CN217559880U - Combustion chamber of gas turbine - Google Patents
Combustion chamber of gas turbine Download PDFInfo
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- CN217559880U CN217559880U CN202221024558.XU CN202221024558U CN217559880U CN 217559880 U CN217559880 U CN 217559880U CN 202221024558 U CN202221024558 U CN 202221024558U CN 217559880 U CN217559880 U CN 217559880U
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Abstract
A gas turbine combustion chamber belongs to the technical field of gas turbine combustion chambers. The air-conditioning device comprises an outer shell, wherein a combustion device is arranged in the outer shell, and an air inlet cavity is formed between the outer wall of the combustion device and the inner wall of the outer shell; the combustion device comprises a combustor and a flame tube, wherein the combustor is provided with a nozzle area, the flame tube is arranged on the periphery of the nozzle area, and the outer shell is provided with a flue gas outlet communicated with the flame tube; the nozzle area comprises a class micro-premixing nozzle area and a main combustion class micro-premixing nozzle area; the combustor is provided with a fuel supply area in the direction opposite to the nozzle area, the periphery of the combustor is provided with a shell covering the fuel supply area, and the fuel supply area comprises an on-duty mixing cavity and a main combustion mixing cavity; the periphery of the duty-level mixing cavity is provided with a convolute air inlet channel communicated with the air inlet cavity, the shell is provided with an air inlet communicated with the air inlet channel, and the shell is provided with an air inlet communicated with the air inlet cavity and used for supplying air to the main combustion-level mixing cavity. Thereby reducing the emission of nitrogen oxides and improving the cooling efficiency of the flame tube.
Description
Technical Field
The utility model belongs to the technical field of gas turbine combustion chamber technique and specifically relates to a gas turbine combustion chamber.
Background
The gas turbine has become an indispensable power source in industrial production due to the efficient cleaning characteristic, the gas turbine is continuously developed towards higher efficiency and wider load regulation range along with the iterative update of the technology, and the method for improving the cycle efficiency is mainly realized by improving the combustion temperature and pressure, while the contradictory is that along with the increase of the combustion temperature and pressure, on one hand, the generation amount of nitrogen oxides is rapidly increased, and on the other hand, due to the influence of dual factors of the quality reduction of cooling gas and the increase of the combustion temperature, the wall surface of a flame tube is more difficult to cool, so that how to realize safe, stable and low-emission combustion in the wide load working condition range is an important performance target of a gas turbine combustor.
Most of existing gas turbines adopt a combustor of a Dry Low nitrogen oxide (Dry Low NOx, DLN) combustion technology, the combustor mainly adopts a lean premixed gas formed by mixing excess air and fuel, so as to inhibit the generation of nitrogen oxide, but a combustion engine develops to a J level, the temperature level of the combustion engine is close to the critical value of a DLN effective working range (1670-1900K), if the temperature is further increased, the emission of nitrogen oxide is greatly increased even if the air and the fuel are completely premixed, and on the other hand, the conventional swirl premixed combustion mode is adopted, so that the risks of tempering, self-ignition, thermoacoustic oscillation and the like exist, and therefore the Dry Low nitrogen oxide (Dry Low NOx, DLN) combustion technology cannot meet the development of the gas turbines.
Therefore, it is urgently needed to provide a micro-mixed combustion chamber of a gas turbine, which reduces the emission of nitrogen oxides and improves the cooling efficiency of a flame tube, thereby realizing safe, stable and low-emission combustion in a wide load range.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that it provides one kind to can reduce nitrogen oxide and discharge, improve flame tube cooling efficiency to the not enough of prior art to realize safe, stable, the low gas turbine combustor that discharges the burning under the wide load range.
The technical problem to be solved by the utility model is realized by the following technical scheme, the utility model relates to a combustion chamber of a gas turbine, which is characterized by comprising an outer shell, a combustion device is arranged in the outer shell, an air inlet cavity is formed between the outer wall of the combustion device and the inner wall of the outer shell, and an air inlet communicated with the air inlet cavity is arranged on the outer shell;
the combustion device comprises a combustor and a flame tube, the combustor is provided with a nozzle area, the flame tube is arranged on the periphery of the nozzle area, and the outer shell is provided with a flue gas outlet communicated with the flame tube; the nozzle area comprises a duty-class micro-premixing nozzle area arranged in the middle and a main combustion-class micro-premixing nozzle area arranged on the periphery of the duty-class micro-premixing nozzle area;
the combustor is provided with a fuel supply area in the direction opposite to the nozzle area, a shell covering the fuel supply area is installed on the periphery of the combustor, and the fuel supply area comprises an on-duty mixing cavity for providing gas for the on-duty micro-premixing nozzle area and a main combustion mixing cavity for providing gas for the main combustion micro-premixing nozzle area; a convolute air inlet channel communicated with the air inlet cavity is arranged at the periphery of the duty level mixing cavity, an air inlet communicated with the air inlet channel is arranged on the shell, and a duty level fuel pipe for providing fuel is arranged in the duty level mixing cavity; the shell is provided with a plurality of air inlets which are communicated with the air inlet cavity and supply air to the main combustion stage mixing cavity, and the main combustion stage mixing cavity is internally provided with a main combustion stage fuel pipe for supplying fuel.
The utility model discloses the technical problem that will solve can also further realize through following technical scheme, the class fuel pipe on duty is equipped with 1, the class fuel pipe is fired mainly and is equipped with 2 at least.
The utility model discloses the technical problem that will solve can also further realize through following technical scheme, the class of on duty fuel pipe in the mixed intracavity of class on duty has the class of fuel branch pipe on duty at exit end circumference equipartition, it is equipped with fuel respectively and portal on the class of fuel branch pipe on duty.
The utility model discloses the technical problem that will solve can also further realize through following technical scheme, the main grade fuel pipe exit end circumference equipartition of burning in the mixed intracavity of level of burning has the main grade fuel branch pipe of burning.
The utility model discloses the technical problem that will solve can also further realize through following technical scheme, the size of inlet port equals and dredges the setting after preceding secret on the casing.
The utility model discloses the technical problem that will solve can also further realize through following technical scheme, inlet channel reduces along the air inlet to the sectional area of level on duty hybrid chamber gradually.
Compared with the prior art, the utility model has the advantages that,
(1) Compared with the traditional combustor, each micro premix pipe of the main nozzle of the combustor is relatively independent, and modular array expansion is carried out according to load requirements, so that the combustor has better expansibility; the micro-mixing pipe nozzle is arranged at millimeter level, the flow velocity in the micro-mixing pipe is higher, the tempering problem can be effectively avoided, the residence time of high-temperature flue gas is shortened, and the emission of nitrogen oxides is reduced.
(2) The mixing cavity is combined with the micro-mixing pipe to form a two-stage mixing mode, and fuel and air are mixed in a millimeter scale, so that more uniform fuel and air premixed gas compared with the traditional swirl premixed burner can be obtained, the peak flame temperature in the combustion process can be reduced, and the better nitrogen oxide emission reduction effect can be realized; because the flame formed by the micro mixing pipe is short and uniform in temperature distribution, the length of the flame tube of the combustion chamber can be greatly shortened.
(3) The micro-premixing pipes are distributed in an array form, so that the sprayed flame is relatively dispersed in the radial direction, the heat release is relatively uniform, meanwhile, the micro-premixing pipes of the main nozzles can adopt different structural schemes, the inherent frequency difference is realized, the thermo-acoustic coupling probability is reduced, and the problem of unstable combustion can be effectively avoided.
(4) The rotary air inlet structure matched with the flame tube fins on the class is beneficial to improving the combustion air mixing uniformity, reducing the emission and improving the combustion performance of the combustor; the air on-way distance is increased while the turbulence intensity of the gas mixture is improved, and flame stabilization is facilitated, so that the stable operation boundary of the combustor is widened, the heat exchange time of the wall surface of the flame tube and cooling air is prolonged, and the cooling efficiency of the wall surface of the flame tube is improved.
Drawings
FIG. 1 is a schematic sectional view of a combustion chamber;
FIG. 2 is a schematic front view of a combustion chamber;
FIG. 3 is a schematic view of the structure of the combustor basket;
FIG. 4 is a schematic sectional view of the burner in front elevation;
FIG. 5 is a schematic top cross-sectional view of a combustor;
FIG. 6 is a schematic view of an on-duty fuel tube configuration;
FIG. 7 is a schematic view of a main combustion stage fuel pipe structure.
In the figure: 1. a combustion device; 2. an outer housing; 21. an air inlet; 22. the direction of air flow; 3. a flame tube; 31. a convoluted fin; 32. a primary combustion stage combustion zone; 33. a class burning zone; 34. an air intake chamber; 4. a burner; 41. a primary fuel stage fuel pipe; 41A, a main combustion stage fuel inlet; 41B main combustion stage fuel branch; 42. an on-duty fuel line; 42A, an on-duty fuel inlet; 42B, an on-duty fuel branch pipe; 42C, an on-duty fuel outlet; 43. a primary combustion stage mixing chamber; 43A, air intake; 44. a class mixing chamber; 45. a primary combustion stage micro-premix nozzle zone; 46. a class micro-premix nozzle zone; 47. an intake passage; 48. a fuel flow direction; 49. the mixed gas flows in the direction.
Detailed Description
The following further describes embodiments of the present invention in order to facilitate further understanding of the present invention by those skilled in the art, and does not constitute a limitation to the right thereof.
Referring to fig. 1-7, a combustion chamber of a gas turbine comprises an outer shell, a combustion device is arranged in the outer shell, an air inlet cavity is formed between the outer wall of the combustion device and the inner wall of the outer shell, and an air inlet communicated with the air inlet cavity is arranged on the outer shell;
the combustion device comprises a combustor and a flame tube, the combustor is provided with a nozzle area, the flame tube is arranged on the periphery of the nozzle area, and the outer shell is provided with a flue gas outlet communicated with the flame tube; the nozzle area comprises a duty-class micro-premixing nozzle area arranged in the middle and a main combustion-class micro-premixing nozzle area arranged on the periphery of the duty-class micro-premixing nozzle area;
the combustor is provided with a fuel supply area in the direction opposite to the nozzle area, a shell covering the fuel supply area is installed on the periphery of the combustor, and the fuel supply area comprises an on-duty mixing cavity for supplying gas to the on-duty micro-premixing nozzle area and a main combustion mixing cavity for supplying gas to the main combustion micro-premixing nozzle area; a convoluted air inlet channel communicated with the air inlet cavity is arranged on the periphery of the duty-level mixing cavity, an air inlet communicated with the air inlet channel is arranged on the shell, and a duty-level fuel pipe for supplying fuel is arranged in the duty-level mixing cavity; the shell is provided with a plurality of air inlets which are communicated with the air inlet cavity and supply air to the main combustion stage mixing cavity, and the main combustion stage mixing cavity is internally provided with a main combustion stage fuel pipe for supplying fuel.
The class fuel pipe on duty is equipped with 1, main burning level fuel pipe is equipped with 2 at least.
The on-duty fuel branch pipes are circumferentially and uniformly distributed at the outlet ends of the on-duty fuel pipes in the on-duty mixing cavity, and the on-duty fuel branch pipes are respectively provided with fuel outlets.
And main combustion grade fuel branch pipes are uniformly distributed at the outlet end of the main combustion grade fuel pipe in the main combustion grade mixing cavity in the circumferential direction.
The sizes of the air inlets are equal, and the air inlets are densely arranged in the front and sparsely arranged in the back of the shell.
The cross-sectional area of the intake passage decreases along the intake port to the on-duty mixing chamber.
Referring to fig. 1 to 5, the present embodiment discloses a gas turbine combustor including: the burner device 1, the outer casing 2, the flame tube 3, the swirl fin 31, the burner 4, the main fuel stage fuel pipe 41, the on-duty fuel pipe 42, the main fuel stage mixing chamber 43, the on-duty mixing chamber 44, the main fuel stage micro-premix nozzle region 45, the on-duty micro-premix nozzle region 46, and the air intake passage 47.
The outer shell 2 is provided with an air inlet 21, compressed air flows into the outer shell 2 along an air flow direction 22 through the air inlet 21, flows into an air inlet cavity 34 along a cavity channel in the rotary fin in an upstream rotating mode, and finally flows into a main combustion stage mixing cavity 43 and an on-duty mixing cavity 44 through an air inlet 43A and an air inlet channel 47 respectively, the flame tube forms a main combustion stage combustion zone 32 in a main combustion stage micro-premixing nozzle zone communication area, an on-duty combustion zone 33 is formed in an area communicated with the on-duty micro-premixing nozzle zone, and the on-duty combustion zone is arranged inside the main combustion stage combustion zone;
referring to fig. 4-5, the burner 4 adopts a staged combustion mode of main combustion stage and on-duty stage, and two main combustion stage fuel pipes 41 and one value stage fuel pipe 42 are disposed at the front end of the burner 4, wherein the main combustion stage fuel pipes 41 are symmetrically distributed, and the on-duty stage fuel pipe 42 is disposed on the central line of the burner body 4 and is respectively communicated with a main combustion stage mixing chamber 43 and an on-duty stage mixing chamber 44. A plurality of main nozzle micro-premixing pipes are arranged in the main combustion stage micro-premixing nozzle area 45 and are arranged in a staggered mode, so that the influence of outer-layer pipe bundle air intake on inner-layer pipe bundle air intake is reduced, a plurality of value-class nozzle micro-premixing pipes are arranged in the value-class micro-premixing nozzle area 46, and the number of layers is preferably 1-2; in this embodiment, the number of layers is 1, and the main combustion stage micro premixing nozzle region 45 surrounds the number stage micro premixing nozzle region 46 by 360 degrees, which is beneficial to flame propagation and flame stabilization. In addition, the outer wall surface of the main combustion stage mixing cavity is provided with air inlet holes 43A along the axial direction, and the distance between the air inlet holes 43A is gradually increased along the axial direction; 3 air inlet channels 47 of the on-duty mixing chamber are uniformly arranged in the circumferential direction of the on-duty mixing chamber 44, the inlets and outlets of the convoluted air inlet channels 47 are long strips, the area of the inlets of the air inlet channels 47 is smaller than that of the outlets, the air inlet channels 47 are obliquely arranged, the rotating direction of the air inlet channels is consistent with the rotating direction of air, and the air inlet structures of the on-duty mixing chamber are matched with the convoluted fins 31 of the flame tube, so that the air flow loss is reduced on one hand, and on the other hand, after the air enters the on-duty mixing chamber 44 through the air inlet channels 47, the air is rotationally mixed with the fuel in the on-duty mixing chamber 44, so that the mixing uniformity of the fuel and the air is improved, the emission is reduced, the turbulence intensity of the mixed gas is improved, the stability of flame is improved, and the stable operation boundary of the combustor is widened;
referring to fig. 6-7, the fuel flows into the main combustion stage mixing chamber 43 and the duty mixing chamber 44 through the main combustion stage fuel inlet 41A and the duty fuel inlet 42A along the fuel flow direction 48, respectively, the fuel is uniformly dispersed in the mixing chamber and mixed with the air, then flows into the main combustion stage micro-premixing nozzle region 45 and the duty micro-premixing nozzle region 46, respectively, and flows out of the burner body after further mixing, and finally the mixed premixed gas flows into the combustion region of the flame tube in the combustion chamber to participate in the combustion in the main combustion stage combustion region 33 and the duty combustion region 34, respectively.
The main outlet pipeline of the duty fuel pipe 42 is provided with duty fuel branch pipes 42B, preferably, the duty fuel branch pipes 42B are provided with at least 2 and are uniformly arranged along the circumferential direction, and the number of the duty fuel branch pipes 42B is 3 in the embodiment; the on-duty fuel branch pipes 42B are further provided with air outlet holes 42C respectively, the number of the air outlet holes 42C on each on-duty fuel branch pipe 42B is equal and at least 2 air outlet holes are arranged, in the embodiment, the number of the air outlet holes is 2, the size of the air outlet holes is equal, and the air outlet holes face the direction opposite to the rotation direction of the air inlet channel of the on-duty micro premixing area, so that the mixing uniformity of the fuel and the air is improved, and the emission of nitrogen oxides is reduced.
Similarly, the outlet pipes of the main stage fuel pipes 41 are provided with main stage fuel branch pipes 41B, in this embodiment, 3 main stage fuel branch pipes 41B are uniformly arranged on each main stage fuel pipe 41 along the circumferential direction, the fuel outlet direction is perpendicular to the main stage fuel pipe axis, and finally enters the combustion zone of the flame tube along the direction of the mixed gas flow direction 49, the fuel flow direction is opposite to the outer ring cavity air inlet direction, so that the fuel and the air are opposite to each other, and the main stage fuel air mixing uniformity is improved.
Although specific embodiments of the present invention have been described above, it will be understood by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and the principles of the present invention, and these changes and modifications are all within the scope of the present invention.
Claims (6)
1. A gas turbine combustor characterized by: the air inlet cavity is formed between the outer wall of the combustion device and the inner wall of the outer shell, and an air inlet communicated with the air inlet cavity is formed in the outer shell;
the combustion device comprises a combustor and a flame tube, the combustor is provided with a nozzle area, the flame tube is arranged on the periphery of the nozzle area, and the outer shell is provided with a flue gas outlet communicated with the flame tube; the nozzle area comprises a duty-class micro-premixing nozzle area arranged in the middle and a main combustion-class micro-premixing nozzle area arranged at the periphery of the duty-class micro-premixing nozzle area;
the combustor is provided with a fuel supply area in the direction opposite to the nozzle area, a shell covering the fuel supply area is installed on the periphery of the combustor, and the fuel supply area comprises an on-duty mixing cavity for providing gas for the on-duty micro-premixing nozzle area and a main combustion mixing cavity for providing gas for the main combustion micro-premixing nozzle area; a convoluted air inlet channel communicated with the air inlet cavity is arranged on the periphery of the duty-level mixing cavity, an air inlet communicated with the air inlet channel is arranged on the shell, and a duty-level fuel pipe for supplying fuel is arranged in the duty-level mixing cavity; the shell is provided with a plurality of air inlets which are communicated with the air inlet cavity and supply air to the main combustion stage mixing cavity, and the main combustion stage mixing cavity is internally provided with a main combustion stage fuel pipe for supplying fuel.
2. The gas turbine combustor of claim 1, wherein: the class fuel pipe on duty is equipped with 1, main burning level fuel pipe is equipped with 2 at least.
3. The gas turbine combustor of claim 1, wherein: the on-duty fuel branch pipes are circumferentially and uniformly distributed at the outlet end of the on-duty fuel pipe in the on-duty mixing cavity, and the on-duty fuel branch pipes are respectively provided with fuel outlets.
4. The gas turbine combustor of claim 1, wherein: and main combustion grade fuel branch pipes are uniformly distributed at the outlet end of the main combustion grade fuel pipe in the main combustion grade mixing cavity in the circumferential direction.
5. The gas turbine combustor of claim 1, wherein: the sizes of the air inlets are equal, and the air inlets are arranged on the shell in a dense mode and a sparse mode.
6. The gas turbine combustor of claim 1, wherein: the cross-sectional area of the air inlet channel from the air inlet to the duty-stage mixing cavity is gradually reduced.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221024558.XU CN217559880U (en) | 2022-04-29 | 2022-04-29 | Combustion chamber of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221024558.XU CN217559880U (en) | 2022-04-29 | 2022-04-29 | Combustion chamber of gas turbine |
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| Publication Number | Publication Date |
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| CN217559880U true CN217559880U (en) | 2022-10-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202221024558.XU Active CN217559880U (en) | 2022-04-29 | 2022-04-29 | Combustion chamber of gas turbine |
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| CN (1) | CN217559880U (en) |
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2022
- 2022-04-29 CN CN202221024558.XU patent/CN217559880U/en active Active
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