CN114992672B - Micro-premixing type combustion chamber of gas turbine - Google Patents
Micro-premixing type combustion chamber of gas turbine Download PDFInfo
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- CN114992672B CN114992672B CN202210656807.5A CN202210656807A CN114992672B CN 114992672 B CN114992672 B CN 114992672B CN 202210656807 A CN202210656807 A CN 202210656807A CN 114992672 B CN114992672 B CN 114992672B
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- tube bundle
- nozzle tube
- duty
- air inlet
- cavity
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 107
- 239000000446 fuel Substances 0.000 claims abstract description 71
- 239000007789 gas Substances 0.000 claims abstract description 44
- 238000009826 distribution Methods 0.000 claims abstract description 40
- 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
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 21
- 238000005516 engineering process Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 238000005192 partition Methods 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 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
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004140 cleaning Methods 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
- 239000006185 dispersion Substances 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000009776 industrial production Methods 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000005496 tempering 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
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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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
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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
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-premixing type gas turbine combustion chamber belongs to the technical field of gas turbine combustion chambers. The combustion device comprises an outer shell and a combustion device, wherein 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 tube bundle area is arranged on the burner, the nozzle tube bundle area comprises a duty-level nozzle tube bundle area and a main combustion-level nozzle tube bundle area, and a flue gas outlet communicated with the flame tube is arranged on the outer shell; the periphery of the nozzle tube bundle area is provided with a gas distribution cavity for wrapping the nozzle tube bundle area, a gas distribution system is arranged between the combustion device and the outer shell, the gas distribution system comprises a gas distribution baffle plate arranged in the air inlet cavity, and the gas distribution baffle plate divides the air inlet cavity into an inner gas inlet channel and an outer gas inlet channel; an on-duty air inlet channel communicated with the outer air inlet channel is arranged between the on-duty nozzle tube bundle region and the main combustion nozzle tube bundle region, and a fuel supply region is arranged in the direction opposite to the nozzle tube bundle region, wherein the fuel supply region comprises an on-duty fuel cavity and a main combustion fuel cavity.
Description
Technical Field
The invention relates to the technical field of combustion chambers of gas turbines, in particular to a micro-premixing combustion chamber of a gas turbine.
Background
Because the efficient cleaning property of the gas turbine has become an indispensable power source in industrial production, with the technological iteration update, the gas turbine is continuously developed towards higher efficiency and wider load adjustment range, and the method for improving the cycle efficiency is mainly realized by improving the combustion temperature and 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 pressure, so that how to realize stable and low-emission combustion in a wide load working condition range is an important performance target of a combustion chamber of the gas turbine.
Most of existing gas engines adopt a combustor adopting Dry Low nitrogen oxide (DLN) combustion technology, the combustor mainly adopts the mode that excessive air and fuel are mixed into lean premixed gas so as to inhibit the generation of nitrogen oxides, but the gas engine is developed to a J level, the temperature level of the gas engine 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 backfire, self-ignition, thermoacoustic oscillation and the like exist, so that the Dry Low nitrogen oxide (Dry NOx, DLN) combustion technology cannot meet the development of gas turbines, and the micro-mixed combustion technology is generated in the background.
The application numbers 202010772045.6 and 202021949562.8 propose a micro-premixing combustion chamber structure, the main body of the burner adopts a class-level and main-combustion stage-division combustion technology, but two-level air supply is not independent, and as the micro-premixing tube bundles of the main-combustion stage nozzle are arranged around the space of the micro-premixing tube bundles of the class-level nozzle, the main-combustion stage and the class-level air supply are mutually influenced, and the actual flow distribution deviates from the design value, so that the performance of the burner is reduced, and the stable and low-emission combustion performance requirements under a wide range of working conditions cannot be realized.
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 improve the performance of the burner and realize the requirements of stable and low-emission combustion performance under a wide range of working conditions.
The technical problem to be solved by the invention is realized by the following technical scheme that the invention is a micro-premixing type 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 combustor and a flame tube, wherein a nozzle tube bundle area is arranged on the combustor, the nozzle tube bundle area comprises a duty-level nozzle tube bundle area arranged in the middle and a main combustion-level nozzle tube bundle area arranged at the periphery of the duty-level nozzle tube bundle area, an upper port and a lower port are arranged on the flame tube, the upper port of the flame tube is arranged at the periphery of the nozzle tube bundle area, and a flue gas outlet communicated with the lower port of the flame tube is arranged on an outer shell;
The periphery of the nozzle tube bundle area is provided with an air distribution cavity wrapping the nozzle tube bundle area, an air inlet hole is arranged on a tube bundle in the air distribution cavity, an air distribution system is arranged between the combustion device and the outer shell, the air distribution system comprises an air distribution baffle plate arranged in the air inlet cavity, the air distribution baffle plate divides the air inlet cavity into an inner air inlet channel and an outer air inlet channel, and the inner air inlet channel is communicated with the air distribution cavity; an end cover is arranged at the front end of the burner, and a plurality of radial swirl blades for improving the air flow intensity of the outer air inlet channel are radially arranged on the upper surface of the end cover; an on-duty air inlet channel communicated with the outer air inlet channel is arranged between the on-duty nozzle tube bundle region and the main combustion nozzle tube bundle region, the on-duty air inlet channel is communicated with the air distribution cavity, and a plurality of axial swirl blades for improving the air flow intensity of the on-duty air inlet channel are arranged in the on-duty air inlet channel;
The burner is provided with a fuel supply area in the direction opposite to the nozzle tube bundle area, the fuel supply area comprises an on-duty fuel cavity for providing fuel for the on-duty nozzle tube bundle area and a main combustion stage fuel cavity for providing fuel for the main combustion stage nozzle tube bundle area, a class-value fuel tube is arranged in the on-duty fuel cavity, and a main combustion stage fuel tube is arranged in the main combustion stage fuel cavity.
The technical problem to be solved by the invention can be further solved by the following technical scheme, wherein the inner diameter of the nozzle tube bundle in the nozzle tube bundle area is 5-12 mm.
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 the flame tube forms an on-duty combustion zone in a zone communicated with the on-duty nozzle tube bundle zone, and forms a main combustion zone in a zone communicated with the main combustion nozzle tube bundle zone.
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, the burner nozzle tube bundles are relatively independent, the main combustion stage nozzle tube bundles are arranged around the valve stage nozzle tube bundles, and the modularized array expansion is carried out according to load requirements, so that the burner has better expansibility.
(2) The inner diameters of the nozzle tube bundles are all millimeter-sized, and the fuel and the air are mixed in millimeter scale, so that more uniform fuel and air premixed gas can be obtained compared with the traditional cyclone premixed burner, the peak flame temperature in the combustion process can be reduced, and a better nitrogen oxide emission reduction effect is realized; and the flow velocity in the nozzle tube bundle is higher, so that 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.
(3) Through setting up the nozzle tube bank that distributes with array form, therefore the flame of blowout is radial relative dispersion, and the heat release is even relatively, and each main nozzle micromixing tube can adopt different structural schemes simultaneously, realizes the natural frequency difference, has reduced thermoacoustic coupling probability, can effectively avoid burning unstable problem.
(4) The independent inner and outer air inlet channels are arranged on the valve class and the main combustion stage, so that mutual interference between the two stages is reduced, the two-stage actual air flow distribution accords with a design value, and the combustion performance of the combustor is ensured.
(5) Through set up radial swirl vane at the front end housing of combustor and set up axial swirl vane in the level of on duty air inlet channel, improved air turbulence intensity, both be favorable to burning air mixing, can widen the flame stability of combustor again, improve the ignition and the flame transfer performance of nozzle on duty.
Drawings
FIG. 1 is a schematic diagram of the principal cross-sectional structure of the present invention;
FIG. 2 is a schematic diagram of the structure of the present invention;
FIG. 3 is a schematic cross-sectional view of a combustor;
FIG. 4 is a three-dimensional semi-sectional view of a combustor;
FIG. 5 is a schematic top cross-sectional view of a nozzle tube bundle region;
FIG. 6 is a schematic view of a main combustion stage nozzle tube configuration;
FIG. 7 is a schematic view of a duty cycle nozzle tube configuration.
In the figure: 1. an outer housing; 2. an inner cavity; 3. a burner; 4. a flame tube; 21. an air intake line; 22. air flow direction; 23. an air intake chamber; 24. a combustion zone; 31. a primary fuel pipe; 32. an on-duty fuel pipe; 33. a primary combustion stage nozzle tube bundle region; 33A, inlet holes of the main combustion stage nozzle pipe; 33B, main stage nozzle tube fuel inlet; 33C, main stage nozzle tube fuel outlet; 34. a duty stage nozzle tube bundle zone; 34A, an air inlet of a duty nozzle pipe; 34B, duty nozzle tube fuel inlet; 34 C, a fuel outlet of the on-duty nozzle pipe; 35. a main combustion stage fuel chamber; 36. class fuel cavity; 37. an outer intake passage; 38. an inner intake passage; 39. a gas distribution baffle plate; 310. the flow direction of the fuel gas; 311. radial swirl vanes; 312. axial swirl vanes; 313. an air distribution cavity; 314. A partition plate; 315. the premixed gas flows.
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-premix gas turbine combustion chamber comprises an outer shell, wherein an inner cavity is formed in the outer shell, a combustion device is installed 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 formed in the outer shell; the combustion device comprises a combustor and a flame tube, wherein a nozzle tube bundle area is arranged on the combustor, the nozzle tube bundle area comprises a duty-level nozzle tube bundle area arranged in the middle and a main combustion-level nozzle tube bundle area arranged at the periphery of the duty-level nozzle tube bundle area, an upper port and a lower port are arranged on the flame tube, the upper port of the flame tube is arranged at the periphery of the nozzle tube bundle area, and a flue gas outlet communicated with the lower port of the flame tube is arranged on an outer shell;
The periphery of the nozzle tube bundle area is provided with an air distribution cavity wrapping the nozzle tube bundle area, an air inlet hole is arranged on a tube bundle in the air distribution cavity, an air distribution system is arranged between the combustion device and the outer shell, the air distribution system comprises an air distribution baffle plate arranged in the air inlet cavity, the air distribution baffle plate divides the air inlet cavity into an inner air inlet channel and an outer air inlet channel, and the inner air inlet channel is communicated with the air distribution cavity; an end cover is arranged at the front end of the burner, and a plurality of radial swirl blades for improving the air flow intensity of the outer air inlet channel are radially arranged on the upper surface of the end cover; an on-duty air inlet channel communicated with the outer air inlet channel is arranged between the on-duty nozzle tube bundle region and the main combustion nozzle tube bundle region, the on-duty air inlet channel is communicated with the air distribution cavity, and a plurality of axial swirl blades for improving the air flow intensity of the on-duty air inlet channel are arranged in the on-duty air inlet channel;
The burner is provided with a fuel supply area in the direction opposite to the nozzle tube bundle area, the fuel supply area comprises an on-duty fuel cavity for providing fuel for the on-duty nozzle tube bundle area and a main combustion stage fuel cavity for providing fuel for the main combustion stage nozzle tube bundle area, a class-value fuel tube is arranged in the on-duty fuel cavity, and a main combustion stage fuel tube is arranged in the main combustion stage fuel cavity.
The inner diameter of the nozzle tube bundle in the nozzle tube bundle area is 5-12 mm.
The on-duty grade fuel pipe is provided with 1, and the main combustion grade fuel pipe is provided with 2 at least.
The flame tube forms an on-duty combustion zone in a zone communicated with the on-duty nozzle tube bundle zone, and forms a main combustion zone in a zone communicated with the main combustion nozzle tube bundle zone.
The air inlet is arranged on the outer shell body and is close to the flue gas outlet end.
As shown in fig. 2, the combustion chamber of the present embodiment includes a burner 3 disposed at the front end of the inner cavity 2 and connected with a flame tube 4 to be disposed in the outer casing 1; an air inlet cavity 23 is formed between the outer shell 1 and the combustion device, an air inlet 21 is formed at the bottom of the outer shell 1, compressed air flows into the outer shell 1 through the air inlet 21 and flows upstream along the air inlet cavity 23, is split into an inner air inlet channel 38 and an outer air inlet channel 37 through an air distribution partition 39, and flows into an air distribution cavity 313 of the main combustion stage nozzle tube bundle area 33 and the duty stage nozzle tube bundle area 34 respectively.
As shown in fig. 3-5, the burner 3 adopts a main combustion stage and an on-duty stage combustion mode, and two main combustion stage fuel pipes 31 and one on-duty stage fuel pipe 32 are arranged at the front end of the burner 3, wherein the main combustion stage fuel pipes 31 are symmetrically distributed, and the on-duty stage fuel pipes 32 are positioned on the central line of the burner 3. The fuel supply area and the distribution chamber are separated from each other by a separator plate 314. The rear end of the burner is provided with an end cap at the outlet of the nozzle tube bundle, which isolates the plenum 313 from the combustion zone 24 of the cartridge.
After entering the fuel pipe, the fuel flows into the main combustion stage fuel cavity 35 and the duty stage fuel cavity 36 along the fuel flow direction 310 respectively, and the fuel flows into the fuel cavity to be uniformly dispersed, and then flows into the main combustion stage nozzle tube bundle region 33 and the duty stage nozzle tube bundle region 34 through the main combustion stage nozzle tube bundle fuel inlet 33B and the duty stage nozzle tube bundle inlet 34B respectively. Air in the inner air inlet channel enters the primary combustion stage nozzle tube bundle zone 33 through the primary combustion stage nozzle tube air inlet aperture 33A; the radial swirl vanes 311 are arranged on the front end cover of the burner, the axial swirl vanes 312 are arranged in the on-duty air inlet channel, compressed air flows through the radial swirl vanes 311 and the axial swirl vanes 312 after entering the outer air inlet channel 37 through the air distribution partition plate, finally enters the on-duty nozzle tube bundle region 34 from the on-duty nozzle tube air inlet 34A, and as mentioned above, on-duty air supply and main combustion air supply are mutually opposite, so that control of air flow distribution between two stages is facilitated, the actual values of the main combustion air flow and the on-duty air flow are more consistent with the design values, combustion performance of the combustion chamber is ensured, and in addition, the radial swirl vanes and the axial swirl vanes arranged on the burner greatly improve air turbulence intensity, so that combustion-air mixing is facilitated, flame stability of the burner can be widened, and ignition and flame transfer performance of the on-duty nozzle are improved.
The primary stage nozzle bundle section 33 includes a plurality of primary stage nozzle tubes, preferably 3 to 8, in this embodiment 3, and each equal in number, staggered to reduce the effect of the outer tube bundle air intake on the inner tube bundle air intake. The duty nozzle tube bundle area 34 comprises a plurality of duty nozzle tubes, and the number of layers is preferably 1-2; in the embodiment, the number of layers is 2, and the layers are equal, and the layers are staggered, so that the influence of air inlet of the outer layer tube bundle on air inlet of the inner layer tube bundle is reduced. In addition, the main combustion stage nozzle pipe surrounds the duty stage nozzle pipe, and surrounds the duty stage nozzle pipe by 360 degrees, so that flame transfer and flame stabilization are facilitated.
As shown in fig. 6-7, the main combustion stage nozzle pipe and the duty stage nozzle pipe adopt the same structure, and the fuel inlets are all positioned at the end parts of the nozzle pipes and communicated with the fuel supply cavity; the air inlet adopts a circular hole structure, two rows of air inlets are formed in the side wall of the nozzle pipe along the axial position, the horizontal positions of the air inlet 33A of the main combustion stage nozzle pipe and the air inlet 34A of the duty stage nozzle pipe are the same, and after air and fuel are mixed, the air and the fuel are sprayed into the flame tube for combustion along the premixed air flow direction 315 from the fuel outlet 34C of the duty stage nozzle pipe and the fuel outlet 33C of the main combustion stage nozzle pipe.
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 (5)
1. A micro-premix gas turbine combustor, characterized by: the combustion device comprises an outer shell, wherein an inner cavity is formed 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 formed in the outer shell; the combustion device comprises a combustor and a flame tube, wherein a nozzle tube bundle area is arranged on the combustor, the nozzle tube bundle area comprises a duty-level nozzle tube bundle area arranged in the middle and a main combustion-level nozzle tube bundle area arranged at the periphery of the duty-level nozzle tube bundle area, an upper port and a lower port are arranged on the flame tube, the upper port of the flame tube is arranged at the periphery of the nozzle tube bundle area, and a flue gas outlet communicated with the lower port of the flame tube is arranged on an outer shell;
The periphery of the nozzle tube bundle zone is provided with a gas distribution cavity wrapping the nozzle tube bundle zone, the gas distribution cavity comprises a gas distribution cavity wrapping the nozzle tube bundle zone of the class and a gas distribution cavity wrapping the nozzle tube bundle zone of the main combustion stage, the nozzle tube bundles in the gas distribution cavity are provided with gas inlets, a gas distribution system is arranged between the combustion device and the outer shell and comprises a gas distribution baffle plate arranged in the air inlet cavity, the gas distribution baffle plate divides the air inlet cavity into an inner gas inlet channel and an outer gas inlet channel, and the inner gas inlet channel is communicated with the gas distribution cavity wrapping the nozzle tube bundle zone of the main combustion stage; an end cover is arranged at the front end of the burner, and a plurality of radial swirl blades for improving the air flow intensity of the outer air inlet channel are radially arranged on the upper surface of the end cover; an on-duty air inlet channel communicated with the outer air inlet channel is arranged between the on-duty nozzle tube bundle region and the main combustion nozzle tube bundle region, the on-duty air inlet channel is communicated with an air distribution cavity wrapping the on-duty nozzle tube bundle region, and a plurality of axial swirl blades for improving the air flow intensity of the on-duty air inlet channel are arranged in the on-duty air inlet channel;
The burner is provided with a fuel supply area in the direction opposite to the nozzle tube bundle area, the fuel supply area comprises an on-duty fuel cavity for providing fuel for the on-duty nozzle tube bundle area and a main combustion stage fuel cavity for providing fuel for the main combustion stage nozzle tube bundle area, a class-value fuel tube is arranged in the on-duty fuel cavity, and a main combustion stage fuel tube is arranged in the main combustion stage fuel cavity.
2. The micro premix gas turbine combustor as recited in claim 1, wherein: the inner diameter of the nozzle tube bundle in the nozzle tube bundle area is 5-12 mm.
3. The micro premix gas turbine combustor as recited 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.
4. The micro premix gas turbine combustor as recited in claim 1, wherein: the flame tube forms an on-duty combustion zone in a zone communicated with the on-duty nozzle tube bundle zone, and forms a main combustion zone in a zone communicated with the main combustion nozzle tube bundle zone.
5. The micro premix gas turbine combustor as recited in claim 1, wherein: the air inlet is arranged on the outer shell body and is close to the flue gas outlet end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210656807.5A CN114992672B (en) | 2022-06-11 | 2022-06-11 | Micro-premixing type combustion chamber of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210656807.5A CN114992672B (en) | 2022-06-11 | 2022-06-11 | Micro-premixing type combustion chamber of gas turbine |
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| CN114992672A CN114992672A (en) | 2022-09-02 |
| CN114992672B true CN114992672B (en) | 2024-04-26 |
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| CN202210656807.5A Active CN114992672B (en) | 2022-06-11 | 2022-06-11 | Micro-premixing type combustion chamber of gas turbine |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115451433B (en) * | 2022-09-22 | 2024-04-02 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle premixing system for combustion chamber of gas turbine |
| 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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| CN1401938A (en) * | 2001-08-29 | 2003-03-12 | 株式会社日立制作所 | Burner of gas turbine and its operation method |
| CN102032597A (en) * | 2010-11-29 | 2011-04-27 | 北京航空航天大学 | Premixing pre-vaporization combustion chamber for main combustible stage of discrete pipe |
| CN103388838A (en) * | 2012-05-10 | 2013-11-13 | 通用电气公司 | System and method having multi-tube fuel nozzle with differential flow |
| CN103343985A (en) * | 2013-06-21 | 2013-10-09 | 北京航空航天大学 | Double-pre-film pneumatic nebulization low pollution combustor head structure |
| CN105716119A (en) * | 2016-03-22 | 2016-06-29 | 北京航空航天大学 | Lean direct injection low-emission combustor adopting effervescent atomizers |
| CN108626749A (en) * | 2018-03-16 | 2018-10-09 | 南京航空航天大学 | A kind of 7 points of oil-poor direct injection heads for low pollution combustor |
| CN108980891A (en) * | 2018-04-27 | 2018-12-11 | 北京航空航天大学 | A kind of center classification low emission combustor head with pneumatic water conservancy diversion and anti-backfire structure |
| CN109611891A (en) * | 2018-12-16 | 2019-04-12 | 中国航发沈阳发动机研究所 | A kind of dry low emission combustor |
| CN110131750A (en) * | 2019-04-26 | 2019-08-16 | 沈阳航空航天大学 | A kind of gas turbine low discharging burning chamber of using gas fuel |
| 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 |
| CN111928295A (en) * | 2020-09-08 | 2020-11-13 | 中国科学院工程热物理研究所 | Micro-premixing on-duty nozzle assembly and micro-premixing combustion chamber of 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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