CN114857619A - Micro-mixing combustion chamber of gas turbine - Google Patents
Micro-mixing combustion chamber of gas turbine Download PDFInfo
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- CN114857619A CN114857619A CN202210466604.XA CN202210466604A CN114857619A CN 114857619 A CN114857619 A CN 114857619A CN 202210466604 A CN202210466604 A CN 202210466604A CN 114857619 A CN114857619 A CN 114857619A
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 98
- 238000002156 mixing Methods 0.000 title claims abstract description 73
- 239000000446 fuel Substances 0.000 claims abstract description 95
- 239000007789 gas Substances 0.000 claims abstract description 35
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 claims abstract description 5
- 239000003546 flue gas Substances 0.000 claims abstract description 5
- 239000000779 smoke Substances 0.000 claims description 3
- 230000007423 decrease Effects 0.000 claims description 2
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 abstract description 27
- 238000001816 cooling Methods 0.000 abstract description 5
- 238000004378 air conditioning Methods 0.000 abstract 1
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009776 industrial production Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000005496 tempering Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
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
- F23R3/28—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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
Abstract
A micro-mixing combustion chamber of a gas turbine belongs to the technical field of combustion chambers of gas turbines. The air-conditioning device comprises an outer shell, wherein a combustion device is arranged in the outer shell, and an air inlet cavity is formed between the outer wall of the combustion device and the inner wall of the outer shell; the combustion device comprises a combustor and a flame tube, wherein a nozzle area is arranged on the combustor, the flame tube is arranged on the periphery of the nozzle area, and a flue gas outlet communicated with the flame tube is arranged on the outer shell; the nozzle area comprises an on-duty micro-premixing nozzle area and a main combustion micro-premixing nozzle area; the combustor is provided with a fuel supply area in the direction opposite to the nozzle area, the periphery of the combustor is provided with a shell covering the fuel supply area, and the fuel supply area comprises an on-duty mixing cavity and a main combustion mixing cavity; the periphery of the duty-level mixing cavity is provided with a convolute air inlet channel communicated with the air inlet cavity, the shell is provided with an air inlet communicated with the air inlet channel, and the shell is provided with an air inlet communicated with the air inlet cavity and used for supplying air to the main combustion-level mixing cavity. Thereby reducing the emission of nitrogen oxides and improving the cooling efficiency of the flame tube.
Description
Technical Field
The invention relates to the technical field of micro-mixing combustion chambers of gas turbines, in particular to a micro-mixing combustion chamber of a gas turbine.
Background
The gas turbine has become an indispensable power source in industrial production due to the efficient cleaning characteristic, the gas turbine is continuously developed towards higher efficiency and wider load regulation range along with the iterative updating of the technology, the method for improving the cycle efficiency is mainly realized by improving the combustion temperature and pressure, and in contradiction, along with the increase of the combustion temperature and pressure, the generation amount of nitrogen oxides is rapidly increased on one hand, and on the other hand, the wall surface of a flame tube is more difficult to cool due to the dual factors of the reduction of the quality of cooling gas and the increase of the combustion temperature, so that how to realize safe, stable and low-emission combustion in the wide load working condition range is an important performance target of the micro-mixing combustion chamber of the gas turbine.
Most of existing gas turbines adopt a combustor of a Dry Low nitrogen oxide (dly Low NOx, DLN) combustion technology, the combustor mainly adopts a method of mixing excess air and fuel into lean premixed gas to inhibit the generation of nitrogen oxide, but the gas turbine is developed to a level J, the temperature level of the combustor approaches to the critical value of a DLN effective working range (1670-.
Therefore, it is urgently needed to provide a micro-mixing combustion chamber of a gas turbine, which can reduce the emission of nitrogen oxides and improve the cooling efficiency of a flame tube, thereby realizing safe, stable and low-emission combustion in a wide load range.
Disclosure of Invention
The invention aims to solve the technical problem of providing a micro-mixed combustion chamber of a gas turbine, which can reduce the emission of nitrogen oxides and improve the cooling efficiency of a flame tube so as to realize safe, stable and low-emission combustion in a wide load range.
The technical problem to be solved by the invention is realized by the following technical scheme, and the micro-mixing combustion chamber of the gas turbine is characterized by comprising an outer shell, wherein an inner cavity is arranged in the outer shell, a combustion device is arranged in the inner cavity, an air inlet cavity is formed between the outer wall of the combustion device and the inner wall of the outer shell, and an air inlet communicated with the air inlet cavity is arranged on the outer shell;
the combustion device comprises a combustor and a flame tube, the combustor is provided with a nozzle area, the flame tube is arranged on the periphery of the nozzle area, and the outer shell is provided with a flue gas outlet communicated with the flame tube; the nozzle area comprises a duty-class micro-premixing nozzle area arranged in the middle and a main combustion-class micro-premixing nozzle area arranged on the periphery of the duty-class micro-premixing nozzle area;
the combustor is provided with a fuel supply area in the direction opposite to the nozzle area, a shell covering the fuel supply area is installed on the periphery of the combustor, and the fuel supply area comprises an on-duty mixing cavity for providing gas for the on-duty micro-premixing nozzle area and a main combustion mixing cavity for providing gas for the main combustion micro-premixing nozzle area; a convolute air inlet channel communicated with the air inlet cavity is arranged at the periphery of the duty level mixing cavity, an air inlet communicated with the air inlet channel is arranged on the shell, and a duty level fuel pipe for providing fuel is arranged in the duty level mixing cavity; the shell is provided with a plurality of air inlets which are communicated with the air inlet cavity and supply air to the main combustion stage mixing cavity, and a main combustion stage fuel pipe for supplying fuel is arranged in the main combustion stage mixing cavity;
and a rotary fin is arranged in the air inlet cavity between the inner wall of the outer shell and the outer wall of the flame tube, the rotary fin is connected with the outer wall of the flame tube, and the rotary direction of the rotary fin is the same as that of an air inlet channel at the periphery of the duty-level mixing cavity.
The technical problem to be solved by the invention can be further solved by the following technical scheme that 1 number of the duty-level fuel pipes is arranged, and at least 2 numbers of the main fuel-level fuel pipes are arranged.
The technical problem to be solved by the invention can be further realized by the following technical scheme that duty fuel branch pipes are uniformly distributed at the outlet end of a duty fuel pipe in the duty mixing cavity in the circumferential direction, and the duty fuel branch pipes are provided with fuel outlets.
The technical problem to be solved by the invention can be further realized by the following technical scheme that main combustion stage fuel branch pipes are circumferentially and uniformly distributed at the outlet ends of main combustion stage fuel pipes in the main combustion stage mixing cavity.
The technical problem to be solved by the invention can be further realized by the following technical scheme that the air inlets are equal in size and are densely arranged in the front and sparsely arranged in the rear on the shell.
The technical problem to be solved by the invention can be further solved by the following technical scheme that the sectional area of the air inlet channel from the air inlet to the mixing cavity on duty is gradually reduced.
The technical problem to be solved by the invention can be further solved by the following technical scheme that the air inlet is arranged on the outer shell close to the smoke outlet end.
Compared with the prior art, the invention has the advantages that,
(1) compared with the traditional combustor, each micro premix pipe of the main nozzle of the combustor is relatively independent, and modular array expansion is carried out according to load requirements, so that the combustor has better expansibility; the micro-mixing pipe nozzle is arranged at millimeter level, the flow velocity in the micro-mixing pipe is higher, the tempering problem can be effectively avoided, the residence time of high-temperature flue gas is shortened, and the emission of nitrogen oxides is reduced.
(2) The mixing cavity is combined with the micro-mixing pipe to form a two-stage mixing mode, and fuel and air are mixed in a millimeter scale, so that more uniform fuel and air premixed gas compared with the traditional swirl premixed burner can be obtained, the peak flame temperature in the combustion process can be reduced, and the better nitrogen oxide emission reduction effect can be realized; because the flame formed by the micro mixing pipe is short and uniform in temperature distribution, the length of the flame tube of the combustion chamber can be greatly shortened.
(3) The micro-premixing pipes are distributed in an array form, so that the sprayed flame is relatively dispersed in the radial direction, the heat release is relatively uniform, meanwhile, the micro-premixing pipes of the main nozzles can adopt different structural schemes, the inherent frequency difference is realized, the thermoacoustic coupling probability is reduced, and the problem of unstable combustion can be effectively avoided.
(4) The rotary air inlet structure matched with the flame tube fins on the class is beneficial to improving the combustion air mixing uniformity, reducing the emission and improving the combustion performance of the combustor; the air on-way distance is increased while the turbulence intensity of the gas mixture is improved, and flame stabilization is facilitated, so that the stable operation boundary of the combustor is widened, the heat exchange time of the wall surface of the flame tube and cooling air is prolonged, and the cooling efficiency of the wall surface of the flame tube is improved.
Drawings
FIG. 1 is a schematic sectional view of a combustion chamber;
FIG. 2 is a schematic front view of a combustion chamber;
FIG. 3 is a schematic view of a flame tube;
FIG. 4 is a schematic sectional view of the burner in front elevation;
FIG. 5 is a schematic sectional top view of the burner;
FIG. 6 is a schematic view of an on-duty fuel tube configuration;
FIG. 7 is a schematic view of a main combustion stage fuel pipe structure.
In the figure: 1. a combustion device; 2. an outer housing; 21. an air inlet; 22. the direction of air flow; 3. a flame tube; 31. a convoluted fin; 32. a primary combustion stage combustion zone; 33. a class burning zone; 34. an air intake chamber; 4. a burner; 41. a primary fuel stage fuel pipe; 41A, a main combustion stage fuel inlet; 41B main combustion stage fuel branch; 42. an on-duty grade fuel pipe; 42A, an on-duty fuel inlet; 42B, an on-duty fuel branch pipe; 42C, an on-duty fuel outlet; 43. a primary combustion stage mixing chamber; 43A, air intake; 44. a class mixing chamber; 45. a primary combustion stage micro-premix nozzle zone; 46. a class micro-premix nozzle zone; 47. an air intake passage; 48. a fuel flow direction; 49. the mixed gas flows in the direction.
Detailed Description
The following further describes particular embodiments of the present invention to facilitate further understanding of the present invention by those skilled in the art, and does not constitute a limitation to the right thereof.
Referring to fig. 1-7, a micro-mixing combustion chamber of a gas turbine is characterized by comprising an outer shell, wherein an inner cavity is arranged in the outer shell, a combustion device is arranged in the inner cavity, an air inlet cavity is formed between the outer wall of the combustion device and the inner wall of the outer shell, and an air inlet communicated with the air inlet cavity is arranged on the outer shell;
the combustion device comprises a combustor and a flame tube, the combustor is provided with a nozzle area, the flame tube is arranged on the periphery of the nozzle area, and the outer shell is provided with a flue gas outlet communicated with the flame tube; the nozzle area comprises a duty-class micro-premixing nozzle area arranged in the middle and a main combustion-class micro-premixing nozzle area arranged on the periphery of the duty-class micro-premixing nozzle area;
the combustor is provided with a fuel supply area in the direction opposite to the nozzle area, a shell covering the fuel supply area is installed on the periphery of the combustor, and the fuel supply area comprises an on-duty mixing cavity for providing gas for the on-duty micro-premixing nozzle area and a main combustion mixing cavity for providing gas for the main combustion micro-premixing nozzle area; a convolute air inlet channel communicated with the air inlet cavity is arranged at the periphery of the duty level mixing cavity, an air inlet communicated with the air inlet channel is arranged on the shell, and a duty level fuel pipe for providing fuel is arranged in the duty level mixing cavity; the shell is provided with a plurality of air inlets which are communicated with the air inlet cavity and supply air to the main combustion stage mixing cavity, and a main combustion stage fuel pipe for supplying fuel is arranged in the main combustion stage mixing cavity;
and a rotary fin is arranged in the air inlet cavity between the inner wall of the outer shell and the outer wall of the flame tube, the rotary fin is connected with the outer wall of the flame tube, and the rotary direction of the rotary fin is the same as that of an air inlet channel at the periphery of the duty-level mixing cavity.
The on-duty level fuel pipe is equipped with one, main burning level fuel pipe is equipped with two at least.
The on-duty fuel branch pipes are circumferentially and uniformly distributed at the outlet end of the on-duty fuel pipe in the on-duty mixing cavity, and the on-duty fuel branch pipes are respectively provided with fuel outlets.
And main combustion grade fuel branch pipes are uniformly distributed at the outlet end of the main combustion grade fuel pipe in the main combustion grade mixing cavity in the circumferential direction.
The sizes of the air inlets are equal, and the air inlets are arranged on the shell in a dense mode and a sparse mode.
The cross-sectional area of the intake passage decreases along the intake port to the on-duty mixing chamber.
The air inlet is arranged on the outer shell and close to the smoke outlet end.
Referring to fig. 1 to 5, the present embodiment discloses a micro-hybrid combustor for a gas turbine, including: the burner device 1, the outer casing 2, the flame tube 3, the swirl fin 31, the burner 4, the main fuel stage fuel pipe 41, the on-duty fuel pipe 42, the main fuel stage mixing chamber 43, the on-duty mixing chamber 44, the main fuel stage micro-premix nozzle region 45, the on-duty micro-premix nozzle region 46, and the air intake passage 47.
The outer shell 2 is provided with an air inlet 21, compressed air flows into the outer shell 2 along an air flow direction 22 through the air inlet 21, flows into an air inlet cavity 34 along a cavity channel in the rotary fin in an upstream rotating mode, and finally flows into a main combustion stage mixing cavity 43 and an on-duty mixing cavity 44 through an air inlet 43A and an air inlet channel 47 respectively, the flame tube forms a main combustion stage combustion zone 32 in a main combustion stage micro-premixing nozzle zone communication area, an on-duty combustion zone 33 is formed in an area communicated with the on-duty micro-premixing nozzle zone, and the on-duty combustion zone is arranged inside the main combustion stage combustion zone;
referring to fig. 4-5, the burner 4 adopts a staged combustion mode of main combustion stage and on-duty stage, and two main combustion stage fuel pipes 41 and one value stage fuel pipe 42 are disposed at the front end of the burner 4, wherein the main combustion stage fuel pipes 41 are symmetrically distributed, and the on-duty stage fuel pipe 42 is disposed on the central line of the burner body 4 and is respectively communicated with a main combustion stage mixing chamber 43 and an on-duty stage mixing chamber 44. A plurality of main nozzle micro-premixing pipes are arranged in the main combustion stage micro-premixing nozzle area 45 and are arranged in a staggered mode, so that the influence of outer-layer pipe bundle air intake on inner-layer pipe bundle air intake is reduced, a plurality of value-class nozzle micro-premixing pipes are arranged in the value-class micro-premixing nozzle area 46, and the number of layers is preferably 1-2; in this embodiment, the number of layers is 1, and the main combustion stage micro premixing nozzle region 45 surrounds the number stage micro premixing nozzle region 46 by 360 degrees, which is beneficial to flame propagation and flame stabilization. In addition, the outer wall surface of the main combustion stage mixing cavity is provided with air inlet holes 43A along the axial direction, and the distance between the air inlet holes 43A is gradually increased along the axial direction; 3 air inlet channels 47 of the on-duty mixing chamber are uniformly arranged in the circumferential direction of the on-duty mixing chamber 44, the inlets and outlets of the convoluted air inlet channels 47 are long strips, the area of the inlets of the air inlet channels 47 is smaller than that of the outlets, the air inlet channels 47 are obliquely arranged, the rotating direction of the air inlet channels is consistent with the rotating direction of air, and the air inlet structures of the on-duty mixing chamber are matched with the convoluted fins 31 of the flame tube, so that the air flow loss is reduced on one hand, and on the other hand, after the air enters the on-duty mixing chamber 44 through the air inlet channels 47, the air is rotationally mixed with the fuel in the on-duty mixing chamber 44, so that the mixing uniformity of the fuel and the air is improved, the emission is reduced, the turbulence intensity of the mixed gas is improved, the stability of flame is improved, and the stable operation boundary of the combustor is widened;
referring to fig. 6-7, the fuel flows into the main combustion stage mixing chamber 43 and the on-duty mixing chamber 44 through the main combustion stage fuel inlet 41A and the on-duty fuel inlet 42A along the fuel flow direction 48, respectively, the fuel is uniformly dispersed in the mixing chamber and mixed with air, then flows into the main combustion stage micro-premixing nozzle zone 45 and the on-duty micro-premixing nozzle zone 46, respectively, flows out of the burner body after further mixing, and finally the mixed premixed gas flows into the combustion zone of the flame tube in the combustion chamber to participate in combustion in the main combustion stage combustion zone 33 and the on-duty combustion zone 34, respectively.
The main outlet pipeline of the duty fuel pipe 42 is provided with duty fuel branch pipes 42B, preferably, the duty fuel branch pipes 42B are provided with at least 2 and are uniformly arranged along the circumferential direction, and the number of the duty fuel branch pipes 42B is 3 in the embodiment; the on-duty fuel branch pipes 42B are further provided with air outlet holes 42C respectively, the number of the air outlet holes 42C on each on-duty fuel branch pipe 42B is equal and at least 2 air outlet holes are arranged, in the embodiment, the number of the air outlet holes is 2, the size of the air outlet holes is equal, and the air outlet holes face the direction opposite to the rotation direction of the air inlet channel of the on-duty micro premixing area, so that the mixing uniformity of the fuel and the air is improved, and the emission of nitrogen oxides is reduced.
Similarly, the outlet pipes of the main stage fuel pipes 41 are provided with main stage fuel branch pipes 41B, in this embodiment, 3 main stage fuel branch pipes 41B are uniformly arranged on each main stage fuel pipe 41 along the circumferential direction, the fuel outlet direction is perpendicular to the main stage fuel pipe axis, and finally enters the combustion zone of the flame tube along the direction of the mixed gas flow direction 49, the fuel flow direction is opposite to the outer ring cavity air inlet direction, so that the fuel and the air are opposite to each other, and the main stage fuel air mixing uniformity is improved.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (7)
1. A micro-mixing combustion chamber of a gas turbine is characterized in that: the air inlet cavity is formed between the outer wall of the combustion device and the inner wall of the outer shell, and an air inlet communicated with the air inlet cavity is formed in the outer shell;
the combustion device comprises a combustor and a flame tube, the combustor is provided with a nozzle area, the flame tube is arranged on the periphery of the nozzle area, and the outer shell is provided with a flue gas outlet communicated with the flame tube; the nozzle area comprises a duty-class micro-premixing nozzle area arranged in the middle and a main combustion-class micro-premixing nozzle area arranged on the periphery of the duty-class micro-premixing nozzle area;
the combustor is provided with a fuel supply area in the direction opposite to the nozzle area, a shell covering the fuel supply area is installed on the periphery of the combustor, and the fuel supply area comprises an on-duty mixing cavity for providing gas for the on-duty micro-premixing nozzle area and a main combustion mixing cavity for providing gas for the main combustion micro-premixing nozzle area; a convolute air inlet channel communicated with the air inlet cavity is arranged at the periphery of the duty level mixing cavity, an air inlet communicated with the air inlet channel is arranged on the shell, and a duty level fuel pipe for providing fuel is arranged in the duty level mixing cavity; the shell is provided with a plurality of air inlets which are communicated with the air inlet cavity and supply air to the main combustion stage mixing cavity, and a main combustion stage fuel pipe for supplying fuel is arranged in the main combustion stage mixing cavity;
and a rotary fin is arranged in the air inlet cavity between the inner wall of the outer shell and the outer wall of the flame tube, the rotary fin is connected with the outer wall of the flame tube, and the rotary direction of the rotary fin is the same as that of an air inlet channel at the periphery of the duty-level mixing cavity.
2. The gas turbine micro-hybrid combustor of claim 1, wherein: the class fuel pipe on duty is equipped with 1, main burning level fuel pipe is equipped with 2 at least.
3. The gas turbine micro-hybrid combustor of claim 1, wherein: the on-duty fuel branch pipe is evenly distributed at the outlet end of the on-duty fuel pipe in the on-duty mixing cavity in the circumferential direction, and the on-duty fuel branch pipe is provided with a fuel outlet.
4. The gas turbine micro-hybrid combustor of claim 1, wherein: and main combustion grade fuel branch pipes are uniformly distributed at the outlet end of the main combustion grade fuel pipe in the main combustion grade mixing cavity in the circumferential direction.
5. The gas turbine micro-hybrid combustor of claim 1, wherein: the sizes of the air inlets are equal, and the air inlets are arranged on the shell in a dense mode and a sparse mode.
6. The gas turbine micro-hybrid combustor of claim 1, wherein: the cross-sectional area of the intake passage decreases along the intake port to the on-duty mixing chamber.
7. The gas turbine micro-hybrid combustor of claim 1, wherein: the air inlet is arranged on the outer shell and close to the smoke outlet end.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210466604.XA CN114857619B (en) | 2022-04-29 | 2022-04-29 | Micro-mixed combustion chamber of gas turbine |
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| CN202210466604.XA CN114857619B (en) | 2022-04-29 | 2022-04-29 | Micro-mixed combustion chamber of gas turbine |
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| CN114857619B CN114857619B (en) | 2024-01-26 |
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| CN114294680A (en) * | 2021-12-29 | 2022-04-08 | 哈尔滨工业大学 | Micro-premix combustion chamber of center-staged gas turbine |
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