CN-122015128-A - Flame tube wall cooling structure, flame tube and combustion chamber

CN122015128ACN 122015128 ACN122015128 ACN 122015128ACN-122015128-A

Abstract

The invention discloses a flame tube wall cooling structure, a flame tube and a combustion chamber, which relate to the technical field of aeroengines and gas turbines and comprise a plurality of diffusion hole groups, wherein each diffusion hole group is used for being sequentially arranged on the flame tube wall along the incoming flow direction, each diffusion hole group is provided with a plurality of diffusion holes, each diffusion hole is used for being sequentially arranged along the circumferential direction of the flame tube wall, and each diffusion hole is used for penetrating through the flame tube wall along the thickness direction; the annular bulge structures are provided with a plurality of annular bulge structures, are coaxially arranged on the flame tube wall and are respectively used for bulge towards one side of the combustion chamber, the annular bulge structures are correspondingly arranged at the rear of each diffusion hole group along the incoming flow direction respectively, a cooling air film is formed between the flame tube wall surface and high-temperature fuel gas, direct impact of the high-temperature fuel gas on the flame tube wall surface can be isolated, heat insulation protection on the flame tube wall surface is realized, and the performance of the combustion chamber is optimized.

Inventors

Dong Haoqiang
PAN ZIMING
ZHANG LUMING
SUN HAIJUN
LIU YANG
Xiang Xulu
HU XIAOAN
ZHANG LIHONG
WANG XINYUE
WU YAOBIN
SUN MINGYANG

Assignees

南昌航空大学

Dates

Publication Date: 20260512
Application Date: 20260312

Claims (10)

1. A flame tube wall cooling structure, comprising: The diffusion hole groups are provided with a plurality of diffusion holes, each diffusion hole group is used for being sequentially arranged on the flame tube wall along the incoming flow direction, each diffusion hole group is provided with a plurality of diffusion holes, each diffusion hole is used for being sequentially arranged along the circumferential direction of the flame tube wall, and each diffusion hole is used for penetrating through the flame tube wall along the thickness direction; the annular bulge structures are provided with a plurality of annular bulge structures, are coaxially arranged on the flame tube wall and are used for bulge towards one side of the combustion chamber, and the annular bulge structures are correspondingly arranged behind the diffusion hole groups along the incoming flow direction respectively.
2. The cooling structure of the flame tube wall according to claim 1, wherein the diffusion holes are rectangular structures, the long sides of which extend along the circumferential direction of the flame tube wall, and the wide sides of which are parallel to the axial direction of the flame tube wall.
3. The flame tube wall cooling structure of claim 2, wherein the ratio of the length to the width of the diffusion holes is greater than 2.
4. The flame tube wall cooling structure of claim 1, wherein the surface of the annular raised structure is an arcuate surface structure.
5. The flame tube wall cooling structure of claim 4, wherein a side edge of the annular projection structure adjacent to the diffusion hole is tangential to an edge of the diffusion hole.
6. The cooling structure of the flame tube wall according to claim 4, wherein the diffusion holes are rectangular structures, the long sides of the diffusion holes extend along the circumferential direction of the flame tube wall, and the wide sides of the diffusion holes are parallel to the axial direction of the flame tube wall; the radial section of the annular bulge structure is semicircular, and the ratio of the curvature radius to the wide edge of the diffusion hole is between 0.5 and 1.
7. The flame tube is characterized by comprising an inner tube, an outer tube, a front end plate and the flame tube wall cooling structure according to any one of claims 1 to 6, wherein the inner tube and the outer tube are coaxially nested and are arranged at intervals, the inner tube and the outer tube are respectively provided with the flame tube wall cooling structure, the annular protruding structure on the inner tube is arranged on the outer circumference side of the tube wall of the inner tube, the annular protruding structure on the outer tube is arranged on the inner circumference side of the tube wall of the outer tube, the front end plate is arranged between the inner tube and the outer tube and is positioned at the same end of the inner tube and the outer tube, the outer circumference edge of the front end plate is connected with the outer tube, and the inner circumference edge of the front end plate is connected with the inner tube.
8. The liner of claim 7, wherein the front end plate is circumferentially and uniformly provided with first jet holes.
9. The flame tube of claim 8, wherein the outer barrel is sequentially provided with at least one set of first primary combustion holes, at least one set of first secondary combustion holes, and at least one set of first blending holes in an axial direction, and the inner barrel is sequentially provided with at least one set of second jet holes, at least one set of second primary combustion holes, at least one set of second secondary combustion holes, and at least one set of second blending holes in an axial direction.
10. A combustion chamber, which is characterized by comprising an outer casing, an inner casing, an evaporation pipe, an oil delivery pipe, a fuel nozzle, a supporting plate, an outlet mounting ring, a mounting plate and the flame tube according to claim 9; The flame tube comprises an outer barrel, an outer casing, an evaporation tube, an oil delivery tube, a fuel nozzle, a front end plate, an oil delivery tube, a flame tube and a flame tube, wherein the outer barrel of the flame tube is arranged in the outer casing, one end of the outer barrel is connected with the mounting plate; One end of the inner cylinder of the flame tube is connected with the front end plate, and the other end of the inner cylinder of the flame tube is connected with a supporting plate; The inner casing is positioned in the inner cylinder, one end of the inner casing is connected with the supporting plate, and the other end of the inner casing extends out from one side of the inner cylinder connected with the front end plate; one end of the outlet mounting ring is connected with the mounting plate, and the other end of the outlet mounting ring is connected with the outer casing and used for mounting the turbine guide.

Description

Flame tube wall cooling structure, flame tube and combustion chamber Technical Field The invention relates to the technical field of aeroengines and gas turbines, in particular to a flame tube wall cooling structure, a flame tube and a combustion chamber. Background The combustion chamber is used as a core hot end component of the aeroengine and the gas turbine, is an important place for the gas turbine to perform combustion chemical reaction, and the high-temperature and high-pressure gas generated by the combustion chamber pushes the turbine to rotate to do work and is finally converted into engine thrust, so that the thrust output, the combustion efficiency and the operation reliability of the engine are directly determined, and the combustion chamber is a key hub for connecting the gas compressor and the turbine, and plays a decisive role in the overall performance of the aeroengine and the gas turbine. The wall surface of the flame tube in the combustion chamber bears high-temperature fuel gas impact for a long time, the working environment is very harsh, and in addition, multiple loads such as airflow impact, thermal cycle fatigue and the like are resisted. If the wall temperature exceeds the material tolerance limit, thermal fatigue, deformation and even ablation failure can be caused, so that the service life of the flame tube is shortened, the combustion chamber is failed, and the safe and stable operation of the engine is further affected. Therefore, the flame tube has extremely high requirements on the cooling technology, high-efficiency heat insulation and cooling are needed to be realized, cooling continuity and stability are also needed to be ensured, cooling air flow consumption and flow resistance are controlled, and the influence on combustion efficiency is avoided. Cooling technology has become one of the key technologies in the core of the aero-engine and gas turbine fields. In order to achieve effective cooling and heat insulation protection of the wall surface of the flame tube, various cooling modes have been developed in the prior art, including air film cooling, convection cooling, impact cooling, various composite cooling modes, and the like. The core principle of the air film cooling is that cooling air is sprayed to the wall surface through cooling holes on the wall surface of the flame tube, a layer of low-temperature air film is formed between the wall surface and high-temperature fuel gas, and the heat transfer from the high-temperature fuel gas to the wall surface is blocked by utilizing the isolation effect of the air film. However, in the prior art, the air film cooling structure still needs to process the fish scale hole guide plate, which inevitably leads to complex processing mode, high cost and low yield. Disclosure of Invention The invention aims to provide a flame tube wall cooling structure, a flame tube and a combustion chamber, so as to solve the problems in the prior art, form a cooling air film between the flame tube wall surface and high-temperature fuel gas, isolate direct impact of the high-temperature fuel gas on the flame tube wall surface, realize heat insulation protection on the flame tube wall surface and optimize the performance of the combustion chamber. In order to achieve the above purpose, the invention provides a cooling structure for a flame tube wall, comprising: The diffusion hole groups are provided with a plurality of diffusion holes, each diffusion hole group is used for being sequentially arranged on the flame tube wall along the incoming flow direction, each diffusion hole group is provided with a plurality of diffusion holes, each diffusion hole is used for being sequentially arranged along the circumferential direction of the flame tube wall, and each diffusion hole is used for penetrating through the flame tube wall along the thickness direction; the annular bulge structures are provided with a plurality of annular bulge structures, are coaxially arranged on the flame tube wall and are used for bulge towards one side of the combustion chamber, and the annular bulge structures are correspondingly arranged behind the diffusion hole groups along the incoming flow direction respectively. Optionally, the diffusion hole is in a rectangular structure, the long edge of the diffusion hole extends along the circumferential direction of the flame tube wall, and the wide edge of the diffusion hole is parallel to the axial direction of the flame tube wall. Optionally, the ratio of the length to the width of the diffusion hole is greater than 2. Optionally, the surface of the annular protruding structure is an arc-shaped surface structure. Optionally, an edge of the annular protrusion structure near one side of the diffusion hole is tangent to an edge of the diffusion hole. Optionally, the diffusion hole has a rectangular structure, the long edge of the diffusion hole extends along the circumferential direction of the flame tube wall, and the wide edge