Flame tube wall cooling structure, flame tube and combustion chamber

Abstract

The invention discloses a flame tube wall cooling structure, a flame tube and a combustion chamber, and relates to the technical field of aero-engines and gas turbines.The flame tube wall cooling structure comprises a plurality of diffusion hole sets, the diffusion hole sets are used for being sequentially arranged on the flame tube wall in the incoming flow direction, and each diffusion hole set is provided with a plurality of diffusion holes; the diffusion holes are sequentially distributed in the circumferential direction of the flame tube wall and penetrate through the flame tube wall in the thickness direction; the multiple annular protruding structures are coaxially arranged on the flame tube wall and used for protruding towards one side of the combustion cavity, the annular protruding structures are correspondingly arranged behind the diffusion hole sets in the incoming flow direction, a cooling gas film is formed between the flame tube wall face and high-temperature fuel gas, direct impact of the high-temperature fuel gas on the flame tube wall face can be isolated, and therefore the flame tube wall face can be cooled, and the service life of the flame tube is prolonged. Heat insulation protection on the wall face of the flame tube is achieved, and combustion chamber performance is optimized.

Description

Technical Field

[0001] This invention relates to the field of aero-engine and gas turbine technology, and in particular to a flame tube wall cooling structure, as well as a flame tube and combustion chamber. Background Technology

[0002] As the core hot-end component of aero-engines and gas turbines, the combustion chamber is an important place where combustion chemical reactions take place in gas turbines. The high-temperature and high-pressure gas generated here drives the turbine to rotate and do work, which is ultimately converted into engine thrust. It directly determines the engine's thrust output, combustion efficiency and operational reliability. It is a key hub connecting the compressor and the turbine and plays a decisive role in the overall performance of aero-engines and gas turbines.

[0003] The combustion chamber's flame tube walls are subjected to constant high-temperature combustion gas impacts in an extremely harsh environment. Furthermore, they must withstand multiple loads, including airflow impacts and thermal cycling fatigue. If the wall temperature exceeds the material's tolerance limit, it can lead to thermal fatigue, deformation, or even ablation failure, directly shortening the flame tube's lifespan, causing combustion chamber malfunctions, and ultimately affecting the engine's safe and stable operation. Therefore, the flame tube places extremely high demands on cooling technology. It not only needs to achieve efficient heat insulation and cooling but also ensure continuous and stable cooling, while controlling cooling airflow consumption and flow resistance to avoid impacting combustion efficiency. Cooling technology has become one of the core technologies in the fields of aero-engines and gas turbines.

[0004] To achieve effective cooling and thermal insulation of the flame tube wall, various cooling methods have been developed, including film cooling, convection cooling, impingement cooling, and various composite cooling methods. Among them, film cooling is one of the most widely used technologies. Its core principle is to spray cooling air onto the flame tube wall through cooling holes, forming a low-temperature gas film between the wall and the high-temperature combustion gas. The gas film's insulating effect prevents heat transfer from the high-temperature combustion gas to the wall. However, existing film cooling structures still require the fabrication of perforated guide plates, inevitably leading to complex processing methods, high costs, and low yield rates. Summary of the Invention

[0005] The purpose of this invention is to provide a flame tube wall cooling structure, a flame tube, and a combustion chamber to solve the problems existing in the prior art. A cooling gas film is formed between the flame tube wall and the high-temperature gas, which can isolate the direct impact of the high-temperature gas on the flame tube wall, achieve heat insulation protection for the flame tube wall, and optimize the performance of the combustion chamber.

[0006] To achieve the above objectives, the present invention provides the following solution: The present invention provides a flame tube wall cooling structure, comprising: A plurality of diffuser hole groups are provided, each of which is arranged sequentially on the flame tube wall along the incoming flow direction. Each of the diffuser hole groups is provided with a plurality of diffuser holes, each of which is arranged sequentially along the circumference of the flame tube wall and is used to penetrate the flame tube wall along the thickness direction. Multiple annular protrusion structures are provided, all coaxially arranged on the flame tube wall, and all protrude towards the combustion chamber side. Each annular protrusion structure is respectively arranged behind each diffuser hole group along the incoming flow direction.

[0007] Optionally, the diffuser hole has a rectangular structure, with its long side extending circumferentially along the flame tube wall and its wide side parallel to the axial direction of the flame tube wall.

[0008] Optionally, the aspect ratio of the diffusion hole is greater than 2.

[0009] Optionally, the surface of the annular protrusion structure is an arc-shaped surface structure.

[0010] Optionally, the annular protrusion structure has its edge near the diffuser hole tangent to the edge of the diffuser hole.

[0011] Optionally, the diffuser hole has a rectangular structure, with its long side extending circumferentially along the flame tube wall and its wide side parallel to the axial direction of the flame tube wall. The radial cross-section of the annular protrusion is semi-circular, and the ratio of its radius of curvature to the width of the diffusion hole is between 0.5 and 1.

[0012] A flame tube is also provided, comprising an inner cylinder, an outer cylinder, a front end plate, and a flame tube wall cooling structure as described above. The inner cylinder and the outer cylinder are coaxially nested and spaced apart, and both the inner cylinder and the outer cylinder are provided with the flame tube wall cooling structure. The annular protrusion structure on the inner cylinder is disposed on the outer circumferential side of the inner cylinder wall, and the annular protrusion structure on the outer cylinder is disposed on the inner circumferential side of the outer cylinder wall. The front end plate is disposed between the inner cylinder and the outer cylinder and is located at the same end of the inner cylinder and the outer cylinder. The outer circumferential edge of the front end plate is connected to the outer cylinder, and its inner circumferential edge is connected to the inner cylinder.

[0013] Optionally, the front end plate is provided with first jet holes evenly distributed around the perimeter.

[0014] Optionally, the outer cylinder is provided with at least one set of first main combustion holes, at least one set of first combustion holes, and at least one set of first mixing holes in sequence along the axial direction; the inner cylinder is provided with at least one set of second jet holes, at least one set of second main combustion holes, at least one set of second combustion holes, and at least one set of second mixing holes in sequence along the axial direction. A combustion chamber is also provided, comprising an outer casing, an inner casing, an evaporator pipe, a fuel supply pipe, a fuel nozzle, a support plate, an outlet mounting ring, a mounting plate, and a flame tube as described above; The outer cylinder of the flame tube is installed inside the outer casing, and one end of it is connected to the mounting plate; an evaporator tube is fixed on one side of the mounting plate, the evaporator tube is located in the outer cylinder, and an oil supply pipe and a fuel nozzle are arranged on the other side. The fuel nozzle is located outside the outer cylinder and is connected to the oil supply pipe. The oil supply pipe passes through the mounting plate and extends into the evaporator tube; a front end plate is connected to the other end of the outer cylinder. The inner cylinder of the flame tube is connected at one end to the front end plate and at the other end to a support plate. The inner casing is located inside the inner cylinder, with one end connected to the support plate and the other end extending from the side of the inner cylinder connected to the front end plate; One end of the outlet mounting ring is connected to the mounting plate, and the other end is connected to the outer casing, and is used to install the turbine guide.

[0015] The present invention achieves the following technical effects compared to the prior art: The flame tube wall cooling structure disclosed in this invention allows the compressor outlet airflow to enter the combustion chamber after passing through the diffuser, and then enter the flame tube through the diffuser hole. After entering the diffuser hole, the airflow adheres to the surface of the annular protrusion structure due to the Coanda effect and flows backward along the flame tube wall, forming a cooling gas film between the flame tube wall and the high-temperature combustion gas. This film can isolate the direct impact of the high-temperature combustion gas on the flame tube wall, achieving heat insulation protection for the flame tube wall and optimizing the combustion chamber performance. Compared with the gas film cooling structure in the prior art, it avoids the need to process fish scale hole guide plates, making the processing method simpler, reducing processing costs and improving the processing yield. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the combustion chamber structure in one example disclosed in this invention; Figure 2 for Figure 1 A three-dimensional sectional view of the central flame tube; Figure 3 for Figure 2 A cross-sectional schematic diagram of the cooling structure of the flame tube wall on the outer tube of the middle flame tube; Figure 4 for Figure 3 Schematic diagram of gas flow on the surface of the cooling structure of the middle flame tube wall; Figure 5 for Figure 2 A three-dimensional schematic diagram of the outer cylinder of the central flame tube; Figure 6 for Figure 2 A three-dimensional schematic diagram of the inner cylinder of the central flame tube; Among them, 1-outer casing, 2-inner casing, 3-flame tube, 4-evaporator tube, 5-oil supply pipe, 6-support plate, 7-outlet mounting ring, 8-mounting plate, 31-front end plate, 32-outer cylinder, 33-inner cylinder, 311-first jet hole, 321-first main combustion hole, 322-first primary combustion hole, 323-first mixing hole, 324-flame tube wall cooling structure, 331-second jet hole, 332-second main combustion hole, 333-secondary combustion hole, 334-second mixing hole, 91-diffusion hole, 92-annular protrusion structure. Detailed Implementation

[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] The purpose of this invention is to provide a flame tube wall cooling structure, a flame tube, and a combustion chamber to solve the problems existing in the prior art. A cooling gas film is formed between the flame tube wall and the high-temperature gas, which can isolate the direct impact of the high-temperature gas on the flame tube wall, achieve heat insulation protection for the flame tube wall, and optimize the performance of the combustion chamber.

[0020] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0021] like Figures 1 to 6 As shown, the present invention provides a flame tube wall cooling structure, including a diffuser hole group and an annular protrusion structure 92. The diffuser hole group is provided with multiple diffuser holes, each diffuser hole group is arranged sequentially on the flame tube wall along the incoming flow direction, and each diffuser hole group is provided with multiple diffuser holes 91, each diffuser hole 91 is arranged sequentially along the circumference of the flame tube wall, and the diffuser holes 91 are used to penetrate the flame tube wall along the thickness direction. The annular protrusion structure 92 is provided with multiple diffuser holes, all of which are coaxially arranged on the flame tube wall and are all used to protrude towards the combustion chamber side. Each annular protrusion structure 92 is respectively arranged behind each diffuser hole group along the incoming flow direction.

[0022] The flame tube wall cooling structure 324 disclosed in this invention allows the compressor outlet airflow to enter the combustion chamber after passing through the diffuser, and then enter the flame tube 3 through the diffuser hole 91. After entering the diffuser hole 91, the airflow adheres to the surface of the annular protrusion structure 92 due to the Coanda effect and flows backward along the flame tube wall, forming a cooling gas film between the flame tube wall and the high-temperature gas. This film can isolate the direct impact of the high-temperature gas on the flame tube wall, achieving heat insulation protection for the flame tube wall and optimizing the combustion chamber performance.

[0023] Based on the above embodiments, the processing method of the diffuser hole 91 is, but not limited to, punching or laser drilling, and the processing method of the annular protrusion structure 92 is, but not limited to, welding. The processing method is simple, which meets the strength requirements and reduces the processing cost. Alternatively, the diffuser hole 91, the annular protrusion structure 92 and the flame tube wall can be integrally formed by additive manufacturing, which can avoid the deformation of punching and welding, and ensure the feasibility and quality of processing. Regardless of the processing method, compared with the gas film cooling structure in the prior art, it avoids the processing of fish scale hole guide plates, the processing method is simpler, which reduces the processing cost and improves the processing yield.

[0024] The cooling structure and cooling method disclosed in this invention focus on optimizing the cooling structure design to improve the stability and coverage of the air film adhesion, reduce the cooling air consumption, take into account low flow resistance and lightweight, adapt to the design requirements of compact and thin-walled combustion chambers, and simplify the processing technology and improve the structural reliability to meet the development needs of high thrust-to-weight ratio and long-life engines.

[0025] In one embodiment, the diffuser hole 91 is a rectangular structure, with its long side extending circumferentially along the flame tube wall and its wide side parallel to the axial direction of the flame tube wall. The length-to-width ratio of the diffuser hole 91 is greater than 2. In this embodiment, the rectangular diffuser hole 91 preferably has a cross-sectional length of 6-8 mm and a width of 1-2 mm. The radius of curvature of the semi-circular convex structure 92 is preferably 0.5-2 mm, and the surface of the semi-circular convex structure 92 is continuously smooth without abrupt sharp edges.

[0026] In one embodiment, the surface of the annular protrusion 92 is an arc-shaped surface structure. Specifically, the edge of the annular protrusion 92 closest to the diffuser hole 91 is tangent to the edge of the diffuser hole 91, ensuring a smooth and continuous transition section.

[0027] In one embodiment, the diffuser hole 91 has a rectangular structure, with its long side extending circumferentially along the flame tube wall and its wide side parallel to the axial direction of the flame tube wall; the radial cross-section of the annular protrusion structure 92 is semi-circular, and the ratio of its radius of curvature to the wide side of the diffuser hole 91 is between 0.5 and 1.

[0028] Furthermore, a flame tube 3 is also provided, including an inner tube 33, an outer tube 32, a front end plate 31, and a flame tube wall cooling structure 324 as described above. The inner tube 33 and the outer tube 32 are coaxially nested and spaced apart, and both the inner tube 33 and the outer tube 32 are provided with flame tube wall cooling structures 324. An annular protrusion structure 92 on the inner tube 33 is disposed on the outer circumferential side of the inner tube wall, and an annular protrusion structure 92 on the outer tube 32 is disposed on the inner circumferential side of the outer tube wall. The inner tube 33 and the outer tube 32 are processed by sheet metal processing and welding, or integrally formed with the diffuser hole 91 and the annular protrusion structure 92 by additive manufacturing, ensuring processing feasibility and processing quality. The front end plate 31 is disposed between the inner tube 33 and the outer tube 32, and is located at the same end of the inner tube 33 and the outer tube 32. The outer circumferential edge of the front end plate 31 is connected to the outer tube 32, and its inner circumferential edge is connected to the inner tube 33.

[0029] Based on the above implementation method, the inner cylinder 33 and the outer cylinder 32 are cylindrical in shape and are arranged concentrically. The front end plate 31 is annular, with its outer circumference connected to the outer cylinder 32 and its inner circumference connected to the inner cylinder 33.

[0030] In one embodiment, the front end plate 31 is provided with first jet holes 311 evenly distributed in the circumferential direction.

[0031] In one embodiment, the outer cylinder 32 is provided with at least one set of first main combustion holes 321, at least one set of first primary combustion holes 322, and at least one set of first mixing holes 323 in sequence along the axial direction; the inner cylinder 33 is provided with at least one set of second jet holes 331, at least one set of second main combustion holes 332, at least one set of second secondary combustion holes 333, and at least one set of second mixing holes 334 in sequence along the axial direction. The first jet holes 311 and second jet holes 331 mainly provide primary air for oil-gas mixing, combustion organization, and flow field control; the first main combustion holes 321 and second main combustion holes 332 mainly provide secondary air for combustion organization and flame stabilization; the first primary combustion holes 322 and second secondary combustion holes 333 mainly provide secondary air for end-point air supply and temperature control; the first mixing holes 323 and second mixing holes 334 mainly provide mixed air for temperature control; and the flame tube wall cooling structure 324 provided on the outer cylinder 32 and inner cylinder 33 mainly provides cooling air for cooling the wall surface.

[0032] Based on the above embodiments, in each group of the first main combustion hole 321, the first combustion hole 322, and the first mixing hole 323, the number of holes in each group is not less than 2, and they are evenly distributed along the circumferential surface of the outer cylinder 32. In each group of the second main combustion hole 332, the second combustion hole 333, and the second mixing hole 334, the number of holes in each group is not less than 2, and they are evenly distributed along the circumferential surface of the inner cylinder 33. Among them, the number of each group of the first main combustion hole 321, the first combustion hole 322, the first mixing hole 323, the second jet hole 331, the second main combustion hole 332, the second combustion hole 333, and the second mixing hole 334 is positively correlated with the number of evaporation tubes 4, and the preferred number is 8-16.

[0033] In some specific examples, taking the matching diffuser hole group and annular protrusion structure 92 as a cooling structure, the outer cylinder 32 is provided with multiple sets of such cooling structures, and the first main combustion hole 321, the first combustion hole 322, and the first mixing are sequentially and alternately distributed with each cooling structure along the axial direction of the outer cylinder 32. The inner cylinder 33 is provided with multiple sets of such cooling structures, and the second main combustion hole 332, the second combustion hole 333, and the second mixing are sequentially and alternately distributed with each cooling structure along the axial direction of the outer cylinder 32, so as to form a more effective cooling gas film.

[0034] Based on the above embodiments, the number of the first main combustion hole 321, the first combustion hole 322, and the first mixing hole 323 distributed on the outer cylinder 32 is preferably 1-2 groups, the number of holes in each group is preferably 8-16, and the hole diameters are preferably Φ11mm, Φ13mm, and Φ15mm respectively. The number of cooling structures on the outer cylinder 32 is preferably 4-8 groups, which are distributed on both sides of the combustion hole and the mixing hole respectively. Each group of cooling structures on the outer cylinder 32 includes multiple diffusion holes 91 and an annular protrusion structure 92, wherein the number of diffusion holes 91 is preferably 32-48, and they are evenly distributed along the circumferential direction of the outer cylinder 32 wall.

[0035] Based on the above embodiments, the number of second jet holes 331 distributed on the inner cylinder 33 is preferably 1-3 groups, the number of second main combustion holes 332, second secondary combustion holes 333, and second mixing holes 334 is preferably 1-2 groups, the number of holes in each group is preferably 8-16, and the hole diameters are Φ11mm, Φ13mm, and Φ15mm respectively. The number of cooling structures on the inner cylinder 33 is preferably 3-7 groups, which are distributed on both sides of the combustion holes and mixing holes. Each group of cooling structures on the inner cylinder 33 includes multiple diffusion holes 91 and an annular protrusion structure 92, wherein the number of diffusion holes 91 is preferably 24-32, and they are evenly distributed along the circumferential direction of the inner cylinder 33 wall.

[0036] Furthermore, a combustion chamber is also provided, including an outer casing 1, an inner casing 2, an evaporator pipe 4, a fuel supply pipe 5, a fuel nozzle, a support plate 6, an outlet mounting ring 7, a mounting plate 8, and a flame tube 3 as described above; the outer tube 32 of the flame tube 3 is installed inside the outer casing 1, and one end of it is connected to the mounting plate 8; the evaporator pipe 4 is fixed on one side of the mounting plate 8, the evaporator pipe 4 is located in the outer tube 32, and the fuel supply pipe 5 and the fuel nozzle are arranged on the other side, the fuel nozzle is located outside the outer tube 32 and is connected to the fuel supply pipe 5, the fuel supply pipe 5 passes through the mounting plate 8 and extends into the evaporator pipe 4; it can be understood that the mounting plate 8 The fuel line 5 and fuel nozzle are used for positioning, fixing, and sealing the evaporator tube 4. The fuel line 5 and fuel nozzle are responsible for stably delivering fuel to the combustion chamber, with the fuel nozzle and evaporator tube 4 installed in a one-to-one correspondence. The other end of the outer cylinder 32 is connected to the front end plate 31. One end of the inner cylinder 33 of the flame tube 3 is connected to the front end plate 31, and the other end is connected to the support plate 6. The inner casing 2 is located inside the inner cylinder 33, with one end connected to the support plate 6 and the other end extending from the side of the inner cylinder 33 connected to the front end plate 31. One end of the outlet mounting ring 7 is connected to the mounting plate 8, and the other end is connected to the outer casing 1, and is used to install the turbine guide. It can be further understood that the area enclosed by the outer casing 1, the flame tube 3, and the inner casing 2 is the secondary flow channel, and the area enclosed by the outer cylinder 32 and the inner cylinder 33 is the combustion chamber.

[0037] In some specific examples, the number of evaporator tubes 4 is preferably 8-16. It should be noted that the number of first jet holes 311 is positively correlated with the number of evaporator tubes 4, with a preferred number of 8-16, and the distribution of the first jet holes 311 corresponds one-to-one with the position of the evaporator tubes 4.

[0038] As described above, this invention is based on the Coanda effect. By arranging a flame tube wall cooling structure 324 on the flame tube wall, air in the secondary flow channel enters the flame tube 3 through the diffuser hole 91. Most of the gas can adhere to the surface of the annular protrusion structure 92 and flow backward along the flame tube wall to form a cooling gas film. This isolates the high-temperature combustion gas from the direct impact on the wall, achieving heat insulation protection of the flame tube wall, suppressing thermal failure, and improving the performance of the flame tube 3. Compared with the gas film cooling structure in the prior art, it avoids the need to process fish scale hole guide plates, making the processing method simpler, reducing processing costs, and improving the processing yield.

[0039] Any adaptive changes made according to actual needs are within the scope of protection of this invention.

[0040] It should be noted that, for those skilled in the art, it is obvious that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0041] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A flame tube wall cooling structure, characterized in that, include: A plurality of diffuser hole groups are provided, each of which is arranged sequentially on the flame tube wall along the incoming flow direction. Each of the diffuser hole groups is provided with a plurality of diffuser holes, each of which is arranged sequentially along the circumference of the flame tube wall and is used to penetrate the flame tube wall along the thickness direction. Multiple annular protrusion structures are provided, all coaxially arranged on the flame tube wall, and all protrude towards the combustion chamber side. Each annular protrusion structure is respectively arranged behind each diffuser hole group along the incoming flow direction.

2. The flame tube wall cooling structure according to claim 1, characterized in that, The diffuser hole has a rectangular structure, with its long side extending circumferentially along the flame tube wall and its wide side parallel to the axial direction of the flame tube wall.

3. The flame tube wall cooling structure according to claim 2, characterized in that, The aspect ratio of the diffusion hole is greater than 2.

4. The flame tube wall cooling structure according to claim 1, characterized in that, The surface of the annular protrusion structure is an arc-shaped surface structure.

5. The flame tube wall cooling structure according to claim 4, characterized in that, The annular protrusion structure has its edge near the diffuser hole tangent to the edge of the diffuser hole.

6. The flame tube wall cooling structure according to claim 4, characterized in that, The diffuser hole has a rectangular structure, with its long side extending circumferentially along the flame tube wall and its wide side parallel to the axial direction of the flame tube wall. The radial cross-section of the annular protrusion is semi-circular, and the ratio of its radius of curvature to the width of the diffusion hole is between 0.5 and 1.

7. A flame tube, characterized in that, The device includes an inner cylinder, an outer cylinder, a front end plate, and a flame tube wall cooling structure as described in any one of claims 1 to 6. The inner cylinder and the outer cylinder are coaxially nested and spaced apart, and both the inner cylinder and the outer cylinder are provided with the flame tube wall cooling structure. The annular protrusion structure on the inner cylinder is disposed on the outer circumferential side of the inner cylinder wall, and the annular protrusion structure on the outer cylinder is disposed on the inner circumferential side of the outer cylinder wall. The front end plate is disposed between the inner cylinder and the outer cylinder and is located at the same end of the inner cylinder and the outer cylinder. The outer circumferential edge of the front end plate is connected to the outer cylinder, and its inner circumferential edge is connected to the inner cylinder.

8. The flame tube according to claim 7, characterized in that, The front end plate is uniformly provided with first jet holes in the circumferential direction.

9. The flame tube according to claim 8, characterized in that, The outer cylinder is provided with at least one set of first main combustion holes, at least one set of first combustion holes and at least one set of first mixing holes in sequence along the axial direction; the inner cylinder is provided with at least one set of second jet holes, at least one set of second main combustion holes, at least one set of second combustion holes and at least one set of second mixing holes in sequence along the axial direction.

10. A combustion chamber, characterized in that, It includes an outer casing, an inner casing, an evaporator pipe, an oil delivery pipe, a fuel nozzle, a support plate, an outlet mounting ring, a mounting plate, and a flame tube as described in claim 9; The outer cylinder of the flame tube is installed inside the outer casing, and one end of it is connected to the mounting plate; an evaporator tube is fixed on one side of the mounting plate, the evaporator tube is located in the outer cylinder, and an oil supply pipe and a fuel nozzle are arranged on the other side. The fuel nozzle is located outside the outer cylinder and is connected to the oil supply pipe. The oil supply pipe passes through the mounting plate and extends into the evaporator tube; a front end plate is connected to the other end of the outer cylinder. The inner cylinder of the flame tube is connected at one end to the front end plate and at the other end to a support plate. The inner casing is located inside the inner cylinder, with one end connected to the support plate and the other end extending from the side of the inner cylinder connected to the front end plate; One end of the outlet mounting ring is connected to the mounting plate, and the other end is connected to the outer casing, and is used to install the turbine guide.

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