of mixing jet flow is improved. The airflow flowing into the strong mixing guide pipe 17 forms vortexes with different sizes at the downstream after passing through the turbulence column 25, and the mixing effect between the mixing jet flow and the high-temperature fuel gas is further enhanced.
The type of the combustion chamber capable of automatically adjusting the mixed air in the embodiment is an axial flow, baffling or backflow combustion chamber.
From the above description, it can be seen that the above-described embodiments of the present invention achieve the following technical effects:
1. partial flow distribution of the inlet flow of the combustion chamber is realized, and the Mach number of the inlet of the combustion chamber is reduced, so that the total pressure loss of the diffuser is reduced, and the total pressure recovery coefficient and the combustion efficiency of the combustion chamber are improved.
2. The intelligent regulation and control of the temperature field distribution of the local (single head or a plurality of heads) and the whole-ring outlet of the combustion chamber can be realized, and the service life of the turbine is prolonged.
3. The closed inner ring mixing air inlet pipeline can obviously improve the mixing jet flow pressure difference, is favorable for improving the penetration depth and the mixing effect of the mixing jet flow, and the turbulence degree and the mixing effect of the inner ring mixing jet flow are further improved by the design of a plurality of rows of turbulence columns in the strong mixing guide pipe.
4. Meanwhile, the interference and influence of the cooling bleed air of the turbine at the outlet of the annular flow passage in the combustion chamber on the flow field at the mixing hole of the inner ring in the traditional scheme can be reduced, and the flow stability of the mixing jet flow of the inner ring under different working conditions is improved.
It should be understood that the above description is only exemplary of the invention, and is not intended to limit the scope of the invention, so that the replacement of equivalent elements or equivalent changes and modifications made in the present invention should be included within the scope of the present invention. In addition, the technical features, the technical schemes and the technical schemes can be freely combined and used.
Claims (6)
1. A combustion chamber capable of automatically adjusting blended intake air, connected to the last stage guide vane (11) of a compressor, characterized in that the combustion chamber capable of automatically adjusting blended intake air comprises:
the flame tube (18) and the diffuser (14), the diffuser (14) is arranged at the downstream of the last stage guide vane (11) of the compressor;
the inlet end of the mixing gas inlet assembly is communicated with the compressor last stage guide vane (11), the outlet end of the mixing gas inlet assembly is communicated with the flame tube (18), and the mixing gas inlet assembly can directly introduce gas at the compressor last stage guide vane (11) into the flame tube (18);
the blending air intake assembly comprises: the inlet end of the bleed pipe (12) is communicated with the last stage guide vane (11) of the compressor; the inlet end of the intermediate communicating pipe (16) is communicated with the outlet end of the air guide pipe (12); the inlet end of the strong mixing conduit (17) is communicated with the outlet end of the intermediate communicating pipe (16), and the outlet end of the strong mixing conduit (17) is communicated with the flame tube (18); the self-adaptive adjusting device (15) is arranged between the outlet end of the air guide pipe (12) and the inlet end of the intermediate communicating pipe (16), and the self-adaptive adjusting device (15) can adjust the flow of the mixing air inlet assembly;
the adaptive adjustment device (15) includes: a throttle valve (24) arranged at the inlet end of the intermediate communicating pipe (16); the driving control component is connected with the throttle valve (24) and can control the opening of the throttle valve (24);
the drive control assembly includes: the data interaction machine (31) is used for carrying out communication signal interaction with the upper end control assembly; the integrated processor (21) is connected with the data interaction machine (31) and is used for receiving and processing the communication signal and sending a control signal according to the communication signal; the synchronous motor (22) is connected with the integrated processor (21), and the synchronous motor (22) can adjust the rotating speed and the rotating direction according to the control signal; and the gear set transmission device (23) is connected with the synchronous motor (22) and the throttle valve (24), and the synchronous motor (22) can adjust the opening of the throttle valve (24) through the gear set transmission device (23).
2. Combustion chamber with automatic regulation of the blended charge air according to claim 1, characterised in that the throttle valve (24) is of the plate, cascade or vane type.
3. The combustion chamber capable of automatically adjusting the blended intake air as claimed in claim 1, wherein the inner wall of the strong blending conduit (17) is provided with a plurality of turbulence columns (25) arranged at intervals.
4. The combustion chamber capable of automatically adjusting mixing air inflow as claimed in claim 1, wherein the outer wall of the strong mixing conduit (17) is provided with a plurality of sealing grooves, and each sealing groove is provided with a sealing gasket (26).
5. The combustion chamber capable of automatically adjusting blended intake air according to claim 1, wherein the diffuser (14) is connected with the inner casing (20), and the outer wall of the intermediate communicating pipe (16) is provided with a flange edge which is fixedly connected with the inner casing (20) in a bolt connection manner.
6. The combustion chamber capable of automatically adjusting mixing air inflow of any one of claims 1 to 5, characterized in that a flame tube (18) comprises a flame tube inner ring and a flame tube outer ring, an inner ring mixing hole is arranged on the flame tube inner ring, an outer ring mixing hole (29) is arranged on the flame tube outer ring, and the outlet end of the mixing air inflow component is connected with the inner ring mixing hole and/or the outer ring mixing hole (29).
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| CN202210057571.3A CN114076324B (en) | 2022-01-19 | 2022-01-19 | Combustion chamber capable of automatically adjusting mixed air intake |
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| CN202210057571.3A CN114076324B (en) | 2022-01-19 | 2022-01-19 | Combustion chamber capable of automatically adjusting mixed air intake |
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| CN114076324B true CN114076324B (en) | 2022-07-08 |
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| CN114704851A (en) * | 2022-03-01 | 2022-07-05 | 林胜杰 | Nozzle for gas turbine and gas turbine |
| CN115218220B (en) * | 2022-09-01 | 2023-01-17 | 中国航发四川燃气涡轮研究院 | Hot spot migration control design method for main combustion chamber |
| CN116677496B (en) * | 2023-08-03 | 2023-10-03 | 中国航发四川燃气涡轮研究院 | Automatic bleed air mechanism and compressor through pressure adjustment |
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