CN115597088A - Combustion chamber structure and combustion regulation and control method - Google Patents
Combustion chamber structure and combustion regulation and control method Download PDFInfo
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- CN115597088A CN115597088A CN202211381773.XA CN202211381773A CN115597088A CN 115597088 A CN115597088 A CN 115597088A CN 202211381773 A CN202211381773 A CN 202211381773A CN 115597088 A CN115597088 A CN 115597088A
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 416
- 238000000034 method Methods 0.000 title claims abstract description 19
- 239000000446 fuel Substances 0.000 claims abstract description 375
- 238000009792 diffusion process Methods 0.000 claims abstract description 120
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 claims abstract description 57
- 230000010355 oscillation Effects 0.000 claims abstract description 14
- 239000007789 gas Substances 0.000 claims description 58
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 40
- 239000001257 hydrogen Substances 0.000 claims description 35
- 229910052739 hydrogen Inorganic materials 0.000 claims description 35
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 24
- 238000001816 cooling Methods 0.000 claims description 19
- 238000002347 injection Methods 0.000 claims description 17
- 239000007924 injection Substances 0.000 claims description 17
- 238000004891 communication Methods 0.000 claims description 15
- 230000002093 peripheral effect Effects 0.000 claims description 9
- 238000009826 distribution Methods 0.000 claims description 8
- 230000000670 limiting effect Effects 0.000 claims description 8
- 230000000694 effects Effects 0.000 claims description 5
- 230000009471 action Effects 0.000 claims description 2
- 239000007921 spray Substances 0.000 claims description 2
- 239000003570 air Substances 0.000 description 142
- 230000002829 reductive effect Effects 0.000 description 11
- 238000010248 power generation Methods 0.000 description 8
- 239000003345 natural gas Substances 0.000 description 7
- 230000001276 controlling effect Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 230000001105 regulatory effect Effects 0.000 description 5
- 238000005496 tempering Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 239000002131 composite material Substances 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 230000002401 inhibitory effect Effects 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 238000000563 Verneuil process Methods 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 239000000112 cooling gas Substances 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
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- 238000002679 ablation Methods 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
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- 238000009828 non-uniform distribution Methods 0.000 description 1
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Images
Classifications
-
- 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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Abstract
The invention discloses a combustion chamber structure and a combustion regulation and control method, wherein the combustion chamber structure comprises a plurality of micro-mixing combustors, and each micro-mixing combustor comprises a plurality of unit micro-mixing nozzles, a central diffusion combustion nozzle and a combustor shell; a plurality of independent fuel chambers are arranged in the combustor shell, the fuel chambers are configured to be filled with fuel, a first part of the fuel chambers are communicated with the unit micro-mixing nozzles, and a second part of the fuel chambers are communicated with the central diffusion combustion nozzle; the combustion chamber structure can effectively improve the flame stability, reduce the emission of nitrogen oxides and effectively inhibit thermoacoustic oscillation.
Description
Technical Field
The invention belongs to the technical field of combustion of gas turbines, and particularly relates to a combustion chamber structure and a combustion regulation and control method.
Background
Aeroderivative gas turbines are widely used in distributed power generation, ship propulsion, gas compression, ocean platform power generation and other occasions. In gas turbine design, nitrogen oxide emissions are a concern.
In the related art, in order to reduce the emission of nitrogen oxides, lean premixed combustion is often adopted to control the flame temperature, but the lean premixed combustion is close to a flameout boundary, so that the combustion stability is poor, and the flameout is very easy. Therefore, in the design of a gas turbine, the problem of easy flameout needs to be solved on the basis of meeting the emission of nitrogen oxides.
Disclosure of Invention
The present invention provides a combustion chamber structure and a combustion regulation method, which at least partially solve the above technical problems.
One aspect of the present invention provides a combustion chamber structure, including a plurality of micro-hybrid combustors, wherein the plurality of micro-hybrid combustors are circumferentially distributed along a combustion chamber space, and each micro-hybrid combustor includes a plurality of unit micro-hybrid nozzles, a central diffusion combustion nozzle, and a combustor casing.
Wherein the unit micro-mixing nozzle is used for realizing the premixed combustion of fuel and air in the combustion chamber; the central diffusion combustion nozzle is used for realizing diffusion combustion of fuel and air in the combustion chamber; a plurality of independent fuel chambers are arranged in the combustor shell and are configured to be filled with fuel, a first part of the fuel chambers are communicated with the unit micro-mixing nozzles, and a second part of the fuel chambers are communicated with the central diffusion combustion nozzle.
According to an embodiment of the present invention, the combustion chamber structure further includes a plurality of helmholtz resonators, wherein the plurality of helmholtz resonators are distributed and arranged along a circumferential direction of the combustion chamber space.
According to an embodiment of the present invention, the plurality of micro-hybrid burners includes a plurality of long-sector micro-hybrid burners, a plurality of short-sector micro-hybrid burners, the short-sector micro-hybrid burners having a length less than that of the long-sector micro-hybrid burners; a short fan-shaped micro-mixing combustor and a Helmholtz resonator form a combined unit, and in any combined unit, the short fan-shaped micro-mixing combustor and the Helmholtz resonator are distributed along the radial direction of the combustion chamber; the long fan-shaped micro-mixing combustors and the combined units are alternately distributed and arranged along the circumferential direction of the combustion chamber space.
According to an embodiment of the invention, the burner housing comprises a first type burner housing that mates with the long sector micro-hybrid burner, wherein the first type burner housing comprises a first fuel chamber, a second fuel chamber, and a third fuel chamber; the multiple unit micro-mixing nozzles in the long fan-shaped micro-mixing combustor form a first nozzle group and a second nozzle group, the central diffusion combustion nozzles and the second nozzle group in the first nozzle group and the long fan-shaped micro-mixing combustor are arranged along the radial direction from outside to inside of the combustion chamber, and the central diffusion combustion nozzles and the second nozzle group in the first nozzle group and the long fan-shaped micro-mixing combustor are respectively communicated with the first fuel chamber, the second fuel chamber and the third fuel chamber; the combustor shell comprises a second type combustor shell which is matched with the short fan-shaped micro-mixing combustor, wherein the second type combustor shell comprises a fourth fuel chamber and a fifth fuel chamber; a plurality of unit micro-mixing nozzles in the short fan-shaped micro-mixing combustor form a third nozzle group, central diffusion combustion nozzles in the third nozzle group and the short fan-shaped micro-mixing combustor are arranged along the radial direction from outside to inside of the combustion chamber, and the central diffusion combustion nozzles in the third nozzle group and the short fan-shaped micro-mixing combustor are respectively communicated with the fourth fuel chamber and the fifth fuel chamber.
According to the embodiment of the invention, along the radial direction of the combustion chamber, the combustion zone of the combustion chamber is divided into a plurality of sub-combustion zones, and the plurality of sub-combustion zones comprise a first combustion zone, a second combustion zone and a third combustion zone which are sequentially distributed along the radial direction of the combustion chamber; the central diffusion combustion nozzle and the second nozzle group in the first nozzle group and the long fan-shaped micro-mixing combustor respectively correspond to the first combustion area, the second combustion area and the third combustion area; and the central diffusion combustion nozzles in the third nozzle group and the short fan-shaped micro-mixing combustor respectively correspond to the first combustion area and the second combustion area.
According to the embodiment of the invention, a first fuel flow cavity channel communicated with the first fuel chamber, a second fuel flow cavity channel communicated with the second fuel chamber and a third fuel flow cavity channel communicated with the third fuel chamber are also arranged in the first type combustor shell; and a fourth fuel flowing cavity channel communicated with the fourth fuel cavity and a fifth fuel flowing cavity channel communicated with the fifth fuel cavity are also arranged in the second type combustor shell.
According to an embodiment of the invention, the combustion chamber is an annular combustion chamber, and the combustion chamber structure further comprises a peripheral wall assembly, an inner wall assembly and an air inlet end component.
The outer wall assembly and the inner wall assembly are in concentric annular wall structures, an annular combustion chamber is formed by enclosing the outer wall assembly and the inner wall assembly, and a plurality of micro-mixing burners are arranged between the outer wall assembly and the inner wall assembly so as to divide the annular combustion chamber into a flame tube head air inlet area and a combustion area by the micro-mixing burners; the inlet end member is in communication with the liner head inlet region and is configured to communicate air to the liner head inlet region such that at least a portion of the air in the liner head inlet region enters the plurality of unit micro-mixing nozzles.
According to the embodiment of the invention, the unit micro-mixing nozzle comprises a nozzle shell, wherein a fuel inlet cavity and a pre-mixing cavity which are independent from each other are arranged in the nozzle shell, the fuel inlet cavity is communicated with the pre-mixing cavity through a fuel injection hole, the fuel inlet cavity is communicated with the first part of fuel cavity and is configured to be filled with fuel, an air inlet hole is arranged in the cavity wall of the pre-mixing cavity, the air inlet hole is communicated with an air inlet area at the head part of the flame tube and is configured to be filled with air, and the outlet end of the pre-mixing cavity is communicated with a combustion area of a combustion chamber; wherein, in the unit micro-mixing nozzle, the premixing chamber is used for: the air entering through the air inlet hole and the fuel from the fuel inlet cavity are mixed to form premixed gas, and the premixed gas is injected to the combustion area to realize premixed combustion of the fuel and the air in the combustion chamber.
According to an embodiment of the invention, nozzle cooling film holes are provided in the chamber wall near the outlet end of the premixing chamber.
According to the embodiment of the invention, the nozzle shell adopts a circular tubular structure; the fuel inlet cavity comprises a section of circular tube-shaped air inlet pipe with a closed tail end, and the air inlet pipe and the nozzle shell are coaxially arranged so that an annular premixing cavity is formed between the outer surface of the air inlet pipe and the inner surface of the nozzle shell;
the front end of the air inlet pipe is provided with a fuel injection hole, and the tail end of the air inlet pipe is provided with a concave central body.
According to an embodiment of the invention, the air inlet holes comprise a primary air inlet hole and a secondary air inlet hole, the primary air inlet hole and the secondary air inlet hole being arranged in the direction of flow of the gas in the premixing chamber.
According to an embodiment of the present invention, a central diffusion combustion nozzle includes a sleeve, a fuel injector head; the sleeve is provided with an air inlet and a diffusion gas outlet, the air inlet is communicated with the air inlet area at the head of the flame tube and is configured to be filled with air, and the diffusion gas outlet is communicated with the combustion area of the combustion chamber;
the inlet end of the fuel nozzle is communicated with the second part of the fuel chamber, so that fuel from the second part of the fuel chamber is introduced into the fuel nozzle, the outlet end of the fuel nozzle is provided with a fuel injection hole, and the fuel nozzle is communicated with the sleeve through the fuel injection hole; wherein the central diffusion combustion nozzle is configured to: the air entering through the air inlet and the fuel sprayed in through the fuel nozzle are sprayed into a combustion area of the combustion chamber through a diffusion gas outlet of the sleeve after the diffusion effect of the sleeve, so that the diffusion combustion of the fuel and the air in the combustion chamber is realized.
According to an embodiment of the present invention, the central diffusion combustion nozzle further comprises a venturi disposed within the sleeve, the fuel injector head and the venturi communicating through the fuel injection hole.
According to an embodiment of the invention, the central diffusion combustion nozzle further comprises a swirl cup arranged at the air inlet of the sleeve such that the air, after entering, forms a swirl in the sleeve.
According to an embodiment of the invention, the peripheral wall assembly includes an outer casing and a liner outer ring; the inner surrounding wall component comprises an inner casing and a flame tube inner ring; the outer ring of the flame tube, the inner ring of the flame tube and the micro-mixing burners are enclosed to form a combustion area; the inlet section of the outer casing, the inlet section of the inner casing and the micro-mixing burners are enclosed to form a flame tube head air inlet area.
According to the embodiment of the invention, an outer cavity channel is formed by enclosing the outer casing and the outer ring of the flame tube; an inner ring cavity channel is formed by enclosing the inner casing and the inner ring of the flame tube; the outer ring cavity channel and the inner ring cavity channel are respectively communicated with the flame tube head air inlet area, so that at least part of air in the flame tube head air inlet area is cooled after entering the outer ring cavity channel and is cooled for the flame tube outer ring, and the inner ring cavity channel is cooled for the flame tube inner ring.
According to the embodiment of the invention, the air inlet end component comprises a diffuser, the outlet of the diffuser is connected with the inlet section of the outer casing and the inlet section of the inner casing, and the inlet of the diffuser is communicated with the outside.
According to an embodiment of the invention, the outlet section of the diffuser is provided with flow guiding ribs.
According to an embodiment of the invention, the combustion chamber structure further comprises a liner head end wall disposed between the liner outer ring and the liner inner ring, the liner head end wall configured to fixedly mount the plurality of micro-hybrid burners; the end wall of the head of the flame tube is provided with a plurality of flame tube gas film cooling holes.
According to an embodiment of the invention, the central axis of the liner film cooling holes is non-parallel to the central axis of the annular combustor.
According to the embodiment of the invention, the outer casing is provided with the burner mounting seat, and the micro-mixing burner is detachably and fixedly arranged on the end wall of the head part of the flame tube through the burner mounting seat.
According to an embodiment of the present invention, a helmholtz resonator includes a cylindrical resonator case, a spiral plate, a first cover plate, and a second cover plate. A resonant cavity is formed in the resonator shell; the spiral plate is arranged in the resonant cavity; the first cover plate and the second cover plate are respectively arranged at two ends of the resonator shell, wherein a plurality of first through holes are formed in the first cover plate, and a plurality of second through holes are formed in the second cover plate; the Helmholtz resonator is used for enabling air to enter the resonant cavity through the first through hole and flow out of the resonant cavity through the second through hole after passing through the spiral plate.
According to an embodiment of the present invention, the first through-holes and the second through-holes are arranged in a non-uniform distribution in the first cover plate and the second cover plate, respectively; the central axes of the first through hole and the second through hole are not parallel to the central axis of the resonator shell.
Another aspect of the present invention provides a method for regulating and controlling combustion by using the combustion chamber structure, including:
in the ignition starting stage, introducing fuel and air into the central diffusion combustion nozzle to realize diffusion combustion of the fuel and the air in the combustion chamber, wherein the fuel introduced in the ignition starting stage comprises methane;
stopping introducing fuel and air into the central diffusion combustion nozzle in a first load working stage, and introducing the fuel and the air into part of nozzles in the plurality of unit micro-mixing nozzles to realize premixed combustion of the fuel and the air in the combustion chamber, wherein the fuel introduced in the first load working stage comprises hydrogen or hydrogen-containing fuel;
in a second load working stage, introducing fuel and air into all the nozzles in the plurality of unit micro-mixing nozzles to realize premixed combustion of the fuel and the air in the combustion chamber, wherein the introduced fuel in the second load working stage comprises hydrogen or hydrogen-containing fuel;
in a third load working stage, introducing fuel and air into part or all of the central diffusion combustion nozzle and the plurality of unit micro-mixing nozzles to realize diffusion combustion and premixed combustion of the fuel and the air in the combustion chamber, wherein in the third load working stage, the fuel introduced into the central diffusion combustion nozzle and the unit micro-mixing nozzles comprises hydrogen or hydrogen-containing fuel;
and the load of the first load working stage is smaller than that of the second load working stage, and the load of the second load working stage is smaller than that of the third load working stage.
According to an embodiment of the present invention, the method further includes:
in the third load working stage, the diffusion premixed fuel ratio is adjusted to meet the preset nitrogen oxide emission limiting condition and the preset thermoacoustic oscillation limiting condition of the combustion chamber, wherein the diffusion premixed fuel ratio is as follows: the ratio of the flow rate of fuel introduced into the central diffusion combustion nozzle to the flow rate of fuel introduced into the unit micro-mixing nozzles.
Drawings
FIG. 1 is a schematic view of a distribution structure of a plurality of micro-hybrid burners in a combustion chamber according to an embodiment of the invention;
FIG. 2 is a schematic view of the internal structure of a long sector micro-hybrid combustor according to an embodiment of the present invention;
FIG. 3 is a schematic view of a flow channel configuration within an elongated fan micro-hybrid combustor in accordance with an embodiment of the present invention;
FIG. 4 is a schematic structural view of a combustor structure according to an embodiment of the present invention;
FIG. 5 is a schematic structural view of a unit micro-mixing nozzle according to an embodiment of the present invention;
FIG. 6 is a schematic structural view of a unit micro-mixing nozzle according to another embodiment of the present invention;
FIG. 7 is a schematic illustration of a center diffusion combustion nozzle configuration according to an embodiment of the present invention;
FIG. 8 is a schematic diagram of a Helmholtz resonator according to an embodiment of the invention;
FIG. 9 is a system schematic of a gas turbine power generation system according to an embodiment of the invention;
FIG. 10 is a schematic diagram of a method of combustion regulation according to an embodiment of the present invention.
Description of reference numerals:
1. a gas compressor;
2. a combustion chamber;
200. a combustion zone;
2001. a first combustion zone;
2002. a second combustion zone;
2003. a third combustion zone;
201. a flame tube head air inlet zone;
202. an outer annular channel;
203. an inner annular cavity channel;
21. a diffuser;
211. flow guiding ribs;
22. an outer case;
221. a burner mount;
23. an inner case;
24. a flame tube head end wall;
241. mounting holes;
242. a flame tube film cooling hole;
25. an outer ring of the flame tube;
26. an inner ring of the flame tube;
27A, a long fan-shaped micro-mixing burner;
27B, a short fan-shaped micro-mixing burner;
271. a flange mounting edge;
272. a burner housing;
2721. a first fuel flow channel;
2722. a second fuel flow channel;
2723. a third fuel flow channel;
2724. a first fuel chamber;
2725. a second fuel chamber;
2726. a third fuel chamber;
273. a unit micro-mixing nozzle;
27301. a first nozzle group;
27302. a second nozzle group;
2731. a nozzle housing;
2732. a fuel intake chamber;
2733. a fuel injection hole;
2734. a primary air inlet;
2735. a secondary air inlet;
2736. a premixing chamber;
2737. nozzle cooling film holes;
2738. a concave central body;
274. a central diffusion combustion nozzle;
2741. a sleeve;
2742. a vortex cup;
2743. a fuel injector;
2744. a venturi;
275. a combustor end cover;
28. a Helmholtz resonator;
281. a first cover plate;
282. a resonator housing;
283. a second cover plate;
284. a resonant cavity;
285. a spiral plate;
286. a first through hole;
287. a second through hole;
29. an igniter;
3. a turbine;
4. a generator;
5. starting the motor;
f1, a first fuel;
f2, a second fuel;
f3, a third fuel;
f4, fuel flow at the inlet of the unit micro-mixing nozzle;
f5, accelerating the post-combustion fuel flow by the unit micro-mixing nozzle;
a0, ambient air;
a1, high-pressure air at an outlet of a compressor;
a2, air in an air inlet area at the head of the flame tube;
a3, outer ring cooling air flow;
a4, cooling the air flow of the inner ring;
a5, combusting the reaction air flow;
g1, high-temperature fuel gas;
g2, tail gas;
p1, premix gas.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the accompanying drawings in combination with the embodiments.
Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings. It is to be understood that such description is merely illustrative and not intended to limit the scope of the present invention. In the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the invention. It may be evident, however, that one or more embodiments may be practiced without these specific details. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.
All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.
In those instances where a convention analogous to "at least one of A, B, and C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B, and C" would include but not be limited to systems that have A alone, B alone, C alone, A and B together, A and C together, B and C together, and/or A, B, and C together, etc.). In those instances where a convention analogous to "at least one of A, B, or C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B, or C" would include but not be limited to systems that have A alone, B alone, C alone, A and B together, A and C together, B and C together, and/or A, B, and C together, etc.).
The conventional gas turbine mostly uses natural gas as a main fuel component, but the combustion of the natural gas cannot avoid generating a large amount of carbon dioxide emission, so that the carbon-free fuel for replacing the natural gas is urgently needed to be found. Hydrogen is a carbon-free fuel with higher heat value and has great potential as a main fuel of a gas turbine in a new era. Combining hydrogen energy with gas turbine technology, gas turbine carbon emissions can be greatly reduced by using clean hydrogen-rich/hydrogen fuel instead of natural gas as fuel. When the hydrogen percentage reaches 80%, the carbon emission can be reduced by about 50%.
However, the chemical reaction activity of hydrogen is higher, and the traditional gas turbine combustion chamber directly burns hydrogen fuel, so that the tempering problem is more likely to occur compared with natural gas, the heat-affected zone of the head part of the combustion chamber is affected, and the service life of the combustion chamber is reduced; meanwhile, the high flame adiabatic temperature is easy to cause high temperature in a local range, so that the emission of nitrogen oxides is improved, and the hydrogen gas turbine is also a great difference from the traditional gas turbine.
In the related art, a gas turbine operating on natural gas generally adopts a swirl premixing structure in order to reduce nitrogen oxide emission, and strong turbulence shearing action is generated by swirl to promote fuel and air to be fully mixed in a premixing mixing section, and then the fuel and the air are sent into a combustion chamber to realize space homogeneous combustion, so that the nitrogen oxide emission is suppressed. However, when the hydrogen content in the fuel is increased, the partial combustion temperature may be too high due to the higher adiabatic flame temperature of hydrogen compared to natural gas, thereby increasing nitrogen oxide emissions. In addition, hydrogen has extremely high flame propagation speed, and the flame of the hydrogen can propagate upstream and be stabilized in the nozzle, so that the phenomena of tempering and fire hanging occur, and the safe operation of the combustor is influenced; moreover, the rotational flow premixing combustion chamber also frequently faces the problem of thermoacoustic oscillation, and the mechanical structures of the combustor and the flame tube can be damaged when the low-frequency large-amplitude pressure oscillation is serious, so that the safe operation of the combustion chamber is seriously threatened; finally, low emission control of the gas turbine is realized, the combustion chamber generally adopts a lean premixed combustion technology, but the temperature of a combustion area is directly lower, so that the combustion stability is poor, and the risk of flameout is easy to occur.
Therefore, in view of the above problems, it is desirable to design a gas turbine combustor system (including a combustor and a combustor nozzle) that can simultaneously address the above problems. The redesign of the combustor needs to consider not only the anti-backfire and low-emission design of the combustor, but also the requirements of the overall design of the combustion chamber, including the adjusting capability of different loads of the combustion engine, the capability of inhibiting the instability of the heat sound, the outlet temperature distribution uniformity index and the lower pressure loss coefficient.
In view of the above, embodiments of the present invention provide a combustion chamber structure, which includes a plurality of micro-hybrid combustors, wherein the plurality of micro-hybrid combustors are arranged circumferentially along a combustion chamber space.
Each micro-hybrid combustor includes a plurality of unit micro-hybrid nozzles, a central diffusion combustion nozzle, a combustor casing.
Wherein the unit micro-mixing nozzle is used for realizing the premixed combustion of fuel and air in the combustion chamber; the central diffusion combustion nozzle is used for realizing diffusion combustion of fuel and air in the combustion chamber; a plurality of independent fuel chambers are arranged in the combustor shell and are configured to be filled with fuel, a first part of the fuel chambers are communicated with the unit micro-mixing nozzles, and a second part of the fuel chambers are communicated with the central diffusion combustion nozzle.
FIG. 1 is a schematic view of a distribution structure of a plurality of micro-hybrid burners in a combustion chamber according to an embodiment of the invention; fig. 2 is a schematic view of the internal structure of a long-sector micro-hybrid combustor 27A according to an embodiment of the present invention.
As shown in fig. 1 and fig. 2, the combustion chamber structure of the embodiment of the present invention includes a plurality of micro-hybrid burners (a plurality of long-sector micro-hybrid burners 27A and a plurality of short-sector micro-hybrid burners 27B as shown in fig. 1), wherein the plurality of micro-hybrid burners are arranged in a circumferential distribution along the combustion chamber space.
Wherein in each micro-hybrid burner, there are a plurality of unit micro-hybrid nozzles 273 and a central diffusion combustion nozzle 274. Wherein the unit micro-mixing nozzles 273 are used to achieve premixed combustion of fuel and air within the combustion chamber; the central diffusion combustion nozzle 274 is used to effect diffusion combustion of fuel and air within the combustion chamber.
As shown in fig. 2, the micro-hybrid combustor further includes a combustor housing 272, and a plurality of independent fuel chambers are disposed in the combustor housing 272, and as shown in fig. 2, a first fuel chamber 2724, a second fuel chamber 2725, and a third fuel chamber 2726 are disposed in the combustor housing 272. The fuel chambers are configured to be vented with fuel, with a portion of the plurality of fuel chambers in communication with the plurality of unit micro-mixing nozzles 273 and the remaining portion of the fuel chambers in communication with the central diffusion combustion nozzle 274. As shown in fig. 2, the first fuel chamber 2724 and the third fuel chamber 2726 communicate with the plurality of unit micro-mixing nozzles 273 and the second fuel chamber 2725 communicates with the central diffusion combustion nozzle 274.
In a micro-hybrid combustor, according to an embodiment of the present invention, the dimensions of the unit micro-mixing nozzle 273 are small, for example in the range of 5 to 15mm in diameter. The micro-mixing burner is used for replacing the traditional swirl premixing burner and consists of a plurality of unit micro-mixing nozzles 273, the unit micro-mixing nozzles 273 can realize premixing combustion of fuel and air in a combustion chamber, mixing under a smaller scale is realized, mixing efficiency can be improved, the fuel and the air are fully mixed in the unit micro-mixing nozzles 273, and accordingly the uniformity of flame temperature in a flame tube is improved; moreover, because the plurality of unit micro-mixing nozzles 273 are distributed in an array manner, and each nozzle outlet can generate relatively independent small flames, the generation of high-temperature areas in the flame tube can be avoided, the temperature distribution of the outlet of the combustion chamber can be more uniform, the peak temperature of the flames is reduced, and the emission of nitrogen oxides is inhibited; the small flame formed by the unit micro-mixing nozzle 273 has smaller size, and plays a positive role in shortening the length of the flame tube of the combustion chamber; the outlet of the unit micro-mixing nozzle 273 has higher jet speed, and the tempering phenomenon during the combustion of the fuel with high hydrogen content can be effectively inhibited.
According to the embodiment of the invention, a plurality of independent fuel cavities are arranged in the combustor shell 272, and each cavity can be independently supplied with fuel, so that staged combustion is facilitated, and the change of the working condition of the combustion chamber from low load to high load can be adapted.
Problems encountered with lean premixed combustion technologies according to embodiments of the present invention are reduced combustion stability, flashback in the premix chamber and flameout from load changes or changes in fuel calorific value and composition, and large thermoacoustic oscillations. In the micro-hybrid combustor of the embodiment of the invention, on the basis of reducing the tempering problem of the lean-burn premixed combustion technology by using the unit micro-mixing nozzle 273, the central diffusion combustion nozzle 274 is introduced and used for realizing the diffusion combustion of fuel and air in the combustion chamber, because the diffusion combustion flame has high stability and the thermoacoustic oscillation is low, the flame stability can be effectively improved by introducing the central diffusion combustion nozzle 274, and meanwhile, the composite flame consisting of premixed combustion flame and diffusion combustion flame with different layering ratios can be formed conveniently and subsequently by regulating and controlling the fuel ratio entering the unit micro-mixing nozzle 273 and the central diffusion combustion nozzle 274, and the composite flame has stronger capability of inhibiting the thermoacoustic oscillation than the pure premixed flame.
According to an embodiment of the present invention, the combustion chamber structure further comprises a plurality of helmholtz resonators 28, wherein the plurality of helmholtz resonators 28 are distributed and arranged along the circumferential direction of the combustion chamber space. Through setting up helmholtz resonator 28, can change the natural acoustic frequency of flame tube and absorb the sound wave and vibrate the energy to effectively slow down the heat and sound and vibrate the problem.
According to an embodiment of the present invention, as shown in fig. 1, the above-described combustor structure further comprises a liner head end wall 24, the liner head end wall 24 being configured to fixedly mount a plurality of micro-hybrid burners.
The end cover of the micro-mixing burner is of a fan-shaped structure and is divided into a long fan-shaped micro-mixing burner 27A and a short fan-shaped micro-mixing burner 27B according to the size of the fan-shaped structure, and the length of the short fan-shaped micro-mixing burner 27B is smaller than that of the long fan-shaped micro-mixing burner 27A; the combustor liner head end wall 24 is provided with a mounting hole 241 for mounting the helmholtz resonator 28 at a position corresponding to each short fan-shaped micro-hybrid burner 27B.
Wherein, one short fan-shaped micro-mixing burner 27B and one helmholtz resonator 28 form one combined unit, and in any combined unit, the short fan-shaped micro-mixing burner 27B and the helmholtz resonator 28 are distributed along the radial direction of the combustion chamber; the long fan-shaped micro-hybrid burners 27A and the combined units are alternately arranged in the circumferential direction of the combustion chamber space.
According to an embodiment of the present invention, the burner housing 272 also includes a first type of burner housing that mates with the long sector micro-hybrid burner 27A, a second type of burner housing that mates with the short sector micro-hybrid burner 27B, based on the different types of micro-hybrid burners including the long sector micro-hybrid burner 27A, the short sector micro-hybrid burner 27B.
As shown in fig. 2, the first type of burner housing includes a first fuel chamber 2724, a second fuel chamber 2725, and a third fuel chamber 2726; the first and third fuel chambers 2724 and 2726 are in communication with the plurality of unit micro-mixing nozzles 273 and the second fuel chamber 2725 is in communication with the central diffusion combustion nozzle 274. Specifically, the plurality of unit micro-mixing nozzles 273 in the long fan micro-mixing combustor 27A form a first nozzle group 27301 and a second nozzle group 27302, the first nozzle group 27301, the central diffusion combustion nozzle 274 in the long fan micro-mixing combustor 27A, and the second nozzle group 27302 are arranged from the outside to the inside in the radial direction of the combustion chamber, and the first nozzle group 27301, the central diffusion combustion nozzle 274 in the long fan micro-mixing combustor 27A, and the second nozzle group 27302 are respectively communicated with the first fuel chamber 2724, the second fuel chamber 2725, and the third fuel chamber 2726. The first fuel chamber 2724, the second fuel chamber 2725 and the third fuel chamber 2726 are sequentially arranged along the radial direction of the combustion chamber, and correspond to the positions of the three nozzle groups one by one, so that a fuel supply passage can be optimized, and the air flow pressure loss of fuel in the passage can be reduced.
Fig. 3 is a schematic view of a flow channel structure in the long sector micro-hybrid combustor 27A according to an embodiment of the present invention.
As shown in fig. 2 and 3, a first fuel flow channel 2721 communicating with the first fuel chamber 2724, a second fuel flow channel 2722 communicating with the second fuel chamber 2725, and a third fuel flow channel 2723 communicating with the third fuel chamber 2726 are further provided in the first type burner housing. The first fuel flow channel 2721, the second fuel flow channel 2722, and the third fuel flow channel 2723 are configured to channel fuel into the three fuel chambers, respectively.
Specifically, fuel supplied from an external fuel line may enter the micro-hybrid combustor through the three separate fuel flow channels. The first fuel f1 entering from the first fuel flow chamber 2721 passes through the first fuel chamber 2724 and flows into the first nozzle group 27301. The secondary fuel entering from the secondary fuel flow channel 2722 passes through the secondary fuel chamber 2725 and then flows into the central diffusion combustion nozzle 274. The third fuel f3 entering from the third fuel flow channel 2723 passes through the third fuel chamber 2726 and flows into the second nozzle group 27302.
Further, the long sector micro-hybrid combustor 27A also includes a flange mounting edge 271 and a combustor end cover 275.
Furthermore, the second type of burner housing comprises a fourth fuel chamber, a fifth fuel chamber; the plurality of unit micro-mixing nozzles 273 in the short fan micro-mixing burner 27B form a third nozzle group, the central diffusion combustion nozzle 274 in the short fan micro-mixing burner 27B are arranged from outside to inside in the radial direction of the combustion chamber, and the central diffusion combustion nozzle 274 in the third nozzle group, the short fan micro-mixing burner 27B are respectively communicated with the fourth fuel chamber, the fifth fuel chamber. A fourth fuel flow channel communicated with the fourth fuel chamber and a fifth fuel flow channel communicated with the fifth fuel chamber are also arranged in the second type combustor shell. The embodiment of the present invention does not provide a schematic view of the internal structure of the short fan micro-hybrid burner 27B, which is similar to the long fan micro-hybrid burner 27A in general structure, and the internal structure thereof can be understood with reference to fig. 2 and 3 based on the structure shown in fig. 1.
Fig. 4 is a structural view of a combustion chamber structure according to an embodiment of the present invention.
The combustor structure according to the embodiment of the present invention may further be an annular combustor 2, as shown in fig. 4, the combustor structure further includes a peripheral wall assembly and an inner wall assembly, wherein the peripheral wall assembly and the inner wall assembly are concentrically arranged annular wall structures, the annular combustor 2 is formed by surrounding the peripheral wall assembly and the inner wall assembly, and a plurality of micro-mixing burners are disposed between the peripheral wall assembly and the inner wall assembly, so that the plurality of micro-mixing burners divide the annular combustor 2 into a torch head intake area 201 and a combustion area 200.
The combustor structure further includes an inlet end member in communication with the liner head inlet region 201 and configured to pass air into the liner head inlet region 201 such that at least a portion of the air in the liner head inlet region 201 enters the plurality of unit micro-mixing nozzles 273.
In the annular combustion chamber 2, the height of the flame tube in the radial direction is larger, and the thermoacoustic oscillation can be effectively weakened relative to the combustion chamber 2 with the smaller height of the flame tube.
According to the embodiment of the present invention, the combustion zone 200 of the combustion chamber 2 is divided into a plurality of sub-combustion zones including the first combustion zone 2001, the second combustion zone 2002 and the third combustion zone 2003, which are sequentially distributed in the radial direction of the combustion chamber 2, along the radial direction of the combustion chamber 2. The number of the sub-combustion zones can be set according to actual use requirements without being limited to the three sub-combustion zones.
Wherein the first nozzle group 27301, the central diffusion combustion nozzle 274 in the long fan micro-hybrid combustor 27A, and the second nozzle group 27302 correspond to the first combustion zone 2001, the second combustion zone 2002, and the third combustion zone 2003, respectively; the central diffusion combustion nozzles 274 in the third nozzle group, short fan micro-hybrid combustor 27B correspond to the first combustion zone 2001 and the second combustion zone 2002, respectively.
For example, for the long fan micro-hybrid combustor 27A, fuel supplied from an external fuel line enters the micro-hybrid combustor through three separate fuel flow channels. The first fuel f1 entering from the first fuel flow channel 2721 flows into the first nozzle group 27301 after passing through the first fuel chamber 2724, so that the first combustion zone 2001 can be separately supplied with fuel. The second fuel entering from the second fuel flow chamber 2722 may be separately fueled to the second combustion zone 2002 by passing through the second fuel chamber 2725 and then through the central diffusion combustion nozzle 274. The third fuel f3 entering from the third fuel flow housing 2723 flows through the third fuel plenum 2726 and into the second nozzle group 27302, which may separately provide fuel to the third combustion zone 2003.
Further in accordance with an embodiment of the present invention, the peripheral wall assembly includes an outer casing 22 and a liner outer ring 25; the inner surrounding wall component comprises an inner casing 23 and a flame tube inner ring 26; the outer ring 25 of the flame tube, the inner ring 26 of the flame tube and a plurality of micro-mixing burners are enclosed to form a combustion area 200; the inlet section of the outer casing 22, the inlet section of the inner casing 23, and the plurality of micro-hybrid burners enclose a flame tube head intake area 201.
An outer cavity 202 is formed between the outer casing 22 and the outer ring 25 of the flame tube for the outer air to flow. An inner ring cavity channel 203 is formed by the inner casing 23 and the inner flame tube ring 26 in an enclosing mode and can be used for air flowing in the inner ring. The outer ring cavity channel 202 and the inner ring cavity channel 203 are respectively communicated with the flame tube head air inlet area 201, so that at least part of air in the flame tube head air inlet area 201 enters the outer ring cavity channel 202 to cool the outer ring 25 of the flame tube and enters the inner ring cavity channel 203 to cool the inner ring 26 of the flame tube.
According to the embodiment of the invention, the air inlet end component comprises a diffuser 21, the diffuser 21 is positioned at the front end of the combustion chamber 2 and is of an annular expansion structure, the outlet of the diffuser 21 is connected with the inlet section of the outer casing 22 and the inlet section of the inner casing 23, and the inlet of the diffuser 21 is communicated with the outside. Specifically, the outer casing 22 is connected to the outer ring of the diffuser 21, and the outer casing and the diffuser together form the outer wall of the combustion chamber 2. The inner casing 23 is connected to the inner ring of the diffuser 21, and both of them together form the inner wall of the combustion chamber 2. The outlet section of the diffuser 21 is provided with guide ribs 211 for guiding the flow of the air stream.
According to an embodiment of the invention, the combustor structure further comprises a liner head end wall 24 disposed between the liner outer ring 25 and the liner inner ring 26, the liner head end wall 24 configured to fixedly mount a plurality of micro-hybrid burners; the outer casing 22 is provided with a burner mounting seat 221, and the micro mixing burner is detachably and fixedly mounted on the end wall 24 of the head of the flame tube through the burner mounting seat 221. Specifically, the micro-hybrid burner may be inserted into the head of the liner and secured through the burner mount 221 on the outer casing 22.
As shown in fig. 4, the combustion chamber structure includes a helmholtz resonator 28, an igniter 29, and the like in addition to the diffuser 21, the outer casing 22, the inner casing 23, the liner head end wall 24, the liner outer ring 25, the liner inner ring 26, the micro-hybrid combustor, and the like, which are listed above. The Helmholtz resonator 28 may be inserted into the mounting hole 241 of the liner head end wall 24 and secured. The igniter 29 is mounted on the outer casing 22 near the rear of the liner head end wall 24, with the forward end of the igniter 29 inserted into the combustion zone 200 inside the liner outer ring 25.
Further, a plurality of flame tube film cooling holes 242 are formed in the end wall 24 of the head of the flame tube, and the central axes of the flame tube film cooling holes 242 are not parallel to the central axis of the combustion chamber 2, and form a certain inclination angle with the flame tube axis, after the air in the head of the flame tube air intake region 201 passes through the inclined flame tube film cooling holes 242, an air film layer is formed on the wall surface of the end wall 24 of the head of the flame tube, which is close to one side of the combustion region 200, so as to cool the surface, so that the head of the flame tube is prevented from high-temperature ablation of the end wall 24 of the head of the flame tube, and meanwhile, the cooling gas can cool the main flame generated by the micro-mixing combustor in the high-temperature combustion region 200, and the flame temperature is reduced, so that the emission of nitrogen oxides is stabilized in a lower range.
FIG. 5 is a schematic diagram of a configuration of a unit micro-mixing nozzle 273 according to one embodiment of the present invention.
As shown in fig. 5, the unit micro-mixing nozzle 273 includes a nozzle housing 2731, wherein a fuel inlet chamber 2732 and a pre-mixing chamber 2736 are provided in the nozzle housing 2731, the fuel inlet chamber 2732 and the pre-mixing chamber 2736 are connected through a fuel injection hole 2733, the fuel inlet chamber 2732 is connected to the first part of the fuel chambers and is configured to be filled with fuel, an air inlet hole is provided in a wall of the pre-mixing chamber 2736 and is connected to the flame tube head inlet area 201 and is configured to be filled with air, and an outlet end of the pre-mixing chamber 2736 is connected to the combustion area 200 of the combustion chamber 2.
Wherein, in the unit micro-mixing nozzle 273, the pre-mixing chamber 2736 is used to: the air entering through the air intake holes and the fuel originating from the fuel intake chamber 2732 are mixed to form a premixed gas, and the premixed gas is injected toward the combustion zone 200 to achieve premixed combustion of the fuel and the air in the combustion chamber 2.
As shown in FIG. 5, in the unit micro-mixing nozzle 273, the interior of the nozzle housing 2731 is divided into a fuel inlet chamber 2732 and a premixing chamber 2736 by a partition wall disposed inside the nozzle housing 2731, and one or more fuel injection holes 2733 are provided in the partition wall disposed inside the nozzle housing 2731 for the passage of fuel to form high velocity jets into the premixing chamber 2736.
According to an embodiment of the present invention, with the above-described structural arrangement, the air flow direction entering through the air intake holes forms a cross jet of fuel/air laterally with the fuel flow direction entering through the fuel injection holes 2733, promoting thorough mixing of the fuel and air within the unit micro-mixing nozzle 273 by strong turbulent interaction, thereby further reducing nitrogen oxide emissions.
According to an embodiment of the present invention, the air intake holes include primary air intake holes 2734 and secondary air intake holes 2735, the primary air intake holes 2734 and secondary air intake holes 2735 being disposed along a flow direction of the gas within the premixing chamber 2736. Providing two air intake ports at the same air intake port area allows for more uniform mixing of air and fuel than providing only one air intake port 2734. Because the two stages of air holes are arranged in a staggered mode in the circumferential direction, uniform air intake without dead angles in 360 degrees in the circumferential direction is guaranteed, and air and fuel are mixed more uniformly in the whole space.
Further, in accordance with an embodiment of the present invention, nozzle cooling film holes 2737 are provided in the chamber wall near the exit end of the premixing chamber 2736. The nozzle cooling gas film holes 2737 are arranged near the outlet of the nozzle shell 2731, and a plurality of layers are uniformly arranged along the circumferential direction, so that the wall temperature and the fuel/air ratio of the wall surface boundary layer can be reduced, the wall temperature is cooled, the boundary layer on the inner side of the wall is broken, the temperature of premixed gas in the premixing chamber 2736 is reduced, the anti-backfire and flame-catching performances of the nozzle can be further improved, and the safe operation of the combustor is ensured.
The mixing process performed in the unit micro-mixing nozzle 273 is: inside the unit micro-mixing nozzle 273, the fuel flow f4 at the inlet of the unit micro-mixing nozzle flowing from the fuel inlet chamber 2732 passes through the fuel injection hole 2733 to form a high-speed jet fuel-unit micro-mixing nozzle accelerated fuel flow f5; meanwhile, air (combustion reaction air flow a 5) enters the nozzle from multiple rows of circumferentially arranged multistage air inlet holes formed in the nozzle housing 2731, is rapidly mixed with the fuel flow f5 accelerated by the unit micro-mixing nozzle, and is subjected to multistage full mixing to form high-speed uniform premixed gas p1, and the premixed gas p1 can be ejected from the nozzle at a high speed and is combusted in the combustion zone 200. By employing the fuel/air cross-jet structure, thorough mixing of fuel and air within the unit micro-mixing nozzle 273 is facilitated through strong turbulent interaction, thereby improving uniformity of flame temperature within the liner, reducing flame peak temperature, and inhibiting nitrogen oxide emissions.
Fig. 6 is a schematic structural view of a unit micro-mixing nozzle 273 according to another embodiment of the present invention.
As shown in fig. 6, the nozzle housing 2731 has a circular tube shape, and the diameter of the nozzle housing 2731 is 5 to 15mm.
The construction of the unitary micro-mixing nozzle 273 of this embodiment is generally the same as that shown in the embodiment of FIG. 5, except that the fuel inlet chamber 2732 comprises a segment of a closed-end, circular-tube-shaped inlet tube coaxially disposed with the nozzle housing 2731 such that an annular pre-mixing chamber 2736 is formed between the outer surface of the inlet tube and the inner surface of the nozzle housing 2731; the front end of the inlet tube is provided with fuel injection holes 2733 and the end of the inlet tube is provided with a concave central body 2738.
The end of the concave central body 2738 is concave and curved, so that a backflow area which develops upstream cannot be generated, and when the front stagnation point of the backflow area reaches the concave surface, the backflow area cannot continue to develop upstream, so that the tempering risk of the nozzle is further reduced.
FIG. 7 is a schematic illustration of a center diffusion combustion nozzle 274 in accordance with an embodiment of the present invention.
As shown in FIG. 7, the central diffusion combustion nozzle 274 includes a sleeve 2741, a fuel bowl 2743.
Therein, the sleeve 2741 is provided with an air inlet in communication with the flame tube head intake zone 201 configured to let in air and a diffusion gas outlet in communication with the combustion zone 200 of the combustion chamber 2. The diffusion gas outlet of the sleeve 2741 is an expanding outlet to limit the radial expansion of the flame and provide space for the stagnation point in the recirculation zone.
The inlet end of the fuel injector 2743 is in communication with the second portion of the fuel chamber such that fuel from the second portion of the fuel chamber passes into the fuel injector 2743, the outlet end of the fuel injector 2743 is provided with fuel injector holes 1-3 mm in diameter, and the fuel injector 2743 and the sleeve 2741 are in communication through the fuel injector holes.
Wherein the central diffusion combustion nozzle 274 is used to: the air entering through the air inlet and the fuel injected through the fuel injector 2743 are injected into the combustion zone 200 of the combustion chamber 2 through the diffusion gas outlet of the shroud 2741 after diffusion by the shroud 2741 to achieve diffusion combustion of the fuel and air within the combustion chamber 2.
According to an embodiment of the present invention, the central diffusion combustion nozzle 274 further includes a venturi 2744 for further increasing the velocity of the gas flow diffusion and improving combustion stability, the venturi 2744 is disposed within a sleeve 2741, and the fuel nozzle 2743 and the venturi 2744 are in communication through a fuel injection hole.
The central diffusion combustion nozzle 274 also includes a swirl cup 2742, the swirl cup 2742 being positioned at the air inlet of the sleeve 2741 such that air enters to create a swirl within the sleeve 2741 to improve combustion stability.
Fig. 8 is a schematic structural diagram of the helmholtz resonator 28 according to an embodiment of the present invention.
As shown in fig. 8, the helmholtz resonator 28 includes a cylindrical resonator housing 282, a resonant cavity 284 is formed in the resonator housing 282, a spiral plate 285 is disposed in the resonant cavity 284, and the spiral plate 285 includes at least two turns.
The helmholtz resonator 28 further includes a first cover plate 281 and a second cover plate 283, which are respectively disposed at two ends of the resonator housing 282, wherein the first cover plate 281 is provided with a plurality of first through holes 286 therein, and the second cover plate 283 is provided with a plurality of second through holes 287 therein; the helmholtz resonator 28 is used for air from the torch head air inlet region 201 to enter the resonant cavity 284 through the first through hole 286, pass through the spiral plate 285, and flow out of the resonant cavity 284 through the second through hole 287. The spiral plate 285 increases the inner surface area of the resonant cavity 284, increases the flow stroke of the internal gas flow, and can effectively absorb the gas flow pulsation energy of the high-temperature gas in the high-temperature combustion area 200 and reduce thermoacoustic oscillation.
According to an embodiment of the present invention, the first through holes 286 and the second through holes 287 are arranged in a non-uniform and irregular distribution in the first cover plate 281 and the second cover plate 283, respectively; the center axes of the first through hole 286 and the second through hole 287 are not parallel to the center axis of the resonator housing 282, that is, both the first through hole 286 and the second through hole 287 may be oblique holes.
The center axes of the first through hole 286 and the second through hole 287 may be parallel to the center axis of the resonator case 282, that is, the first through hole 286 and the second through hole 287 may be straight holes.
In another aspect of the present invention, a gas turbine power generation system including the combustion chamber structure is provided, and fig. 9 is a system schematic diagram of the gas turbine power generation system according to the embodiment of the present invention.
As shown in fig. 9, the system includes a compressor 1, a combustion chamber 2, a turbine 3, a generator 4, a motor, and the like.
Wherein the compressor 1 is configured to compress air. The combustion chamber 2 communicates with the compressor 1 and is configured to be fed with fuel and air from the compressor 1 so that the fuel and air produce combustion gas at a predetermined temperature after combustion in the combustion chamber 2. The turbine 3 includes a turbine, wherein the turbine 3 is in communication with the combustion chamber 2 and is configured to rotate the turbine using combustion gas of a predetermined temperature derived from the combustion chamber 2. The generator 4 is mechanically connected to an output shaft of the turbine and configured to generate electric energy under the driving of the turbine.
Referring to fig. 4 and 9, the compressor 1 sucks and compresses atmospheric air (ambient air a 0) from the external environment, generates high-pressure air a1 at the outlet of the compressor 1 after compression, flows into the combustion chamber 2, and generates air a2 in the intake area at the head of the flame tube after further diffusion and speed reduction through the diffuser 21, wherein the air a2 is divided into three parts: a first stream of air (outer ring cooling air stream a 3) enters the outer ring cavity 202 for cooling the outer ring 25 of the liner; a second stream of air (inner ring cooling air stream a 4) enters the inner ring cavity channel 203 for cooling the inner liner ring 26; the first and second streams of air are cooling air that does not participate in combustion. The third air (combustion reaction air stream a 5) enters a plurality of unit micro-mixing nozzles 273, where it is thoroughly mixed with fuel from the fuel supply and then enters the combustion zone 200 for combustion. High-temperature gas g1 generated after combustion flows through a turbine and expands to do work, tail gas g2 generated after the work is done is discharged into the atmospheric environment, and the generator 4 generates electricity under the high-speed rotation driving of the turbine.
According to an embodiment of the present invention, as described in the foregoing embodiment, the combustion zone 200 of the combustion chamber 2 is divided into a plurality of sub-combustion zones including the first combustion zone 2001, the second combustion zone 2002, and the third combustion zone 2003, which are sequentially distributed in the radial direction of the combustion chamber 2, along the radial direction of the combustion chamber 2. Wherein the first nozzle group 27301, the central diffusion combustion nozzle 274 in the long fan micro-hybrid combustor 27A, and the second nozzle group 27302 correspond to the first combustion zone 2001, the second combustion zone 2002, and the third combustion zone 2003, respectively; the central diffusion combustion nozzles 274 in the third nozzle group, short fan micro-hybrid combustor 27B correspond to the first combustion zone 2001 and the second combustion zone 2002, respectively.
For the long fan micro-hybrid combustor 27A, fuel supplied from an external fuel line enters the micro-hybrid combustor through three separate fuel flow channels. The first fuel f1 entering from the first fuel flow channel 2721 flows into the first nozzle group 27301 after passing through the first fuel chamber 2724, so that the first combustion zone 2001 can be separately supplied with fuel. The second combustion zone 2002 may be separately fueled by a second fuel entering from a second fuel flow channel 2722 after passing through a second fuel chamber 2725 and then through the central diffusion combustion nozzle 274. The third fuel f3 entering from the third fuel flow channel 2723 may be separately supplied to the third combustion zone 2003 by flowing through the third fuel plenum 2726 and then into the second nozzle group 27302. The external fuel supply pipelines connected with the three independent fuel flow channels are provided with flow meters and regulating valves, so that the fuel flow entering different channels (chambers) is independently controllable.
A plurality of nozzle group and a plurality of sub-combustion area one-to-one in the annular combustion area 200, in the nozzle group, fuel and air mix and form after mixing gas in advance, and every nozzle group of accessible independent control can spray gas in advance to a plurality of sub-combustion areas respectively, realizes hierarchical subregion burning, through the burning of independent control subregion, can improve combustion stability, avoids the emergence of flame-out problem.
Specifically, during gas turbine startup, light-off, and low load conditions, due to the low overall fuel/air ratio of combustion zone 200, if fuel is dispersed into each sub-combustion zone at the same time, it is easily extinguished. If only a portion of the fuel passages are opened (e.g., only a portion of the nozzle groups are opened) so that all of the fuel involved in combustion enters the corresponding sub-combustion zones, the local fuel/air ratio of the combustion zone 200 can be greatly increased, and the combustion can be more stable. At this time, the combustion zone 200 acts as an "pilot burner" and the combustion in the combustion zone 200 is lean premixed combustion, which is at a temperature far lower than that of diffusion combustion, and is advantageous for controlling the generation of nitrogen oxides. When the gas turbine needs to be loaded up, the remaining fuel passages can be opened gradually.
Another aspect of the present invention provides a method of combustion regulation using the above-described combustor structure, and fig. 10 is a schematic view of a method of combustion regulation according to an embodiment of the present invention, as shown in fig. 10, the method including:
introducing fuel and air into the central diffusion combustion nozzle 274 during an ignition start phase to effect diffusion combustion of the fuel and air within the combustion chamber 2, wherein the fuel introduced during the ignition start phase comprises methane; specifically, in the ignition start stage of the gas turbine, when the starter drives the bearing to rotate to a certain rotation speed, the igniter is ignited, and at this time, the fuel passage is opened to supply methane fuel, so that all the fuel participating in combustion enters the central diffusion combustion nozzle 274 in the long fan-shaped micro-mixing combustor 27A and the short fan-shaped micro-mixing combustor 27B and is injected into the second combustion area 2002, the ignition start is completed, the supply of the fuel is gradually increased, and the gas turbine operates from the zero rotation speed to the slow-start working condition.
In the ignition stage of the gas turbine, because the total fuel quantity is small, the flameout is easy, at this time, the ignition is completed only by using the central diffusion combustion nozzle 274, because the diffusion combustion mode has good combustion stability, the flameout can be prevented, and by only opening the fuel passage of the central loop, a relatively high local fuel-air ratio in the central combustion area 200 can be ensured, and the stability of the combustion flame can be further improved. And in the ignition starting stage, methane is used as fuel instead of hydrogen fuel, so that the ignition safety can be improved.
After a period of combustion stability, the gas turbine stops the introduction of fuel and air into the center diffusion combustion nozzle 274 and introduces fuel and air into a portion of the plurality of unit micro-mixing nozzles 273 during a first load operation period (e.g., 0% to 20% low load) to achieve premixed combustion of the fuel and air in the combustor 2, wherein the fuel introduced during the first load operation period comprises hydrogen or a hydrogen-containing fuel. Specifically, for example, hydrogen gas or a hydrogen-containing fuel is supplied to the first nozzle group 27301 in the long-sector micro-hybrid combustor 27A and the third nozzle group in the short-sector micro-hybrid combustor 27B, and injected into the first combustion zone 2001 for combustion. In the process of fuel switching, the fuel flow rate of the central diffusion combustion nozzle 274 introduced into the long fan-shaped micro-hybrid combustor 27A and the short fan-shaped micro-hybrid combustor 27B is gradually reduced, the fuel flow rate of the first nozzle group 27301 introduced into the long fan-shaped micro-hybrid combustor 27A and the fuel flow rate of the third nozzle group introduced into the short fan-shaped micro-hybrid combustor 27B are synchronously increased until complete switching is achieved, switching of ignition fuel to operation fuel is completed, and the gas turbine can reach a grid-connected power generation state.
During a second load operation (e.g., 20% -70% medium load), fuel and air are injected into all of the plurality of unit micro-mixing nozzles 273 to achieve premixed combustion of the fuel and air in the combustor 2, wherein the fuel injected during the second load operation comprises hydrogen or a hydrogen-containing fuel. For example, on the basis of the previous operation, the supply of hydrogen gas or the hydrogen-containing fuel to the second nozzle group 27302 in the long-sectored micro-hybrid combustor 27A is continued so that at this stage, the fuel is injected into the first combustion zone 2001 and the third combustion zone 2003 simultaneously for combustion, and by increasing the fuel injected into the third combustion zone 2003, the internal combustion engine is made to continue to raise the power generation load to a 70% state.
During a third load phase (e.g., 70% -100% high load), wherein the fuel introduced into the central diffusion combustion nozzle 274 and the unit micro-mixing nozzles 273 comprises hydrogen or a hydrogen-containing fuel, fuel and air are introduced into the central diffusion combustion nozzle 274 and some or all of the plurality of unit micro-mixing nozzles 273 to achieve diffusion combustion and premixed combustion of the fuel and air within the combustor 2.
For example, the above operation may be to simultaneously introduce hydrogen gas or a hydrogen-containing fuel to the first nozzle group 27301, the central diffusion combustion nozzle 274, and the second nozzle group 27302 in the long-sector micro-hybrid combustor 27A, and to simultaneously introduce hydrogen gas or a hydrogen-containing fuel to the third nozzle group and the central diffusion combustion nozzle 274 in the short-sector micro-hybrid combustor 27B, so that at this stage, the fuel is simultaneously injected into the first combustion zone 2001, the second combustion zone 2002, and the third combustion zone 2003 to be combusted, and the three fuels are simultaneously increased in flow rate, so that the internal combustion engine further increases the power generation load to 100% state.
According to the embodiment of the invention, the regulation and control method is used for respectively controlling the fuel supply to the plurality of sub-combustion areas and independently controlling the fuel flow of each sub-combustion area, so that the purpose of staged and independent control of combustion can be achieved, staged combustion is formed, and the method can adapt to the working condition change of the combustion chamber 2 from low load to high load. Through the independent control subregion burning, can improve combustion stability, avoid the emergence of flame-out problem, can realize the homogeneous phase stable combustion of whole combustion area 200 simultaneously to nitrogen oxide when reducing maximum load discharges. The structural design of combining the unit micro-mixing nozzle 273 and the central diffusion combustion nozzle 274 is adopted, so that ignition and stable flame propagation are facilitated, the flame form can be effectively regulated and controlled, and the flame stability under the low load of the combustion engine is improved.
According to an embodiment of the present invention, the method further includes: in the third load working stage, the diffusion premixed fuel ratio is adjusted to meet the preset nitrogen oxide emission limiting condition and the preset thermoacoustic oscillation limiting condition of the combustion chamber, wherein the diffusion premixed fuel ratio is as follows: the ratio of the flow rate of fuel to the center diffusion combustion nozzle 274 to the flow rate of fuel to the unit micro-mixing nozzle 273.
According to the embodiment of the invention, because the central diffusion combustion nozzle 274 has small thermoacoustic oscillation but high nitrogen oxide emission, on the contrary, the emission of nitrogen oxide from the unit micro-mixing nozzle 273 is low, but the thermoacoustic oscillation problem is obvious, and the composite flame consisting of premixed combustion flame and diffusion combustion flame with different layering ratios can be formed by regulating and controlling the fuel ratio entering the unit micro-mixing nozzle 273 and the central diffusion combustion nozzle 274 according to the real-time emission situation of combustion pollutants and the dynamic pressure pulsation (thermoacoustic oscillation) situation in the combustion chamber 2.
The above-mentioned embodiments, objects, technical solutions and advantages of the present invention are further described in detail, it should be understood that the above-mentioned embodiments are only examples of the present invention, and should not be construed as limiting the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (25)
1. A combustion chamber structure, comprising:
a plurality of micro-hybrid combustors, wherein a plurality of micro-hybrid combustors are arranged along a combustion chamber space circumference distribution, each micro-hybrid combustor comprises:
a plurality of unit micro-mixing nozzles, wherein the unit micro-mixing nozzles are used to effect premixed combustion of fuel and air within a combustion chamber;
a central diffusion combustion nozzle, wherein the central diffusion combustion nozzle is for effecting diffusion combustion of fuel and air within a combustion chamber;
a combustor housing having a plurality of fuel chambers disposed therein that are independent of one another, the fuel chambers configured to be fed with fuel, a first portion of the plurality of fuel chambers in communication with the plurality of unit micro-mixing nozzles, a second portion of the plurality of fuel chambers in communication with the central diffusion combustion nozzle.
2. The combustion chamber structure according to claim 1, further comprising:
a plurality of Helmholtz resonators, wherein the plurality of Helmholtz resonators are distributed circumferentially along the combustion chamber volume.
3. The combustion chamber structure according to claim 2, wherein:
the micro-mixing burners comprise a plurality of long fan-shaped micro-mixing burners and a plurality of short fan-shaped micro-mixing burners, and the length of each short fan-shaped micro-mixing burner is smaller than that of each long fan-shaped micro-mixing burner;
one of the short fan-shaped micro-hybrid burners and one of the Helmholtz resonators form a combined unit, and in any combined unit, the short fan-shaped micro-hybrid burners and the Helmholtz resonators are distributed in the radial direction of the combustion chamber;
the long fan-shaped micro-mixing combustors and the combined units are alternately distributed and arranged along the circumferential direction of the combustion chamber space.
4. The combustion chamber structure according to claim 3, wherein:
the combustor housing comprises a first type combustor housing that mates with the elongated fan micro-hybrid combustor, wherein the first type combustor housing comprises a first fuel chamber, a second fuel chamber, and a third fuel chamber;
a plurality of unit micro-mixing nozzles in the long fan-shaped micro-mixing combustor form a first nozzle group and a second nozzle group, the first nozzle group, a central diffusion combustion nozzle in the long fan-shaped micro-mixing combustor and the second nozzle group are arranged along the radial direction of a combustion chamber from outside to inside, and the first nozzle group, the central diffusion combustion nozzle in the long fan-shaped micro-mixing combustor and the second nozzle group are respectively communicated with the first fuel chamber, the second fuel chamber and the third fuel chamber;
the burner housing comprises a second type burner housing that mates with the short sector micro-hybrid burner, wherein the second type burner housing comprises a fourth fuel chamber, a fifth fuel chamber;
the multiple unit micro-mixing nozzles in the short fan-shaped micro-mixing combustor form a third nozzle group, the third nozzle group and the central diffusion combustion nozzles in the short fan-shaped micro-mixing combustor are arranged along the radial direction of a combustion chamber from outside to inside, and the central diffusion combustion nozzles in the third nozzle group and the short fan-shaped micro-mixing combustor are respectively communicated with the fourth fuel chamber and the fifth fuel chamber.
5. The combustion chamber structure according to claim 4, wherein:
the combustion area of the combustion chamber is divided into a plurality of sub-combustion areas along the radial direction of the combustion chamber, and the sub-combustion areas comprise a first combustion area, a second combustion area and a third combustion area which are sequentially distributed along the radial direction of the combustion chamber;
the first nozzle group, the central diffusion combustion nozzle in the long fan-shaped micro-mixing combustor and the second nozzle group respectively correspond to the first combustion area, the second combustion area and the third combustion area;
and the third nozzle group and the central diffusion combustion nozzle in the short fan-shaped micro-mixing combustor respectively correspond to the first combustion area and the second combustion area.
6. The combustion chamber structure according to claim 4, wherein:
a first fuel flow cavity channel communicated with the first fuel chamber, a second fuel flow cavity channel communicated with the second fuel chamber and a third fuel flow cavity channel communicated with the third fuel chamber are further arranged in the first type combustor shell;
a fourth fuel flow channel communicated with the fourth fuel chamber and a fifth fuel flow channel communicated with the fifth fuel chamber are also arranged in the second type combustor shell.
7. The combustor structure of claim 1, wherein the combustor is an annular combustor, the combustor structure further comprising:
a peripheral wall assembly;
an inner wall assembly, wherein the outer wall assembly and the inner wall assembly are concentrically arranged annular wall structures, an annular combustion chamber is enclosed between the outer wall assembly and the inner wall assembly, and a plurality of micro-mixing burners are arranged between the outer wall assembly and the inner wall assembly, so that the plurality of micro-mixing burners divide the annular combustion chamber into a flame tube head air inlet area and a combustion area;
an inlet end member in communication with the liner head inlet region and configured to pass air into the liner head inlet region such that at least a portion of the air in the liner head inlet region enters the plurality of unit micro-mixing nozzles.
8. The combustion chamber structure according to claim 7, wherein:
the unit micro-mixing nozzle comprises a nozzle shell, wherein a fuel air inlet cavity and a premixing cavity which are independent from each other are arranged in the nozzle shell, the fuel air inlet cavity is communicated with the premixing cavity through a fuel injection hole, the fuel air inlet cavity is communicated with a first part of fuel cavity and is configured to be filled with fuel, an air inlet hole is arranged in the wall of the premixing cavity, the air inlet hole is communicated with a flame tube head air inlet area and is configured to be filled with air, and the outlet end of the premixing cavity is communicated with a combustion area of a combustion chamber;
wherein, in the unit micro-mixing nozzle, the pre-mixing chamber is to: and mixing the air entering through the air inlet hole and the fuel from the fuel inlet cavity to form premixed gas, and injecting the premixed gas to the combustion area to realize premixed combustion of the fuel and the air in the combustion chamber.
9. The combustion chamber structure according to claim 8, wherein:
nozzle cooling film holes are provided in the chamber wall near the outlet end of the premixing chamber.
10. The combustion chamber structure according to claim 8, wherein:
the nozzle shell adopts a circular tubular structure;
the fuel inlet cavity comprises a section of circular tube-shaped air inlet pipe with a closed tail end, and the air inlet pipe is arranged coaxially with the nozzle shell so that an annular premixing cavity is formed between the outer surface of the air inlet pipe and the inner surface of the nozzle shell;
the fuel injection hole is arranged at the front end of the air inlet pipe, and the concave central body is arranged at the tail end of the air inlet pipe.
11. The combustion chamber structure according to claim 8, wherein:
the air inlet holes comprise a primary air inlet hole and a secondary air inlet hole, and the primary air inlet hole and the secondary air inlet hole are arranged along the air flow direction in the premixing cavity.
12. The combustion chamber structure according to claim 7, wherein:
the central diffusion combustion nozzle comprises a sleeve and a fuel nozzle;
the sleeve is provided with an air inlet and a diffusion gas outlet, the air inlet is communicated with the air inlet area at the head of the flame tube and is configured to be filled with air, and the diffusion gas outlet is communicated with the combustion area of the combustion chamber;
the inlet end of the fuel nozzle tip is communicated with the second part of the fuel chamber, so that fuel from the second part of the fuel chamber is led into the fuel nozzle tip, the outlet end of the fuel nozzle tip is provided with fuel injection holes, and the fuel nozzle tip and the sleeve are communicated through the fuel injection holes;
wherein the central diffusion combustion nozzle is to: and after the air entering through the air inlet and the fuel sprayed in through the fuel spray nozzle are subjected to diffusion action of the sleeve, the air and the fuel are sprayed in a combustion area of the combustion chamber through a diffusion gas outlet of the sleeve, so that diffusion combustion of the fuel and the air in the combustion chamber is realized.
13. The combustion chamber structure according to claim 12, wherein:
the central diffusion combustion nozzle further comprises a venturi, the venturi is arranged in the sleeve, and the fuel nozzle and the venturi are communicated through a fuel injection hole.
14. The combustion chamber structure according to claim 12, wherein:
the central diffusion combustion nozzle further comprises a swirl cup disposed at the air inlet of the sleeve such that air forms a swirl within the sleeve upon entry.
15. The combustion chamber structure according to claim 7, wherein:
the peripheral wall assembly comprises an outer casing and a liner outer ring;
the inner surrounding wall component comprises an inner casing and a flame tube inner ring;
the outer ring of the flame tube, the inner ring of the flame tube and the plurality of micro-mixing burners are enclosed to form a combustion area;
the inlet section of the outer casing, the inlet section of the inner casing and the micro-mixing combustors are enclosed to form a flame tube head air inlet area.
16. The combustion chamber structure of claim 15, wherein:
an outer ring cavity channel is formed by enclosing the outer casing and the outer ring of the flame tube;
an inner ring cavity channel is formed by enclosing the inner casing and the inner ring of the flame tube;
the outer ring cavity channel and the inner ring cavity channel are respectively communicated with the flame tube head air inlet area, so that at least part of air in the flame tube head air inlet area enters the outer ring cavity channel and then cools the outer ring of the flame tube, and enters the inner ring cavity channel and then cools the inner ring of the flame tube.
17. The combustion chamber structure of claim 16, wherein:
the air inlet end component comprises a diffuser, an outlet of the diffuser is connected with an inlet section of the outer casing and an inlet section of the inner casing, and an inlet of the diffuser is communicated with the outside.
18. The combustion chamber structure according to claim 17, wherein:
and the outlet section of the diffuser is provided with a flow guide rib.
19. The combustion chamber structure according to claim 16, further comprising:
a liner head end wall disposed between the liner outer ring and the liner inner ring, the liner head end wall configured to fixedly mount a plurality of micro-hybrid burners;
the end wall of the head of the flame tube is provided with a plurality of flame tube gas film cooling holes.
20. The combustion chamber structure of claim 19, wherein:
the central axis of the flame tube gas film cooling hole is not parallel to the central axis of the annular combustion chamber.
21. The combustion chamber structure according to claim 20, wherein:
the outer casing is provided with a burner mounting seat, and the micro-mixing burner is detachably and fixedly mounted on the end wall of the head of the flame tube through the burner mounting seat.
22. The combustion chamber structure according to claim 2, wherein the Helmholtz resonator includes:
a cylindrical resonator housing, a resonant cavity being formed in the resonator housing;
the spiral plate is arranged in the resonant cavity;
the resonator comprises a resonator shell, a first cover plate and a second cover plate, wherein the first cover plate and the second cover plate are respectively arranged at two ends of the resonator shell, a plurality of first through holes are formed in the first cover plate, and a plurality of second through holes are formed in the second cover plate;
the Helmholtz resonator is used for enabling air to enter the resonant cavity through the first through hole and to flow out of the resonant cavity through the second through hole after passing through the spiral plate.
23. The combustion chamber structure according to claim 22, wherein:
first through holes and second through holes which are respectively arranged in the first cover plate and the second cover plate in an uneven distribution mode;
the center axes of the first through hole and the second through hole are not parallel to the center axis of the resonator case.
24. A method of combustion regulation using the combustor structure of any one of claims 1-23, comprising:
in the ignition starting stage, introducing fuel and air into the central diffusion combustion nozzle to realize diffusion combustion of the fuel and the air in the combustion chamber, wherein the fuel introduced into the central diffusion combustion nozzle in the ignition starting stage comprises methane;
stopping introducing fuel and air into the central diffusion combustion nozzle in a first load working stage, and introducing the fuel and the air into part of the nozzles in the plurality of unit micro-mixing nozzles to realize the premixed combustion of the fuel and the air in the combustion chamber, wherein the fuel introduced into the part of the nozzles in the plurality of unit micro-mixing nozzles comprises hydrogen or hydrogen-containing fuel in the first load working stage;
in a second load working stage, introducing fuel and air into all the nozzles in the plurality of unit micro-mixing nozzles to realize the premixed combustion of the fuel and the air in the combustion chamber, wherein in the second load working stage, the fuel introduced into all the nozzles in the plurality of unit micro-mixing nozzles comprises hydrogen or hydrogen-containing fuel;
in a third load working stage, introducing fuel and air into the central diffusion combustion nozzle and part or all of the plurality of unit micro-mixing nozzles to realize diffusion combustion and premixed combustion of the fuel and the air in the combustion chamber, wherein in the third load working stage, the fuel introduced into the central diffusion combustion nozzle and part or all of the plurality of unit micro-mixing nozzles comprises hydrogen or hydrogen-containing fuel;
and the load of the first load working stage is smaller than that of the second load working stage, and the load of the second load working stage is smaller than that of the third load working stage.
25. A method of using the apparatus of claim 24, further comprising:
in a third load working stage, the diffusion premixed fuel ratio is adjusted to meet a preset nitrogen oxide emission limiting condition and a preset thermoacoustic oscillation limiting condition of a combustion chamber, wherein the diffusion premixed fuel ratio is as follows: the ratio of the flow rate of fuel introduced into the central diffusion combustion nozzle to the flow rate of fuel introduced into the unit micro-mixing nozzles.
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| CN115597088B (en) | 2024-03-19 |
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