CN114294680B - Micro-premixing combustion chamber of central grading gas turbine - Google Patents
Micro-premixing combustion chamber of central grading gas turbine Download PDFInfo
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- CN114294680B CN114294680B CN202111641488.2A CN202111641488A CN114294680B CN 114294680 B CN114294680 B CN 114294680B CN 202111641488 A CN202111641488 A CN 202111641488A CN 114294680 B CN114294680 B CN 114294680B
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- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
Abstract
The invention provides a micro-premixing combustion chamber of a central grading gas turbine, which comprises a valve shift, a main combustion stage, an igniter, two-stage end covers, a flame tube and a flame tube outer casing. The on-duty nozzle area adopts diffusion combustion to prevent backfire, and meanwhile, a backflow area is formed at the nozzle outlet due to the speed difference between the on-duty nozzle outlet and the surrounding environment, so that the effect of stabilizing flame is achieved; the nozzles in the sectors of the main combustion stage unit are relatively independent, the array expansion can be carried out according to the working load of the combustion chamber, and a plurality of micro-premixing pipes which are in one-to-one correspondence with the fuel spray holes are contained in a single micro-premixing nozzle, so that the purpose of forming the blending of single fuel and air is achieved, and the blending efficiency is improved. Compared with a traditional gas turbine combustion chamber, the burner can realize uniform mixing of fuel and air under a micro scale, reduce the peak flame temperature in combustion, and a plurality of micro premixing nozzles can simultaneously generate small flames to realize uniform distribution of temperature in the flame tube, shorten the length of a high temperature area and meet the low emission requirement.
Description
Technical Field
The invention belongs to the technical field of combustion chambers of gas turbines, and particularly relates to a micro-pre-mixed combustion chamber of a central grading gas turbine.
Background
The gas turbine is high-end power equipment combining manufacturing technology and energy technology, can be applied to various fields of aviation, ships, power generation and the like, is directly related to national defense safety, technological progress and economic development of the country, and is valued by the world. The gas turbine can use various fuels such as gas, liquid and the like, and has the advantages of high thermal efficiency, small pollution discharge, small volume, quick start and the like. Currently, in order to further increase the efficiency of gas turbines, the initial temperature of the gas and the pressure ratio are continuously increasing. However, since most of the nitrogen oxide emissions from gas turbines are thermal, according to the Zeldovich mechanism, as the temperature in the gas turbine increases significantly, the nitrogen oxide production increases exponentially. Therefore, how to solve the contradiction between the temperature rise and the pollutant emission reduction caused by the improvement of the combustion efficiency of the gas turbine is a serious issue in the research of the gas turbine at the present stage.
At present, a Dry Low Emission (DLE or DLN) combustion technology is mainly adopted for reducing nitrogen oxides in a combustion chamber of a gas turbine, the basic principle is that the combustion is in a dilute state homogeneous premixed combustion, and the local high temperature is avoided in the combustion chamber by uniformly mixing fuel and excessive air before entering the combustion chamber, so that the generation of the nitrogen oxides is inhibited. However, due to the existence of the cyclone in the combustion chamber of the traditional gas turbine, a central backflow area with a larger area is formed in the flame tube, and fuel and air flow and react in the area, so that the temperature of fuel gas formed by combustion is increased, the residence time is prolonged, and the generation amount of oxynitride is increased. In addition, due to the low carbon emission requirements of the current stage, developing a combustion technology suitable for hydrogen and hydrogen-rich synthetic gas is a main development direction for reducing greenhouse gases of future power plants. Compared with the conventional fuel, the hydrogen has the advantages of higher flame propagation speed, low ignition energy and less ignition delay time, and the conventional combustion mode can increase the risks of tempering and spontaneous combustion; and the adiabatic flame temperature of hydrogen is high, which is also a challenge for the control of thermal nitrogen oxides. Therefore, developing new low NOx combustion technologies suitable for hydrogen and hydrogen-rich fuels is a critical issue that needs to be addressed in the current gas turbine combustion arts.
Disclosure of Invention
In view of the above, the invention aims to provide a micro-premixing combustion chamber of a central grading gas turbine, which realizes stable combustion when the hydrogen content of fuel is changed, realizes control of the peak flame temperature and the size of a high-temperature area through uniform mixing of fuel and air in a micro-premixing pipe, and simultaneously reduces the residence time of flue gas in the high-temperature area so as to achieve the aim of reducing pollutant emission.
In order to achieve the above purpose, the technical scheme of the invention is realized as follows:
the utility model provides a little premix combustion chamber of center classifying gas turbine, includes value class, main combustion stage, some firearm, first level end cover, second level end cover, flame tube and flame tube outer receiver, value class and main combustion stage are arranged concentrically, and the class is located the combustion chamber center, and main combustion stage is arranged in value class periphery, some firearm sets up in the central through-hole of combustion chamber head, first level end cover and second level end cover are connected, and are equipped with the clearance between the two-stage end cover, the flame tube is connected with the second level end cover, flame tube outer receiver installs in flame tube outside, and with the coaxial setting of flame tube, forms the air channel between flame tube outer wall and the flame tube outer receiver, the inside combustion chamber combustion zone that forms of flame tube;
the on-duty stage comprises an on-duty stage fuel distribution cavity and a plurality of on-duty stage micro-mixing nozzles, the on-duty stage fuel distribution cavity is arranged at the periphery of a central hole of the head part of the combustion chamber and is used for conveying fuel to the on-duty stage micro-mixing nozzles; the front end part of the duty grade fuel distribution cavity is provided with a duty grade fuel inlet, a first grade end cover is provided with a plurality of mounting positioning holes for mounting duty grade micro-mixing nozzles corresponding to the duty grade fuel distribution cavity area, a second grade end cover is provided with duty grade nozzle air channels corresponding to the duty grade micro-mixing nozzles one by one, one end of each duty grade micro-mixing nozzle is fixed to the mounting positioning holes of the first grade end cover, the other end of each duty grade micro-mixing nozzle is inserted into the corresponding duty grade nozzle air channel, the duty grade micro-mixing nozzle comprises a duty grade nozzle center micro-mixing pipe, the tail end of the duty grade nozzle center micro-mixing pipe is provided with a plurality of duty grade nozzle air inlet holes, and incoming air is injected into the duty grade nozzle center micro-mixing pipe from the tail end of the duty grade nozzle air channel on the second grade end cover from the duty grade nozzle air inlet holes and is mixed with the duty grade nozzle center micro-mixing pipe in the outlet of the duty grade micro-mixing nozzle for diffusion combustion;
the main combustion stage comprises a main combustion stage porous fuel inlet pipe, a main combustion stage fuel distribution cavity and a plurality of main combustion stage micro-premixing spray nozzles; the main combustion stage fuel distribution cavity is arranged at the periphery of the duty stage fuel distribution cavity, the annular main combustion stage fuel distribution cavity is uniformly divided into a plurality of sector ring areas through a plurality of partition boards, each sector ring area is matched with a main combustion stage porous fuel air inlet pipe, a plurality of fuel spray holes are arranged at the tail end of the pipe wall of each main combustion stage porous fuel air inlet pipe, and the main combustion stage porous fuel air inlet pipe extends into the corresponding sector ring area to provide fuel for main combustion stage micro-premixing nozzles in the sector ring area;
the method comprises the steps that a plurality of mounting positioning holes for mounting main-stage micro-premix nozzles are formed in a first-stage end cover corresponding to a main-stage fuel distribution cavity area, a plurality of main-stage nozzle center fuel pipes which are in one-to-one correspondence with the main-stage micro-premix nozzles are formed in a second-stage end cover, the main-stage nozzle center fuel pipes are communicated with the corresponding main-stage micro-premix nozzles, a plurality of main-stage nozzle micro-premix pipes are uniformly arranged around each main-stage nozzle center fuel pipe, the main-stage nozzle center fuel pipes are communicated with the corresponding main-stage nozzle micro-premix pipes through main-stage nozzle fuel spray holes in the pipe wall, the main-stage nozzle center fuel pipes convey fuel for the main-stage nozzle micro-premix pipes, incoming air enters the main-stage nozzle micro-premix pipes through gaps between two-stage end covers, a mixing area of fuel and air is formed in the main-stage nozzle micro-premix pipes, and the mixed premixed air is sprayed into a flame tube at the tail end of the main-stage micro-nozzle micro-premix pipes for premixed combustion.
Further, the first-stage end cover and the second-stage end cover are integrated into a whole, the front end face of the second-stage end cover is a curved surface, and the fitting function of the curved surface curve is a cubic polynomial.
Further, the diameter of the micro-mixing pipe at the center of the duty nozzle is 2-20mm, and the length of the micro-mixing pipe is 10-200mm; the number of the air inlet holes of the class-on-duty micro-mixing nozzle is 4-8 along the circumferential array of the wall of the micro-mixing pipe at the center of the class-on-duty nozzle; the shape of the air inlet hole of the on-duty nozzle is elliptic, the length of the major axis of the elliptic is 0.5-2.5mm, the length of the minor axis of the elliptic is 0.25-2mm, or the shape of the air inlet hole of the on-duty nozzle is rectangular, the length of the rectangular is 0.5-2.5mm, and the width of the rectangular is 0.25-2mm.
Further, the duty-level micro-mixing nozzles are circumferentially arranged for 1-4 layers; the main combustion stage micro-premixing nozzles are arranged in 2-8 layers according to the circumference, the diameters of the primary combustion stage micro-premixing nozzles and the main combustion stage micro-premixing nozzles are 5-20mm, the distance between every two adjacent primary combustion stage micro-premixing nozzles is (1.2-4) times the diameter of the primary combustion stage micro-premixing nozzles, and the distance between every two adjacent primary combustion stage micro-premixing nozzles is (1.2-4) times the diameter of the main combustion stage micro-premixing nozzles.
Further, the diameter of the fuel spray holes on the tail end pipe wall of the main combustion stage porous fuel air inlet pipe is 0.1-1mm, and the main combustion stage porous fuel air inlet pipe surrounds 2-5 layers of pipe wall arrays; the partition plate is used for dividing the main combustion stage fuel distribution cavity into 4-12 sector ring areas, a plurality of layers of porous fuel rectifying plates are arranged in each sector ring area, the aperture of each porous fuel rectifying plate is 0.1-1mm, the number of layers of the porous fuel rectifying plates is 1-5, the small holes on each layer of porous fuel rectifying plates are staggered, and the interval between every two adjacent layers is 1-5mm.
Further, the diameter of the central fuel pipe of the main combustion stage nozzle is 1-5mm, the diameter of the fuel spray holes of the main combustion stage nozzle is 0.1-1mm, and the number of the fuel spray holes is 4-12; the number of the main fuel stage micro-premixing pipes is the same as that of the main fuel stage nozzle fuel spray holes on the pipe wall of the main fuel stage nozzle center fuel pipe.
Further, the main combustion stage micro-premixing tube is a straight tube or a spiral tube; the length of the main combustion stage micro premix tube is 5-100mm; the cross section of the main combustion stage micro-premix pipe is circular, the diameter of the circular main combustion stage micro-premix pipe is 1-10mm, or the cross section of the main combustion stage micro-premix pipe is elliptical, the long axis of the elliptical main combustion stage micro-premix pipe is 1-10mm, the short axis is 0.5-5mm, or the cross section of the main combustion stage micro-premix pipe is regular polygon, and the side length of the regular polygon main combustion stage micro-premix pipe is 1-10mm; or the section of the main combustion stage micro-premix pipe is in a fan shape, the outer diameter of the fan-shaped main combustion stage micro-premix pipe is 2.5-20mm, and the inner diameter of the fan-shaped main combustion stage micro-premix pipe is 1.5-10mm.
Further, the fuel spray holes of the main combustion stage nozzle are arranged in 2-5 layers around the circular array of the pipe wall, the number of adjacent layers is 1-2mm, and each row of fuel spray holes is communicated with one main combustion stage micro-premixing pipe.
Further, the length of the duty stage micro-mixing nozzle is the same as the total length of the main combustion stage micro-mixing nozzle.
Further, the total length of the main combustion stage micro-premixing nozzle is 10-200mm.
Compared with the prior art, the micro-premixing combustion chamber of the central grading gas turbine has the following advantages:
(1) The class-value micro-mixing nozzle adopts a combustion mode of diffusion combustion, and meanwhile, the flow velocity at the outlet is higher due to the smaller size of the nozzle, so that the backfire risk during the combustion of hydrogen and hydrogen-rich fuel can be reduced; in addition, the adoption of the duty stage and the diffusion combustion are also convenient for ignition and stable propagation of flame;
(2) Because the micro-mixing nozzles of the multiple valve classes and the micro-premixing nozzles of the main combustion stage are distributed in an array, each nozzle outlet can generate relatively independent small flame, thereby avoiding the generation of a high temperature area in the flame tube and ensuring that the temperature distribution of the outlet of the combustion chamber is more uniform;
(3) The single main combustion stage micro-premixing nozzle is internally provided with a plurality of micro-premixing pipes, so that a single fuel gas sprayed from a single nozzle on the central fuel pipe wall of the nozzle and a corresponding single air are mixed in a one-to-one mode in the micro-premixing pipe, the mutual influence of a plurality of fuel spray holes sprayed by a plurality of fuel spray holes and the air when being mixed in one premixing pipe is avoided, the mixing efficiency is improved compared with the mixing efficiency realized by the traditional micro-premixing combustion technology, the peak temperature of flame in the combustion process can be further reduced, the speed of premixed gas at the outlet of the micro-premixing nozzle is improved, the tempering risk of hydrogen and hydrogen-rich fuel is reduced, the smoke residence time is shortened, the generation of thermal nitrogen oxides is reduced to a greater extent, the small flame size formed by a plurality of nozzles is smaller, and the length of a flame tube of a combustion chamber is also positively played in shortening;
(4) The curved surface design of the fuel distribution cavity and the front end surface of the second-stage end cover can realize the uniform distribution of fuel and air in the on-duty stage nozzle and the main combustion stage nozzle, and has great effect on improving the uniformity of temperature distribution in the combustion chamber.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a schematic diagram of a micro premix combustor of a center staged gas turbine according to an embodiment of the present invention;
FIG. 2 is a schematic view of a fuel distribution chamber according to an embodiment of the present invention;
FIG. 3 is a schematic view of the outlet face of a fuel distribution chamber according to an embodiment of the present invention;
FIG. 4 is an enlarged schematic view of a micro premix combustor A of a gas turbine according to an embodiment of the invention;
FIG. 5 is an enlarged schematic view of a micro premix combustor B of a gas turbine in accordance with an embodiment of the invention;
FIG. 6 is a schematic three-dimensional view of a second embodiment of a primary micro-premix nozzle;
FIG. 7 is a three-dimensional schematic view of a third embodiment of a primary micro-premix nozzle of the present invention;
FIG. 8 is a schematic view of a first stage end cap according to an embodiment of the present invention;
FIG. 9 is a cross-sectional view taken along the line C-C of FIG. 8 of a two-stage end cap according to an embodiment of the present invention;
FIG. 10 is a schematic view of a second stage end cap according to the embodiment of the present invention along the direction D of FIG. 9;
FIG. 11 is a schematic view of a second stage end cap of an embodiment of the present invention, taken along the E-direction (on duty and primary fuel stage nozzle outlet face) of FIG. 9.
Reference numerals illustrate:
1. a main combustion stage porous fuel air inlet pipe; 2. class fuel inlet; 3. a main combustion stage fuel distribution chamber; 4. a partition plate; 5. A porous fuel rectifying plate; 6. an on-duty fuel distribution cavity; 7. a main combustion stage micro premix nozzle; 8. a main combustion stage nozzle center fuel tube; 9. a main combustion stage nozzle fuel orifice; 10. a main combustion stage nozzle micro-premix tube; 11. class-wide micro-mixing nozzle; 12. A valve class nozzle center micro-mixing pipe; 13. an on duty nozzle air passage; 14. an air inlet hole of the on-duty nozzle; 15. An igniter; 16. a first stage end cap; 17. a second stage end cap; 18. a flame tube; 19. an air passage; 20. the outer casing of the flame cylinder; 21. a main combustion stage nozzle region; 22. a duty stage nozzle zone.
Detailed Description
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other.
The invention will be described in detail below with reference to the drawings in connection with embodiments.
1-11, a micro-premix combustor for a center staged gas turbine is provided, which is adapted for use with a gas fuel having a range of variation in volume fractions of components H 2 :100% -25%, CO:25% -75% of hydrogen-rich synthetic gas and natural gas;
the burner comprises a valve shift, a main combustion stage, an igniter 15, a first-stage end cover 16, a second-stage end cover 17, a flame tube 18 and a flame tube outer casing 20, wherein the valve shift and the main combustion stage are concentrically arranged, the valve shift is positioned at the center of a combustion chamber, the main combustion stage is arranged at the periphery of the valve shift, the igniter 15 is arranged in a central through hole at the head of the combustion chamber and is fixed on the two-stage end covers, the first-stage end cover 16 and the second-stage end cover 17 are connected, a gap is arranged between the two-stage end covers, the flame tube 18 is connected with the second-stage end cover 17, the flame tube 18 is a tapered cylindrical wall surface, the flame tube outer casing 20 is arranged outside the flame tube 18 and is coaxially arranged with the flame tube 18, an air channel 19 is formed between the outer wall of the flame tube 18 and the flame tube outer casing 20, air reversely flows into each nozzle of the valve shift and the main combustion stage along the air channel 19, the flame tube 18 is a tapered cylindrical wall surface, and a combustion chamber combustion area is formed inside the flame tube 18;
the on-duty fuel distribution cavity 6 is arranged at the periphery of a central hole of the head part of the combustion chamber, and the on-duty fuel distribution cavity 6 is used for conveying fuel to the on-duty micro-mixing nozzle 11; the front end part of the on-duty fuel distribution cavity 6 is provided with an on-duty fuel inlet 2, a plurality of mounting positioning holes for mounting on-duty micro-mixing nozzles are formed in a first-stage end cover 16 in a region corresponding to the on-duty fuel distribution cavity 6, a second-stage end cover 17 is provided with on-duty nozzle air channels 13 corresponding to the on-duty micro-mixing nozzles 11 one by one, one end of each on-duty micro-mixing nozzle 11 is fixed to the mounting positioning holes of the first-stage end cover 16, the other end of each on-duty micro-mixing nozzle 11 is inserted into the corresponding on-duty nozzle air channel 13, the on-duty micro-mixing nozzles 11 comprise on-duty nozzle center micro-mixing pipes 12, a plurality of on-duty nozzle air inlets 14 are formed at the tail end of the on-duty nozzle center micro-mixing pipes 12, and incoming air is injected into the on-duty nozzle center micro-mixing pipes 12 from the tail ends of the on-duty nozzle air channels 13 on the second-stage end cover 17 and is converged into the outlet 18 of the on-duty micro-mixing nozzles 11 with the on-duty nozzle center micro-mixing pipes 12 for diffusion combustion;
the main combustion stage comprises a main combustion stage porous fuel inlet pipe 1, a main combustion stage fuel distribution cavity 3 and a plurality of main combustion stage micro-premixing nozzles 7; the main combustion stage fuel distribution cavity 3 is arranged at the periphery of the duty stage fuel distribution cavity 6, the annular main combustion stage fuel distribution cavity 3 is uniformly divided into a plurality of sector ring areas through a plurality of partition plates 4, each sector ring area is matched with a main combustion stage porous fuel air inlet pipe 1, a plurality of fuel spray holes are formed at the tail end of the pipe wall of each main combustion stage porous fuel air inlet pipe 1, and the main combustion stage porous fuel air inlet pipes 1 extend into the corresponding sector ring areas to provide fuel for main combustion stage micro-premixing nozzles 7 in the corresponding sector ring areas;
the method comprises the steps that a plurality of mounting positioning holes for mounting main-stage micro-premixing nozzles 7 are formed in a first-stage end cover 16 in a region corresponding to a main-stage fuel distribution cavity 3, a plurality of main-stage nozzle center fuel pipes 8 which are in one-to-one correspondence with the main-stage micro-premixing nozzles are formed in a second-stage end cover 17, the main-stage nozzle center fuel pipes 8 are communicated with the corresponding main-stage micro-premixing nozzles, a plurality of main-stage nozzle micro-premixing pipes 10 are uniformly arranged around each main-stage nozzle center fuel pipe 8, the main-stage nozzle center fuel pipes 8 are communicated with the corresponding main-stage nozzle micro-premixing pipes 10 through main-stage nozzle fuel spray holes 9 in the pipe wall, the main-stage nozzle center fuel pipes 8 are used for conveying fuel for the main-stage nozzle micro-premixing pipes 10, incoming air enters the main-stage nozzle micro-premixing pipes 10 through gaps between two-stage end covers, a mixing region of fuel and air is formed in the main-stage nozzle micro-premixing pipes 10, and the tail ends of the mixed main-stage premixing pipes 10 are sprayed into flame barrels 18 for premixed combustion.
The first-stage end cover 16 and the second-stage end cover 17 are integrated, the front end surface of the second-stage end cover 17 is a curved surface, and the fitting function of the curved surface curve isThe purpose of the cubic polynomial is to make the air distribution uniform in each nozzle. Wherein, the fitting curve of the curved surface of the second-stage end cover 17 is y=ax 3 +bx 2 +cx+d, a, b, c, d are real numbers.
The second-stage end cover 17 is provided with an on-duty nozzle area 22 and a plurality of main combustion-stage nozzle areas 21 at the inner circle, the number of the main combustion-stage nozzle areas 21 is 4-12, and the plurality of main combustion-stage nozzle areas 21 are arranged around the on-duty nozzle area 22.
The diameter of the on-duty nozzle center micro-mixing pipe 12 is 2-20mm, and the length is 10-200mm; the number of the air inlet holes 14 of the on-duty micro-mixing nozzle is 4-8 along the circumferential array of the wall of the on-duty micro-mixing pipe 12 at the center of the on-duty micro-mixing nozzle; the shape of the air inlet hole 14 of the on-duty nozzle is elliptic, the length of the major axis of the elliptic is 0.5-2.5mm, the length of the minor axis of the elliptic is 0.25-2mm, or the shape of the air inlet hole 14 of the on-duty nozzle is rectangular, the length of the rectangular is 0.5-2.5mm, and the width of the rectangular is 0.25-2mm.
The duty-level micro-mixing nozzles 11 are circumferentially arranged for 1-4 layers; the main combustion stage micro-premixing nozzle 7 is circumferentially arranged in 2-8 layers, the diameter of the duty stage micro-premixing nozzle 11 and the diameter of the main combustion stage micro-premixing nozzle 7 are 5-20mm, the two micro-premixing nozzles can be the same or different, the distance between two adjacent micro-premixing nozzles is (1.2-4) times the diameter of the duty stage micro-premixing nozzle 11, and the distance between two adjacent micro-premixing nozzles is (1.2-4) times the diameter of the main combustion stage micro-premixing nozzle 7.
The diameter of the fuel spray holes on the tail end pipe wall of the main combustion stage porous fuel air inlet pipe 1 is 0.1-1mm, and 2-5 layers are arranged around the pipe wall array; the main combustion stage fuel distribution cavity 3 is divided into 4-12 sector ring areas by a partition plate 4, and a plurality of layers of porous fuel rectifying plates 5 are arranged in each sector ring area and are used for uniformly distributing fuel into main combustion stage micro-premixing nozzles 7 in the corresponding sector ring area; the pore diameter of the porous fuel rectifying plate 5 is 0.1-1mm, the number of layers of the porous fuel rectifying plate is 1-5, the small pores on each layer of porous fuel rectifying plate are staggered, and the interval between two adjacent layers is 1-5mm.
The first structure diagram of the three main combustion stage micro-premixing nozzles is shown in fig. 5, the diameter of a central fuel pipe 8 of the main combustion stage nozzles is 1-5mm, the diameter of fuel spray holes 9 of the main combustion stage nozzles on the pipe wall is 0.1-1mm, and the number of the fuel spray holes is 4-12. The cross section of the main combustion stage nozzle micro-premixing tube 10 is round, elliptic, regular polygon or fan ring; the circular diameter is 1-10mm, the elliptical major axis is 1-10mm, the minor axis is 0.5-5mm, the regular polygon side length is 1-10mm, the sector ring outer diameter is 2.5-20mm, the inner diameter is 1.5-10mm, the number of micro-premixing pipes is the same as the number of main combustion stage nozzle fuel spray holes 9 on the wall of a main combustion stage nozzle central fuel pipe 8, and the length of the micro-premixing pipes is 5-100mm.
Second, as shown in fig. 6, the main-stage nozzle micro-premix pipe 10 in the main-stage micro-premix nozzle 7 is a spiral circular pipe or spiral elliptic pipe, the circular pipe is circumferentially arrayed around the central fuel pipe 8 of the main-stage nozzle, the diameter of the circular pipe is 1-10mm, the long axis of the elliptic pipe is 1-10mm, the short axis is 0.5-5mm, the elliptical pipe is communicated with the main-stage nozzle fuel spray holes 9 on the wall of the central fuel pipe 8 of the main-stage nozzle, the number of the elliptical pipe is 4-12 as the number of the spray holes, the diameter of the spray holes is 0.1-1mm, the diameter of the central fuel pipe is 1-5mm, and the rest structural parameters are the same as those of the first kind.
Third, as shown in fig. 7, the fuel spray holes on the central fuel pipe 8 of the main combustion stage micro-premixing nozzle are arranged in a circumferential array of 2-5 layers, the aperture is 0.1-1mm, 4-12 fuel spray holes are arranged in each layer, and each row of fuel spray holes is communicated with one main combustion stage nozzle micro-premixing pipe 10. In addition, the remaining structural parameters of the micro premix nozzle in this solution are the same as those of the first one.
The length of the duty stage micro-mixing nozzle 11 is the same as the total length of the main combustion stage micro-mixing nozzle 7. The total length of the main combustion stage micro-pre-mixing nozzle 7 is 10-200mm.
The working process of the application comprises the following steps:
gaseous fuel flows out from a gas source and respectively enters the main combustion stage porous fuel gas inlet pipe 1 and the duty stage fuel inlet 2; the fuel in the main combustion stage porous fuel air inlet pipe 1 enters the main combustion stage fuel distribution cavity 3, the main combustion stage fuel distribution cavity 3 is divided into a plurality of sector areas by the partition plate 4, each sector is provided with a main combustion stage porous fuel air inlet pipe 1 for independently supplying fuel, the main combustion stage porous fuel air inlet pipe is uniformly distributed into a main combustion stage nozzle center fuel pipe 8 in a main combustion stage micro-premixing nozzle 7 in each sector through a porous fuel rectifying plate 5, the main combustion stage nozzle fuel spray holes 9 on the pipe wall are radially injected into the main combustion stage nozzle micro-premixing pipe 10 in a surrounding array of the main combustion stage nozzle micro-premixing pipe 10, and the main combustion stage nozzle micro-premixing pipe 10 is mixed with air entering along a gap between the first stage end cover 16 and the second stage end cover 17, and the main combustion stage micro-premixing nozzle 10 is in millimeter level, so that the outlet combustible gas mixing speed of the main combustion stage micro-premixing nozzle 7 is higher, the tempering risk can be effectively reduced, the main combustion stage nozzle micro-premixing pipe 10 is smaller in size, the uniform mixing of the fuel and the air is more favorable, the flame peak temperature is reduced, and the low emission requirement of a combustion chamber is realized;
the fuel in the valve class fuel inlet 2 enters the valve class fuel distribution cavity 6, is uniformly distributed into the valve class nozzle center micro-mixing pipes 12 through the valve class fuel distribution cavity 6, and is sprayed out together with air entering through the valve class air inlet holes 14 at the tail ends of the micro-mixing pipes, and the fuel in the valve class micro-mixing nozzles 7 is only in contact with the air at the tail ends of the valve class nozzle center micro-mixing pipes 12 and is not mixed, so that the valve class nozzles adopt a diffusion combustion mode, the combustion mode can avoid backfire of hydrogen and hydrogen-rich fuel, and can improve the starting of an engine, the ignition under low working load and the stable combustion;
compared with the existing micro-premixed combustion chamber, the micro-premixed channel in the single micro-premixed nozzle is thinned to form one-to-one mixing of a single fuel spray hole and a single air flow, so that the mixing efficiency of fuel and air can be effectively improved, the length of the premixed channel in the micro-premixed nozzle is further shortened, and the peak flame temperature in the combustion process is reduced; in addition, after the micro pre-mixing pipe in the micro pre-mixing nozzle is thinned, the cross-sectional area of the nozzle outlet is reduced, the speed of the fuel/air mixture at the outlet position is improved, tempering of hydrogen-rich fuel is inhibited, the residence time of high-temperature flue gas is reduced, and the aim of reducing the emission of nitrogen oxides is achieved.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.
Claims (8)
1. A micro-premix combustor of a center staged gas turbine, characterized in that: the novel burner comprises a valve shift, a main combustion stage, an igniter (15), a first-stage end cover (16), a second-stage end cover (17), a flame tube (18) and a flame tube outer casing (20), wherein the valve shift and the main combustion stage are concentrically arranged, the valve shift is positioned at the center of a combustion chamber, the main combustion stage is arranged at the periphery of the valve shift, the igniter (15) is arranged in a central through hole at the head of the combustion chamber, the first-stage end cover (16) and the second-stage end cover (17) are connected, a gap is arranged between the two-stage end covers, the flame tube (18) is connected with the second-stage end cover (17), the flame tube outer casing (20) is arranged outside the flame tube (18) and coaxially arranged with the flame tube (18), an air channel (19) is formed between the outer wall of the flame tube (18) and the flame tube outer casing (20), and the flame tube (18) is internally provided with a combustion chamber;
the on-duty stage comprises an on-duty stage fuel distribution cavity (6) and a plurality of on-duty stage micro-mixing nozzles (11), the on-duty stage fuel distribution cavity (6) is arranged on the periphery of a central hole of the head of the combustion chamber, and the on-duty stage fuel distribution cavity (6) is used for conveying fuel to the on-duty stage micro-mixing nozzles (11); the front end part of the on-duty fuel distribution cavity (6) is provided with an on-duty fuel inlet (2), a plurality of mounting positioning holes for mounting on-duty micro-mixing nozzles (11) are formed in a first-stage end cover (16) corresponding to the on-duty fuel distribution cavity (6), a second-stage end cover (17) is provided with on-duty nozzle air channels (13) which are in one-to-one correspondence with the on-duty micro-mixing nozzles (11), one end of each on-duty micro-mixing nozzle (11) is fixed to the mounting positioning hole of the first-stage end cover (16), the other end of each on-duty micro-mixing nozzle is inserted into the corresponding on-duty nozzle air channel (13), the on-duty micro-mixing nozzle (11) comprises an on-duty nozzle center micro-mixing pipe (12), a plurality of on-duty nozzle air inlet holes (14) are formed at the tail end of the on-duty micro-mixing nozzle center micro-mixing pipe (12), and incoming air is sprayed into the on-duty micro-mixing nozzle center micro-mixing pipe (12) from the on-duty air inlet holes (14) at the tail end of the on-duty nozzle air channels (13) on the second-stage end cover (17) from the on-duty nozzle air inlet holes (14) and is sprayed into the on-duty micro-mixing nozzle (12) at the flame center of the combustion tube (18) at the inner side of the on-duty micro-nozzle center micro-mixing nozzle (12);
the main combustion stage comprises a main combustion stage porous fuel air inlet pipe (1), a main combustion stage fuel distribution cavity (3) and a plurality of main combustion stage micro-premixing nozzles (7); the main combustion stage fuel distribution cavity (3) is arranged at the periphery of the duty stage fuel distribution cavity (6), the annular main combustion stage fuel distribution cavity (3) is uniformly divided into a plurality of fan ring areas through a plurality of partition plates (4), each fan ring area is matched with a main combustion stage porous fuel air inlet pipe (1), a plurality of fuel spray holes are formed in the tail end of the pipe wall of each main combustion stage porous fuel air inlet pipe (1), and the main combustion stage porous fuel air inlet pipes (1) extend into the corresponding fan ring areas to supply fuel for main combustion stage micro-premixing nozzles (7) in the fan ring areas;
a plurality of mounting positioning holes for mounting main-stage micro-premix nozzles (7) are formed in the first-stage end cover (16) corresponding to the main-stage fuel distribution cavity (3), a plurality of main-stage nozzle center fuel pipes (8) which are in one-to-one correspondence with the main-stage micro-premix nozzles (7) are formed in the second-stage end cover (17), the main-stage nozzle center fuel pipes (8) are communicated with the corresponding main-stage micro-premix nozzles, a plurality of main-stage nozzle micro-premix pipes (10) are uniformly arranged around each main-stage nozzle center fuel pipe (8), the main-stage nozzle center fuel pipes (8) are communicated with the corresponding main-stage nozzle micro-premix pipes (10) through main-stage nozzle fuel spray holes (9) in the pipe wall, the main-stage nozzle center fuel pipes (8) are used for conveying fuel, incoming air enters the main-stage nozzle micro-premix pipes (10) through gaps between the two-stage end covers, a fuel and air mixing zone is formed in the main-stage micro-premix pipes (10), and the mixed-stage micro-premix nozzles (18) are sprayed into the main-stage micro-premix pipes;
the first-stage end cover (16) and the second-stage end cover (17) are integrated, the front end surface of the second-stage end cover (17) is a curved surface, and a fitting function of a curved surface curve is a cubic polynomial;
the diameter of the fuel spray holes on the tail end pipe wall of the main combustion stage porous fuel air inlet pipe (1) is 0.1-1mm, and the fuel spray holes surround 2-5 layers of pipe wall arrays; the main combustion grade fuel distribution cavity (3) is divided into 4-12 fan ring areas by the partition plate (4), a plurality of layers of porous fuel rectifying plates (5) are arranged in each fan ring area, the aperture of each porous fuel rectifying plate (5) is 0.1-1mm, the number of layers of the porous fuel rectifying plates is 1-5, small holes on each layer of porous fuel rectifying plates are staggered, and the interval between every two adjacent layers is 1-5mm.
2. A center staged gas turbine micro-premix combustor as in claim 1, wherein: the diameter of the on-duty nozzle center micro-mixing pipe (12) is 2-20mm, and the length is 10-200mm; the number of the air inlet holes (14) of the on-duty micro-mixing nozzle is 4-8 along the circumferential array of the wall of the on-duty micro-mixing pipe (12) at the center of the on-duty micro-mixing nozzle; the shape of the air inlet hole (14) of the on-duty nozzle is elliptic, the length of the major axis of the elliptic is 0.5-2.5mm, the length of the minor axis of the elliptic is 0.25-2mm, or the shape of the air inlet hole (14) of the on-duty nozzle is rectangular, the length of the rectangular is 0.5-2.5mm, and the width of the rectangular is 0.25-2mm.
3. A center staged gas turbine micro-premix combustor as in claim 1, wherein: the duty-level micro-mixing nozzles (11) are circumferentially arranged for 1-4 layers; the main combustion stage micro-premixing nozzle (7) is circumferentially arranged with 2-8 layers; the diameter of the valve class micro-mixing nozzle (11) and the diameter of the main combustion stage micro-premixing nozzle (7) are 5-20mm, the distance between two adjacent valve class micro-premixing nozzles is (1.2-4) times the diameter of the valve class micro-mixing nozzle (11), and the distance between two adjacent main combustion stage micro-premixing nozzles is (1.2-4) times the diameter of the main combustion stage micro-premixing nozzle (7).
4. A center staged gas turbine micro-premix combustor as in claim 1, wherein: the diameter of the central fuel pipe (8) of the main combustion-stage nozzle is 1-5mm, the diameter of the fuel spray holes (9) of the main combustion-stage nozzle is 0.1-1mm, and the number of the fuel spray holes is 4-12; the number of the main fuel stage micro-premixing pipes (10) is the same as that of the main fuel stage nozzle fuel spray holes (9) on the pipe wall of the main fuel stage nozzle center fuel pipe (8).
5. A center staged gas turbine micro-premix combustor as in claim 1, wherein: the main combustion stage micro premix tube (10) is a straight tube or a spiral tube; the length of the main combustion stage micro premix tube (10) is 5-100mm; the cross section of the main combustion stage micro-premix pipe (10) is circular, the diameter of the circular main combustion stage micro-premix pipe (10) is 1-10mm, or the cross section of the main combustion stage micro-premix pipe (10) is elliptical, the long axis of the elliptical main combustion stage micro-premix pipe (10) is 1-10mm, the short axis is 0.5-5mm, or the cross section of the main combustion stage micro-premix pipe (10) is regular polygon, and the side length of the regular polygon main combustion stage micro-premix pipe (10) is 1-10mm; or the section of the main combustion stage micro premix pipe (10) is in a fan shape, the outer diameter of the fan-shaped main combustion stage micro premix pipe (10) is 2.5-20mm, and the inner diameter of the main combustion stage micro premix pipe is 1.5-10mm.
6. A center staged gas turbine micro-premix combustor as in claim 1, wherein: the fuel spray holes (9) of the main combustion stage nozzle are arranged in 2-5 layers around the circular array of the pipe wall, the distance between two adjacent layers is 1-2mm, each layer of array is 4-12, and each row of fuel spray holes is communicated with one main combustion stage micro-premixing pipe.
7. A central staged gas turbine micro-premix combustor as in any of claims 1-6, wherein: the length of the duty stage micro-mixing nozzle (11) is the same as the total length of the main combustion stage micro-mixing nozzle (7).
8. A center staged gas turbine micro-premix combustor as in claim 7, wherein: the total length of the main combustion stage micro-premixing nozzle (7) is 10-200mm.
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| CN114857619B (en) * | 2022-04-29 | 2024-01-26 | 江苏中科能源动力研究中心 | Micro-mixed combustion chamber of gas turbine |
| CN114992672B (en) * | 2022-06-11 | 2024-04-26 | 江苏中科能源动力研究中心 | Micro-premixing type combustion chamber of gas turbine |
| CN115342386B (en) * | 2022-07-28 | 2024-01-16 | 北京航空航天大学 | Combustion chamber nozzle structure and combustion chamber |
| CN115355536B (en) * | 2022-08-17 | 2024-02-02 | 北京理工大学 | Oxyhydrogen micro-mixed combustion device suitable for gas turbine and application method thereof |
| CN115451433B (en) * | 2022-09-22 | 2024-04-02 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle premixing system for combustion chamber of gas turbine |
| CN115451431B (en) * | 2022-09-22 | 2024-04-16 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle premixing system for combustion chamber of gas turbine |
| CN116202104B (en) * | 2023-02-06 | 2024-05-07 | 中国科学院工程热物理研究所 | Multi-nozzle array stability-increasing combustion chamber of gas turbine |
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