A combustion chamber flame tube wall structure applied to combustion chamber-turbine cooling

Abstract

The present application belongs to the technical field of gas turbine turbine blade cooling, and particularly relates to a combustion chamber flame tube wall surface structure applied to combustion chamber-turbine cooling. In use, high-pressure cooling gas from a high-pressure compressor is injected into a pre-rotation cooling hole in a cooling cavity. The cooling gas forms a circumferential velocity component on the outer wall of the flame tube on the side close to the inner wall of the flame tube due to the guiding effect of the pre-rotation cooling hole configuration. The cooling gas impacts the downstream of the outer wall of the flame tube laterally, thereby cooling the flame tube and flowing downward to the leading edge plate of the guide vane upper end wall, forming a cooling gas film at the leading edge plate of the guide vane upper end wall to isolate the high-temperature main stream from the wall surface and protect the wall surface from erosion by the high-temperature main stream.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of gas turbine turbine blade cooling, and particularly relates to a combustion chamber flame tube wall surface structure applied to combustion chamber-turbine cooling. BACKGROUND

[0002] An aero-engine is a kind of crown of today's industry, and represents the top industrial design and manufacturing capacity of a country. As one of the most important parameters of an aero-engine, turbine inlet temperature has a great influence on the overall performance of the aero-engine. The increase of the turbine inlet temperature can not only increase the thrust of the engine, but also can adjust the cycle efficiency of the engine through the increase of the pressure ratio. Therefore, increasing the turbine inlet temperature has become a design target pursued by engineers. At present, the turbine inlet temperature of an advanced aero-engine has exceeded 2000K. Such extremely high temperature has exceeded the temperature resistance limit of turbine materials. Therefore, corresponding cooling technology must be adopted. The original component-level cooling design separately designs the turbine blade and end wall cooling, and the combustion chamber flame tube cooling is also designed as a separate design part. For the blade, the current main cooling scheme adopts a combination of internal convection, impingement cooling and external film cooling to play a heat protection role for the turbine blade. For the end wall, firstly, the film cooling on the flame tube is used to cool the wall surface. Through the design of the temperature type of the combustion chamber outlet, the temperature type of the end wall is made to be low on both sides and high in the middle, so as to reduce the cooling difficulty of the blade tip, blade root and end wall of the guide vane and moving vane, thereby reducing the amount of cooling gas. Secondly, the film cooling hole is designed on the end wall to achieve the cooling design purpose. Through the coverage of the cooling gas, the heat flux is reduced, and then the temperature load is reduced. For the flame tube cooling, the film cooling holes of different sizes are opened on the flame tube. The cooling gas adheres to the inner side of the flame tube wall surface passage, so as to isolate the main flow from the flame tube, thereby achieving the purpose of heat protection.

[0003] In the prior art, there is no structure and method for cooling the cooling holes of the combustion chamber flame tube and the turbine guide vane leading edge plate as a whole. SUMMARY

[0004] The application aims to provide a combustion chamber flame tube wall surface structure applied to combustion chamber-turbine cooling to solve the above problems.

[0005] To achieve the above-mentioned purpose, the application provides the following scheme.

[0006] A combustion chamber flame tube wall structure applied to combustion chamber-turbine cooling, comprising: a guide vane lower end wall, a bottom end of a guide vane blade body is fixedly connected to a top surface of the guide vane lower end wall, a top end of the guide vane blade body is fixedly connected to a guide vane upper end wall, a guide vane upper end wall leading edge plate is fixedly connected to one end of the guide vane upper end wall close to an air flow inlet, the guide vane upper end wall leading edge plate is located on a side of the guide vane upper end wall away from the guide vane blade body, a flame tube outer wall surface is installed on the guide vane upper end wall leading edge plate through a guide vane sealing sheet, and an aperture structure is arranged on the guide vane sealing sheet.

[0007] One end of the guide vane lower end wall close to the air flow inlet is fixedly connected to a guide vane lower end wall leading edge plate, the guide vane lower end wall leading edge plate is located on a side of the guide vane lower end wall away from the guide vane blade body, and a flame tube inner wall surface is gap-fitted to a side of the guide vane lower end wall leading edge plate away from the guide vane lower end wall.

[0008] A plurality of pre-rotation cooling holes are arranged on the flame tube outer wall surface, the plurality of pre-rotation cooling holes are located at a downstream of the flame tube outer wall surface, and the plurality of pre-rotation cooling holes are arranged at equal intervals along a direction perpendicular to the air flow.

[0009] Preferably, a short side of a first L-shaped plate is fixedly connected to a side of the flame tube outer wall surface downstream away from the flame tube inner wall surface, the first L-shaped plate is located at an end of the flame tube outer wall surface, a long side of the first L-shaped plate protrudes from the flame tube outer wall surface and is fixedly connected to a bottom end of a long side of a second L-shaped plate arranged vertically, a short side of the second L-shaped plate is fixedly connected to the guide vane sealing sheet, a long side of the first L-shaped plate has a thickness q, a thickness of the flame tube outer wall surface is k, an included angle a exists between the long side of the first L-shaped plate and a top surface of the flame tube outer wall surface, a downstream end of the flame tube outer wall surface protrudes from the short side of the first L-shaped plate by a length l, a first gap is left between the top surface of the flame tube outer wall surface and the long side of the first L-shaped plate, a width of the first gap is m, the plurality of pre-rotation cooling holes are arranged on the long side of the first L-shaped plate and communicate with the first gap, a distance between an axis of the pre-rotation cooling hole and the first L-shaped plate is x, a distance between the long side of the second L-shaped plate and the guide vane upper end wall is p, a diameter of the pre-rotation cooling hole is D, the pre-rotation cooling hole is inclined along a circumferential direction of the first L-shaped plate, and an inclination angle b is arranged between the pre-rotation cooling hole and a radius of the first L-shaped plate.

[0010] Preferably, the thickness k of the flame tube outer wall surface is 1 mm to 2 mm.

[0011] Preferably, the included angle a between the long side of the first L-shaped plate and the top surface of the flame tube outer wall surface is 70° to 90°.

[0012] Preferably, the downstream end of the flame tube outer wall surface protrudes from the short side of the first L-shaped plate by a length l of 3 mm to 5 mm.

[0013] Preferably, the distance x between the axis of the pre-rotation cooling hole and the bending of the first L-shaped plate is 3-5 mm.

[0014] Preferably, the length thickness q of the first L-shaped plate is 1-2 mm.

[0015] Preferably, the width m of the first gap is 2-3.5 mm.

[0016] Preferably, the diameter D of the pre-rotation cooling hole is 0.5-1 mm.

[0017] Preferably, the angle β between the pre-rotation cooling hole and the radius of the first L-shaped plate is 30-60°.

[0018] Compared with the prior art, the present application has the following advantages and technical effects:

[0019] In use, the high-pressure cooling gas from the high-pressure compressor is injected into the pre-rotation cooling hole from the cooling cavity, and the cooling gas forms a circumferential velocity component on the side of the outer wall of the flame tube close to the inner wall of the flame tube due to the guiding effect of the pre-rotation cooling hole configuration. The cooling gas impacts on the downstream of the outer wall of the flame tube, which cools the flame tube and flows downward to the leading edge plate of the guide vane upper end wall, forming a cooling gas film to isolate the high-temperature mainstream from the wall surface and protect the wall surface from erosion by the high-temperature mainstream. BRIEF DESCRIPTION OF DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor based on these drawings:

[0021] Figure 1 is the isometric view of the present application;

[0022] Figure 2 is the right view of the present application;

[0023] Figure 3 is the A-A sectional view of the present application; Figure 2

[0024] Figure 4 is the schematic diagram of the circumferential average gas film adiabatic cooling efficiency along the dimensionless axial direction at the upper end wall of the flame tube when designed with cooling gas and without cooling gas, respectively;

[0025] Figure 5 ​The schematic diagram of the circumferential average film adiabatic cooling efficiency along the dimensionless axial direction at the upper end wall of the flame tube when the cooling gas is designed, without the cooling gas, and with the pre-rotation cooling gas, respectively.

[0026] Wherein, 1, the guide vane lower end wall; 2, the guide vane blade; 3, the guide vane upper end wall; 4, the blade lower end wall leading edge plate; 5, the guide vane upper end wall leading edge plate; 6, the flame tube inner wall surface; 7, the guide vane sealing sheet; 8, the pre-rotation cooling hole; 9, the flame tube outer wall surface. DETAILED DESCRIPTION

[0027] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of the present application.

[0028] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the present application will be further described in detail below with reference to the drawings and specific embodiments.

[0029] Reference Figures 1 to 3 The present application discloses a combustion chamber flame tube wall surface structure applied to combustion chamber-turbine cooling, comprising: a guide vane lower end wall 1, the top surface of the guide vane lower end wall 1 is fixedly connected with the bottom end of a guide vane blade 2, the top end of the guide vane blade 2 is fixedly connected with a guide vane upper end wall 3, one end of the guide vane upper end wall 3 close to the air inlet is fixedly connected with a guide vane upper end wall leading edge plate 5, the guide vane upper end wall leading edge plate 5 is located on the side of the guide vane upper end wall 3 away from the guide vane blade 2, the guide vane upper end wall leading edge plate 5 is installed with a flame tube outer wall surface 9 through a guide vane sealing sheet 7, and the guide vane sealing sheet 7 is provided with an aperture structure.

[0030] One end of the guide vane lower end wall 1 close to the air inlet is fixedly connected with a guide vane lower end wall leading edge plate 4, the guide vane lower end wall leading edge plate 4 is located on the side of the guide vane lower end wall 1 away from the guide vane blade 2, and the side of the guide vane lower end wall leading edge plate 4 away from the guide vane lower end wall 1 is gap-fitted with a flame tube inner wall surface 6.

[0031] A plurality of pre-rotation cooling holes 8 are formed on the flame tube outer wall surface 9, the plurality of pre-rotation cooling holes 8 are all located at the downstream of the flame tube outer wall surface 9, and the plurality of pre-rotation cooling holes 8 are arranged at equal intervals along the direction perpendicular to the air flow.

[0032] Further optimization scheme, the downstream side of the outer wall surface 9 of the flame tube is fixed with the short side of the first L-shaped plate, the first L-shaped plate is located at the end of the outer wall surface 9 of the flame tube, the long side of the first L-shaped plate extends out of the outer wall surface 9 of the flame tube and is fixed with the bottom end of the long side of the second L-shaped plate arranged vertically, the short side of the second L-shaped plate is fixed with the guide vane sealing piece 7, the long side of the first L-shaped plate has a thickness q, the thickness of the outer wall surface 9 of the flame tube is k, there is an angle α between the long side of the first L-shaped plate and the top surface of the outer wall surface 9 of the flame tube, the downstream end of the outer wall surface 9 of the flame tube extends out of the short side of the first L-shaped plate by a length l, a first gap is left between the top surface of the outer wall surface 9 of the flame tube and the long side of the first L-shaped plate, the width of the first gap is m, a plurality of pre-rotation cooling holes 8 are arranged on the long side of the first L-shaped plate and communicate with the first gap, the axis of the pre-rotation cooling hole 8 is at a distance x from the bending part of the first L-shaped plate, the long side of the second L-shaped plate is at a distance p from the guide vane upper end wall 3, the diameter of the pre-rotation cooling hole 8 is D, the pre-rotation cooling hole 8 is inclined along the circumference of the first L-shaped plate, and an inclination angle β is arranged between the pre-rotation cooling hole 8 and the radius of the first L-shaped plate.

[0033] Further optimization scheme, the thickness k of the outer wall surface 9 of the flame tube is 1mm-2mm.

[0034] Further optimization scheme, the angle α between the long side of the first L-shaped plate and the top surface of the outer wall surface 9 of the flame tube is 70°-90°.

[0035] Further optimization scheme, the length l of the downstream end of the outer wall surface 9 of the flame tube extending out of the short side of the first L-shaped plate is 3mm-5mm.

[0036] Further optimization scheme, the distance x of the axis of the pre-rotation cooling hole 8 from the bending part of the first L-shaped plate is 3mm-5mm.

[0037] Further optimization scheme, the thickness q of the long side of the first L-shaped plate is 1mm-2mm.

[0038] Further optimization scheme, the width m of the first gap is 2mm-3.5mm.

[0039] Further optimization scheme, the diameter D of the pre-rotation cooling hole 8 is 0.5mm-1mm.

[0040] Further optimization scheme, the inclination angle β between the pre-rotation cooling hole 8 and the radius of the first L-shaped plate is 30°-60°.

[0041] One specific example: In order to ensure the simplicity of the description, the structure is simplified, and the structural unit in a single rotation period is described, that is, the two sides of the unit can be completely coincident after rotating a certain angle along a certain rotation axis.

[0042] The structure of the application comprises a guide vane lower end wall 1, a guide vane blade body 2, a guide vane upper end wall 3, a guide vane lower end wall leading edge plate 4, a guide vane upper end wall leading edge plate 5, a flame tube inner wall surface 6, a guide vane sealing piece 7, a pre-rotation cooling hole 8 and a flame tube outer wall surface 9. The guide vane lower end wall 1, the guide vane blade body 2 and the guide vane upper end wall 3 jointly constitute a guide vane gas passage; the flame tube inner wall surface 6 and the flame tube outer wall surface 9 jointly constitute a gas passage at the tail side of the combustion chamber, and the two passages jointly constitute a high-temperature main flow passage.

[0043] The guide vane lower end wall leading edge plate 4 is arranged opposite to the flame tube inner wall surface 6, and the guide vane upper end wall leading edge plate 5 is arranged opposite to the flame tube outer wall surface 9. Since the assembly gap of the combustion chamber and the guide vane turbine jointly constitutes a slot cooling groove on the upper and lower surfaces, the cooling gas corresponding to the cooling slot of the guide vane lower end wall leading edge plate 4 is directly blown out from the gap, and the cooling groove corresponding to the guide vane upper end wall leading edge plate 5 is supplied with gas into the slot groove at the upstream position thereof due to the structure of the guide vane sealing piece 7. The guide vane sealing piece 7 is provided with a large bolt mounting hole and four small leakage holes, and the leakage holes are mainly distributed in two sides of the blade passage.

[0044] The pre-rotation cooling hole 8 is located on the boss wall surface (first L-shaped plate) of the flame tube outer wall surface 9. The boss wall surface can be defined by several structural parameters. The thickness of the boss wall surface is q, which is 1-2 mm. The thickness q defines the thickness of the wall surface where the pre-rotation cooling hole 8 is located. The original thickness of the flame tube is defined as k, which is 1-2 mm. In order to match the pre-rotation cooling hole 8, the downstream of the flame tube outer wall surface 9 has a stepped wall surface. In order to ensure that the blade height of the guide vane remains basically unchanged during the extension process, the stepped wall surface has a certain inclination angle, which is defined as α and is between 70° and 90°. The flame tube outer wall surface 9 extends downward to the stepped wall surface to form a baffle with a length of l to form a baffle, which cooperates with the pre-rotation cooling hole 8 to achieve the cooling purpose. The length l of the baffle is between 35 and 50 mm. The extended baffle and the stepped wall surface have a spacing of m, so that the cooling gas has enough development space. The flame tube outer wall surface 9 describes a typical flame tube structure in an aero-engine. The original cooling hole is vertically inward in the wall surface direction on the boss-shaped wall surface, which also has a certain cooling effect. The pre-rotation cooling hole 8 is improved on the basis of the original structure, thereby improving the utilization efficiency of the cooling gas. Figure 3 As shown in the figure, the hole structure is designed on the boss wall surface with a thickness of q. In a single cycle structure, there are ten pre-rotation cooling holes 8. The hole diameter D of the pre-rotation cooling hole 8 is between 0.5 and 1.5 mm and can be changed according to design needs. The pre-rotation angle β of the pre-rotation cooling hole 8 is defined as β, which can be seen from Figure 3 The pre-rotation angle β is actually the included angle between the center line of the hole and the radius line of the hole. β is between 30° and 60° and is designed according to the requirements of engineers.

[0045] A method for guiding flow applied to a combustion chamber flame tube wall structure for combustion chamber-turbine cooling, which adopts a combustion chamber flame tube wall structure for combustion chamber-turbine cooling, high-pressure cooling air from a high-pressure compressor is injected into a pre-rotation cooling hole 8 in a cooling cavity, and the cooling air forms a circumferential velocity component in the circumferential direction due to the guiding effect of the pre-rotation cooling hole 8, and impacts on the downstream end of the outer wall 9 of the flame tube, thereby cooling the outer wall 9 of the flame tube, and flowing downward to the leading edge plate 5 of the upper end wall of the guide vane, and forming a cooling air film at the leading edge plate 5 of the upper end wall of the guide vane, thereby isolating the high-temperature main flow from the leading edge plate 5 of the upper end wall of the guide vane, and protecting the leading edge plate 5 of the upper end wall of the guide vane from erosion by the high-temperature main flow.

[0046] q is selected as 1.5 mm, k is selected as 1.5 mm, a is selected as 75°, the length of l is 40 mm, and the interval m is 1.7 mm, a corresponding model is constructed, the fluid domain for simulation is obtained by subtracting the engine structure from the outside bulk volume by using the Boolean operation of UG, and simulation calculation is performed after the fluid domain is meshed, and it should be noted that the working condition adopted in the simulation is completely same as that used in the GE-E3 blade experiment, the main flow temperature is 709K, the secondary flow cooling air is 500K, and the cooling air flow ratio is adjusted by adjusting the total pressure of the cooling air cavity In the simulation without cooling air, the original cooling air channel is deleted, and corresponding simulation is performed, and when the non-pre-rotation cooling air structure is used, only the cooling air hole is changed to non-pre-rotation, and the remaining structure is completely same as that of the pre-rotation structure.

[0047] Figure 4 The curves show the circumferential average adiabatic film cooling temperature distribution along the axial direction of the upper end wall 3 of the guide vane with and without cooling air, and it can be seen from the curves that the adiabatic cooling efficiency of the surface of the upper end wall 3 of the guide vane is completely zero without cooling air, and the circumferential average adiabatic film cooling efficiency of the upper end wall 3 of the guide vane rapidly increases after the cooling air is added, reaches the maximum value 0.278 at the dimensionless position of zero, and continuously rises away from the wall under the action of the secondary flow of the end wall, which is reflected in the curve that the circumferential average adiabatic film cooling efficiency continuously decreases along the axial direction. The cooling air can obviously protect the upper end wall 3 of the guide vane, and the adiabatic cooling temperature of the upper end wall 3 of the guide vane is significantly reduced, and in order to better exert the cooling potential of the cooling air, the pre-rotation cooling air structure is used. Figure 5The curves of the axial distribution of the adiabatic gas film cooling temperature of the cooling gas with the cooling gas, without the cooling gas, and with the pre-rotation cooling hole 8 are shown. It can be seen that the cooling gas itself has a certain cooling effect. When the pre-rotation cooling hole 8 is added, the cooling effect in the axial direction is very excellent, and increases along the flow direction. In the area with a dimensionless position less than 50%, the cooling efficiency brought by the pre-rotation cooling hole 8 is very obvious. The circumferentially averaged adiabatic gas film cooling efficiency is increased by 78% at the dimensionless position of 25%. This shows that the pre-rotation cooling hole 8 can effectively and significantly improve the cooling effect of the guide vane upper end wall leading edge plate 5 on the basis of the original cooling gas structure. It is worth mentioning that, unlike the pre-rotation leakage flow of the moving blade, the pre-rotation cooling hole 8 is different. The cooling gas is finally injected into the guide vane passage with the axial and circumferential velocity directions under the action of the first L-shaped plate extending out of the flame tube outer wall 9, and forms a gas film at the guide vane upper end wall leading edge plate 5 to protect the guide vane upper end wall leading edge plate 5.

[0048] The present application starts from the real engine structure, and is based on the integration of combustion chamber and turbine cooling design. The cooling effect of the flame tube rear end cooling hole on the guide vane upper end wall leading edge plate 5 and the guide vane lower end wall leading edge plate 4 is considered. The flame tube cooling hole is designed and modified, so that the cooling performance of the cooling gas of the combustion chamber flame tube can be greatly improved. The modified cooling hole has an inclination angle in the circumferential direction. A combustion chamber flame tube wall pre-rotation cooling hole structure applied to combustion chamber-turbine cooling is designed. A flow guiding method is proposed. The improvement effect of the new structure is verified by using a commercial software CFX. The cooling effect of the pre-rotation cooling structure on the guide vane upper end wall 3 and the guide vane upper end wall leading edge plate 5 is quantitatively analyzed. The results show that the structure can further improve the thermal protection capability of the hot part on the basis of the existing real cooling scheme design, thereby improving the service life of the engine high-temperature part.

[0049] In the description of the present application, it should be understood that the terms "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0050] The above-described embodiments are only used to describe the preferred modes of the present application, and do not limit the scope of the present application. Without departing from the design spirit of the present application, various modifications and improvements to the technical solutions of the present application made by those skilled in the art shall fall within the protection scope determined by the claims of the present application.

Claims

1. A combustion chamber flame tube wall structure for combustion chamber-turbine cooling, characterized by The application relates to a guide vane lower end wall (1), a top surface of the guide vane lower end wall (1) is fixedly connected with the bottom end of a guide vane blade body (2), the top end of the guide vane blade body (2) is fixedly connected with a guide vane upper end wall (3), one end of the guide vane upper end wall (3) close to an air flow inlet is fixedly connected with a guide vane upper end wall front edge plate (5), the guide vane upper end wall front edge plate (5) is located on the side of the guide vane upper end wall (3) far away from the guide vane blade body (2), the guide vane upper end wall front edge plate (5) is installed with a flame tube outer wall surface (9) through a guide vane sealing sheet (7), and an aperture structure is arranged on the guide vane sealing sheet (7). One end of the guide vane lower end wall (1) close to the air flow inlet is fixedly connected with a guide vane lower end wall front edge plate (4), the guide vane lower end wall front edge plate (4) is located on the side of the guide vane lower end wall (1) far away from the guide vane blade body (2), and the side of the guide vane lower end wall front edge plate (4) far away from the guide vane lower end wall (1) is gap-connected with a flame tube inner wall surface (6). A plurality of pre-rotation cooling holes (8) are arranged on the flame tube outer wall surface (9), the plurality of pre-rotation cooling holes (8) are located at the downstream of the flame tube outer wall surface (9), and the plurality of pre-rotation cooling holes (8) are arranged at equal intervals along the direction perpendicular to the air flow. The downstream side of the flame tube outer wall surface (9) away from the flame tube inner wall surface (6) is fixedly connected with the short side of a first L-shaped plate, the first L-shaped plate is located at the end of the flame tube outer wall surface (9), the long side of the first L-shaped plate extends out of the flame tube outer wall surface (9) and is fixedly connected with the bottom end of the long side of a second L-shaped plate arranged vertically, the short side of the second L-shaped plate is fixedly connected with the guide vane sealing sheet (7), the long side of the first L-shaped plate has a thickness q, the thickness of the flame tube outer wall surface (9) is k, there is an included angle alpha between the long side of the first L-shaped plate and the top surface of the flame tube outer wall surface (9), the downstream end of the flame tube outer wall surface (9) extends out of the short side of the first L-shaped plate by a length l, a first gap is left between the top surface of the flame tube outer wall surface (9) and the long side of the first L-shaped plate, the width of the first gap is m, the plurality of pre-rotation cooling holes (8) are arranged on the long side of the first L-shaped plate and communicate with the first gap, the distance between the axis of the pre-rotation cooling hole (8) and the bending position of the first L-shaped plate is x, the distance between the long side of the second L-shaped plate and the guide vane upper end wall (3) is p, the diameter of the pre-rotation cooling hole (8) is D, the pre-rotation cooling hole (8) is arranged in an inclined manner along the circumference of the first L-shaped plate, and an inclination angle beta is arranged between the pre-rotation cooling hole (8) and the radius of the first L-shaped plate. The distance x between the axis of the pre-rotation cooling hole (8) and the bending position of the first L-shaped plate is 3mm-5mm. The diameter D of the pre-rotation cooling hole (8) is 0.5mm-1mm. The inclination angle beta between the pre-rotation cooling hole (8) and the radius of the first L-shaped plate is 30 DEG -60 DEG. The thickness k of the flame tube outer wall surface (9) is 1mm-2mm.

2. The combustor flame tube wall structure for combustion chamber-turbine cooling of claim 1, wherein: ​ 3. The combustor flame tube wall structure for combustion chamber-turbine cooling of claim 1, wherein: The included angle α between the long side of the first L-shaped plate and the top surface of the flame tube outer wall surface (9) is 70°-90°.

4. The combustor flame tube wall structure for combustion chamber-turbine cooling of claim 1, wherein: The first L-shaped plate long side length l of the downstream end of the flame tube outer wall surface (9) extending out of the short side is 3mm-5mm.

5. The combustor flame tube wall structure for combustion chamber-turbine cooling of claim 1, wherein: The first L-shaped plate long side thickness q is 1mm-2mm.

6. The combustor flame tube wall structure for combustion chamber-turbine cooling of claim 1, wherein: The first gap width m is 2mm-3.5mm.

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