CN114857619B - Micro-mixed combustion chamber of gas turbine - Google Patents
Micro-mixed combustion chamber of gas turbine Download PDFInfo
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- CN114857619B CN114857619B CN202210466604.XA CN202210466604A CN114857619B CN 114857619 B CN114857619 B CN 114857619B CN 202210466604 A CN202210466604 A CN 202210466604A CN 114857619 B CN114857619 B CN 114857619B
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- air inlet
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- nozzle area
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 101
- 239000000446 fuel Substances 0.000 claims abstract description 96
- 238000002156 mixing Methods 0.000 claims abstract description 64
- 239000007789 gas Substances 0.000 claims abstract description 31
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 claims abstract description 8
- 239000003546 flue gas Substances 0.000 claims abstract description 8
- 239000002737 fuel gas Substances 0.000 claims description 6
- 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 6
- 230000009286 beneficial effect Effects 0.000 description 3
- 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
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 238000005496 tempering Methods 0.000 description 2
- 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
- 238000011161 development 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
- 230000010355 oscillation Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
A micro-mixed combustion chamber of a gas turbine belongs to the technical field of combustion chambers of gas turbines. The 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 burner and a flame tube, a nozzle area is arranged on the burner, the flame tube is arranged at 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 a class micro-premixing nozzle area and a main combustion stage micro-premixing nozzle area; the burner is provided with a fuel supply area in the direction opposite to the nozzle area, the periphery of the burner 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 on-duty stage mixing cavity is provided with a rotary 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 stage 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-mixed combustion chambers of gas turbines, in particular to a micro-mixed combustion chamber of a gas turbine.
Background
The efficient cleaning characteristic of the gas turbine has become an indispensable power source in industrial production, along with the technological iteration update, the gas turbine is continuously developed towards higher efficiency and wider load regulation range, and the method for improving the circulation efficiency is mainly realized by improving the combustion temperature and the combustion pressure, and in contradiction with the method, the generation amount of nitrogen oxides is rapidly increased along with the increase of the combustion temperature and the combustion pressure, and on the other hand, the cooling of the wall surface of the flame cylinder is more difficult due to the influence of the dual factors of the quality reduction of cooling gas and the increase of the combustion temperature, so that how to realize safe, stable and low-emission combustion in a wide load working condition range is an important performance target of a micro-mixing combustion chamber of the gas turbine.
Most of the existing gas turbines adopt a combustor adopting a Dry Low NOx (DLN) combustion technology, the combustor mainly adopts a lean premixed gas mixed by excessive air and fuel so as to inhibit the generation of nitrogen oxides, but the gas turbine is developed to a J level, the temperature level of the gas turbine is close to the critical value of the DLN effective working range (1670-1900K), if the temperature is further increased, on one hand, the emission of nitrogen oxides is greatly increased even if the air and the fuel are completely premixed, and on the other hand, the conventional swirl premixed combustion mode is adopted, the risks of tempering, self-ignition, thermoacoustic oscillation and the like exist, so that the Dry Low NOx (DLN) combustion technology cannot meet the development of the gas turbine.
Therefore, it is needed to provide a micro-mixed combustion chamber of a gas turbine, which reduces the emission of nitrogen oxides and improves the cooling efficiency of a flame tube, so as to realize safe, stable and low-emission combustion under a wide load range.
Disclosure of Invention
The technical problem to be solved by the invention is to provide the micro-mixed combustion chamber of the gas turbine, which can reduce the emission of nitrogen oxides and improve the cooling efficiency of the flame tube, so as to realize safe, stable and low-emission combustion under a wide load range.
The technical problem to be solved by the invention is realized by the following technical scheme that the invention is a micro-mixed combustion chamber of a gas turbine, which 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 burner and a flame tube, a nozzle area is arranged on the burner, the flame tube is arranged at 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 a duty micro-premixing nozzle area arranged in the middle and a main combustion micro-premixing nozzle area arranged at the periphery of the duty micro-premixing nozzle area;
the burner is provided with a fuel supply area in the direction opposite to the nozzle area, the periphery of the burner is provided with a shell covering the fuel supply area, and the fuel supply area comprises an on-duty mixing cavity for providing fuel gas for the on-duty micro-premixing nozzle area and a main combustion mixing cavity for providing fuel gas for the main combustion micro-premixing nozzle area; the periphery of the duty-level mixing cavity is provided with a rotary air inlet channel communicated with the air inlet cavity, the shell is provided with an air inlet communicated with the air inlet channel, 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 the main combustion stage mixing cavity is internally provided with a main combustion stage fuel pipe for providing fuel;
the 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 fin is identical to the rotary direction of the 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 on-duty fuel pipes are arranged, and at least 2 main fuel pipes are arranged.
The technical problem to be solved by the invention can be further solved by the following technical scheme that on-duty fuel pipes in the on-duty mixing cavity are circumferentially and uniformly distributed with on-duty fuel branch pipes at the outlet end, and the on-duty fuel branch pipes are provided with fuel outlet holes.
The technical problem to be solved by the invention can be further solved by the following technical scheme that main combustion stage fuel branch pipes are uniformly distributed at the periphery of the outlet end of the main combustion stage fuel pipe in the main combustion stage mixing cavity.
The technical problem to be solved by the invention can be further solved by the following technical scheme that the size of the air inlet holes is equal and the air inlet holes are densely arranged on the shell at the front and the rear.
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 duty-level mixing cavity 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 and close to the flue gas outlet end.
Compared with the prior art, the invention has the beneficial effects that,
(1) Compared with the traditional burner, each micro-premix tube of the main nozzle of the burner is relatively independent, and modular array expansion is carried out according to load requirements, so that the burner has better expansibility; the micro-mixing pipe nozzles are all 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) By adopting a mode of combining a mixing cavity with a micro-mixing pipe and a double-stage mixing mode, and mixing fuel and air in a millimeter scale, more uniform premixed gas of the fuel and the air can be obtained compared with a traditional cyclone premixed burner, so that the peak flame temperature in the combustion process can be reduced, and a better nitrogen oxide emission reduction effect is realized; because the flame formed by the micro-mixing pipe is short and small and the temperature distribution is uniform, the length of the flame tube of the combustion chamber can be greatly shortened.
(3) The micro-premixing pipes are distributed in an array mode, so that the sprayed flame is relatively dispersed in the radial direction, the heat release is relatively uniform, meanwhile, the micro-mixing pipes of the main nozzles can adopt different structural schemes, the natural frequency difference is realized, the thermo-acoustic coupling probability is reduced, and the problem of unstable combustion can be effectively avoided.
(4) The rotary air inlet structure with the value class matched with the flame tube fin is beneficial to improving the combustion air mixing uniformity, reducing the emission and improving the combustion performance of the burner; the air along distance is increased while the turbulence intensity of the gas mixture is improved, so that flame stabilization is facilitated, the stable operation boundary of the burner is widened, the heat exchange time of the wall surface of the flame and cooling air is increased, and the cooling efficiency of the wall surface of the flame is improved.
Drawings
FIG. 1 is a schematic view of a cross-sectional front view of a combustion chamber;
FIG. 2 is a schematic view of a front view of a combustion chamber;
FIG. 3 is a schematic view of a flame tube structure;
FIG. 4 is a schematic view of a burner in front cross-sectional configuration;
FIG. 5 is a schematic top cross-sectional view of a burner;
FIG. 6 is a schematic illustration of an on-duty fuel pipe configuration;
FIG. 7 is a schematic illustration of a primary fuel pipe structure.
In the figure: 1. a combustion device; 2. an outer housing; 21. an air inlet; 22. air flow direction; 3. a flame tube; 31. a convolute fin; 32. a main combustion stage combustion zone; 33. a class combustion zone; 34. an air intake chamber; 4. a burner; 41. a primary fuel pipe; 41A, main combustion stage fuel inlet; 41B main fuel branch; 42. an on-duty fuel pipe; 42A, duty grade fuel inlet; 42B, duty grade fuel manifold; 42C, duty grade fuel outlet; 43. a primary combustion stage mixing chamber; 43A, air intake holes; 44. a class-setting mixing chamber; 45. a main combustion stage micro-premix nozzle zone; 46. a class micro-premix nozzle zone; 47. an air intake passage; 48. the fuel flow direction; 49. the flow direction of the mixed gas is shown.
Detailed Description
Specific embodiments of the invention are described further below in order to facilitate a further understanding of the invention by those skilled in the art without limiting the scope of the claims thereto.
Referring to fig. 1-7, a micro-mixed 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 burner and a flame tube, a nozzle area is arranged on the burner, the flame tube is arranged at 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 a duty micro-premixing nozzle area arranged in the middle and a main combustion micro-premixing nozzle area arranged at the periphery of the duty micro-premixing nozzle area;
the burner is provided with a fuel supply area in the direction opposite to the nozzle area, the periphery of the burner is provided with a shell covering the fuel supply area, and the fuel supply area comprises an on-duty mixing cavity for providing fuel gas for the on-duty micro-premixing nozzle area and a main combustion mixing cavity for providing fuel gas for the main combustion micro-premixing nozzle area; the periphery of the duty-level mixing cavity is provided with a rotary air inlet channel communicated with the air inlet cavity, the shell is provided with an air inlet communicated with the air inlet channel, 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 the main combustion stage mixing cavity is internally provided with a main combustion stage fuel pipe for providing fuel;
the 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 fin is identical to the rotary direction of the air inlet channel at the periphery of the duty-level mixing cavity.
The on-duty fuel pipes are provided with one fuel pipe, and the main combustion fuel pipe is provided with at least two fuel pipes.
The on-duty fuel pipes in the on-duty mixing cavity are circumferentially and uniformly distributed with on-duty fuel branch pipes at the outlet end, and the on-duty fuel branch pipes are respectively provided with fuel outlet holes.
Main fuel branch pipes are circumferentially and uniformly distributed at the outlet end of the main fuel pipe in the main fuel mixing cavity.
The size of the air inlet holes is equal and the air inlet holes are densely arranged on the shell.
The cross-sectional area of the air inlet channel gradually decreases along the air inlet to the duty-class mixing cavity.
The air inlet is arranged on the outer shell body and is close to the flue gas outlet end.
Referring to fig. 1-5, the present embodiment discloses a micro-mixed combustion chamber of a gas turbine comprising: the combustion device 1, an outer shell 2, a flame tube 3, a swirl fin 31, a burner 4, a main combustion stage fuel pipe 41, a duty stage fuel pipe 42, a main combustion stage mixing cavity 43, a duty stage mixing cavity 44, a main combustion stage micro-premixing nozzle area 45, a duty stage micro-premixing nozzle area 46 and an air inlet channel 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 rotating fin in an upstream rotating way, finally flows into a main combustion stage mixing cavity 43 and a duty stage mixing cavity 44 respectively through an air inlet hole 43A and an air inlet channel 47, the flame tube forms a main combustion stage combustion zone 32 in a main combustion stage micro-premixing nozzle zone communication zone, forms a duty stage combustion zone 33 in a zone communicated with the duty stage micro-premixing nozzle zone, and is arranged in the main combustion stage combustion zone;
referring to fig. 4-5, the burner 4 adopts a main combustion stage and an on-duty stage combustion mode, and the front end of the burner 4 is provided with two main combustion stage fuel pipes 41 and an on-duty stage fuel pipe 42, wherein the main combustion stage fuel pipes 41 are symmetrically distributed, and the on-duty stage fuel pipe 42 is positioned on the central line of the burner main body 4 and is respectively communicated with a main combustion stage mixing cavity 43 and an on-duty stage mixing cavity 44. The main combustion stage micro-premixing nozzle area 45 is internally provided with a plurality of main nozzle micro-premixing pipes which are arranged in a staggered way so as to reduce the influence of air inlet of the outer layer pipe bundle on air inlet of the inner layer pipe bundle, the duty stage micro-premixing nozzle area 46 is internally provided with a plurality of duty nozzle micro-premixing pipes, and the number of layers is preferably 1-2; in this embodiment, the primary micro-premixing nozzle area 45 surrounds the duty micro-premixing nozzle area 46 by 1 layer, and surrounds the same by 360 degrees, which is beneficial to flame transfer and flame stabilization. In addition, an air inlet hole 43A is formed in the outer wall surface of the main combustion stage mixing cavity along the axial direction, and the distance between the air inlet holes 43A is gradually increased along the axial direction; the valve class mixing cavity 44 is circumferentially and uniformly provided with 3 valve class mixing cavity air inlet channels 47, the inlets and outlets of the rotary air inlet channels 47 are strip-shaped, the inlet area of the air inlet channels 47 is smaller than the outlet area, the air inlet channels 47 are obliquely arranged, the rotating direction is consistent with the rotating direction of air, on one hand, the air flow loss is reduced, on the other hand, the air enters the valve class mixing cavity 44 through the air inlet channels 47 and is rotationally mixed with fuel in the valve class mixing cavity 44, so that the mixing uniformity of the fuel and the air is improved, the emission is reduced, the turbulent flow intensity of the mixed gas is improved, the stability of flame is improved, and the stable operation boundary of the burner is widened;
referring to fig. 6-7, the fuel flows into the main stage mixing chamber 43 and the duty stage mixing chamber 44 along the fuel flow direction 48 through the main stage fuel inlet 41A and the duty stage fuel inlet 42A, respectively, the fuel is uniformly dispersed in the mixing chamber and mixed with air, then flows into the main stage micro-premixing nozzle area 45 and the duty stage micro-premixing nozzle area 46, respectively, flows out of the burner body after further mixing, and finally flows into the combustion area of the flame tube in the combustion chamber, and the mixed premixed gas participates in combustion in the main stage combustion area 33 and the duty stage combustion area 34, respectively.
The main pipe at the outlet of the duty fuel pipe 42 is provided with duty fuel branch pipes 42B, preferably, the duty fuel branch pipes 42B are at least provided with 2 and are uniformly arranged along the circumferential direction, and the number of the duty fuel branch pipes 42B in the embodiment is 3; 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, the number of the air outlet holes in the embodiment is 2, the sizes of the air outlet holes are equal, and the direction of the air outlet holes is opposite to the rotating direction of the air inlet channel of the on-duty micro-premixing area, so that the mixing uniformity of fuel and air is improved, and the emission of nitrogen oxides is reduced.
Similarly, the outlet pipe of the main fuel pipe 41 is provided with main fuel branch pipes 41B, in this embodiment, 3 main fuel branch pipes 41B are uniformly arranged on each main fuel pipe 41 along the circumferential direction, the fuel outlet direction is perpendicular to the axis of the main fuel pipe, and finally the fuel enters the combustion area of the flame tube along the direction of the mixed gas flow direction 49, and the fuel flow direction is opposite to the air inlet direction of the outer ring cavity, so that the fuel and the air mutually offset, and the mixing uniformity of the main fuel and the air 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 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 principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.
Claims (7)
1. A gas turbine micro-mixed combustion chamber, characterized in that: the combustion device is arranged in the outer shell, 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 formed in the outer shell;
the combustion device comprises a burner and a flame tube, a nozzle area is arranged on the burner, the flame tube is arranged at 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 a duty micro-premixing nozzle area arranged in the middle and a main combustion micro-premixing nozzle area arranged at the periphery of the duty micro-premixing nozzle area;
the burner is provided with a fuel supply area in the direction opposite to the nozzle area, the periphery of the burner is provided with a shell covering the fuel supply area, and the fuel supply area comprises an on-duty mixing cavity for providing fuel gas for the on-duty micro-premixing nozzle area and a main combustion mixing cavity for providing fuel gas for the main combustion micro-premixing nozzle area; the periphery of the duty-level mixing cavity is provided with a rotary air inlet channel communicated with the air inlet cavity, the shell is provided with an air inlet communicated with the air inlet channel, 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 the main combustion stage mixing cavity is internally provided with a main combustion stage fuel pipe for providing fuel;
a convolution fin is arranged in an air inlet cavity between the inner wall of the outer shell and the outer wall of the flame tube, the convolution fin is connected with the outer wall of the flame tube, and the convolution fin has the same rotation direction as an air inlet channel at the periphery of the duty-level mixing cavity;
a plurality of main nozzle micro-premixing pipes are arranged in the main combustion stage micro-premixing nozzle area in a staggered manner; and a plurality of on-duty nozzle micro-premixing pipes are arranged in the on-duty stage micro-premixing nozzle area.
2. The gas turbine micro-mixed combustor as set forth in claim 1, wherein: the on-duty grade fuel pipe is provided with 1, and the main combustion grade fuel pipe is provided with 2 at least.
3. The gas turbine micro-mixed combustor as set forth in claim 1, wherein: the on-duty fuel pipes in the on-duty mixing cavity are circumferentially and uniformly distributed with on-duty fuel branch pipes at the outlet end, and the on-duty fuel branch pipes are provided with fuel outlet holes.
4. The gas turbine micro-mixed combustor as set forth in claim 1, wherein: main fuel branch pipes are circumferentially and uniformly distributed at the outlet end of the main fuel pipe in the main fuel mixing cavity.
5. The gas turbine micro-mixed combustor as set forth in claim 1, wherein: the size of the air inlet holes is equal and the air inlet holes are densely arranged on the shell.
6. The gas turbine micro-mixed combustor as set forth in claim 1, wherein: the cross-sectional area of the air inlet channel gradually decreases along the air inlet to the duty-class mixing cavity.
7. The gas turbine micro-mixed combustor as set forth in claim 1, wherein: the air inlet is arranged on the outer shell body and is close to the flue gas 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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| CN114857619A CN114857619A (en) | 2022-08-05 |
| CN114857619B true CN114857619B (en) | 2024-01-26 |
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| CN115875693B (en) * | 2022-11-03 | 2024-05-10 | 中国科学院工程热物理研究所 | Combustion chamber integrated with head of gas turbine and gas turbine power generation system |
| CN115978587A (en) * | 2022-12-19 | 2023-04-18 | 江苏中科能源动力研究中心 | Combustion chamber with standing vortex micro-mixing combined nozzle |
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| CN104296160A (en) * | 2014-09-22 | 2015-01-21 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Flow guide bush of combustion chamber of combustion gas turbine and with cooling function |
| CN111765491A (en) * | 2020-08-04 | 2020-10-13 | 中国科学院工程热物理研究所 | Natural gas turbine micro-premix combustor applied to wet air circulation |
| CN113091094A (en) * | 2021-05-13 | 2021-07-09 | 中国联合重型燃气轮机技术有限公司 | Gas turbine combustor nozzle and method of premixing fuel and air in the nozzle |
| CN114046537A (en) * | 2021-12-10 | 2022-02-15 | 浙江意动科技股份有限公司 | Combined premixing nozzle of microminiature gas turbine |
| 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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