A slot structure and cooling device applied to guide vane leakage flow

Abstract

The application relates to the field of gas turbine turbine blade cooling technology and discloses a slot structure applied to guide vane leakage flow and a cooling device, which comprises a first slot surface and a second slot surface, a cooling channel is formed between the first slot surface and the second slot surface, and the cooling channel is used for guiding cooling gas; wherein a plurality of grooves are arranged on the first slot surface in a direction perpendicular to the flow direction of the cooling gas, a convex position is formed between two adjacent grooves, the convex position comprises two side edges, the two side edges extend in a direction away from the first slot surface and meet to form an end point position, a plurality of end point positions are located on the same plane and are parallel to the second slot surface, and the grooves and the convex position are symmetric with respect to the center line of the side edge. The application can make the cooling gas better cover the surface of a turbine guide vane edge plate and an end wall, has better circumferential covering capacity, has better cooling effect, and can reduce the cooling gas consumption on the basis of achieving the same cooling efficiency.

Description

Technical Field

[0001] This invention relates to the field of gas turbine blade cooling technology, and in particular to a slot structure and cooling device for guide vane leakage flow. Background Technology

[0002] Aero engines, often considered the crown jewel of modern industry, represent a nation's pinnacle of industrial design and manufacturing capabilities. As one of the most crucial parameters of an aero engine, turbine inlet temperature significantly impacts its overall performance. Increasing turbine inlet temperature not only boosts engine thrust but also improves cycle efficiency through adjustments to the pressure ratio. Raising turbine inlet temperature has become a constant design goal for engineers. Currently, advanced aero engine turbine inlet temperatures exceed 2000K, surpassing the temperature resistance limits of turbine materials. Therefore, appropriate cooling technologies are essential. For turbine blades, current primary cooling solutions combine internal convection and impingement cooling with external film cooling to provide thermal protection. For the endwall, the first step is to utilize film cooling on the flame tube to cool the wall surface. By designing the temperature profile at the combustion chamber outlet to be low on both sides and high in the middle, the cooling difficulty of the guide vane tip, root, and endwall is reduced, thus decreasing the amount of cooling air required. Secondly, film cooling holes are designed on the endwall to achieve the desired cooling effect. The coverage of cooling air reduces heat flux, thereby reducing temperature load. Slot cooling was not originally an active cooling method. Engineers discovered that the flame tube and guide vane mounting area could not be completely sealed, resulting in leakage at the overlap area. Therefore, engineers proactively designed this area as a non-overlapping structure, allowing cooling air from the high-pressure compressor to actively flow out through the slot. The low-temperature cooling air adheres to the wall surface after exiting, providing good cooling for the guide vane's leading edge plate and endwall. Slot cooling has gradually become a mainstream guide vane cooling design method. Landfester C (Landfester C, Müller G, Böhle M, et al. Aerodynamic effects of turbine vane end wall film cooling for different purge slot configurations in a linear cascade[C] / / International Gas Turbine Conference (IGTC), Paper No. IGTC-201-60. 2019) et al. studied the structural parameters of guide vane slot cooling and analyzed the end wall cooling under different slot inclination angles and different slot width combinations.Thrift AA (ThriftAA, Thole KA, Hada S. Effects of orientation and position of the combustor-turbine interface on the cooling of a vane endwall[J]. 2012) explored the influence of the coupling surface position on the cooling of the guide vane slots. Current research both domestically and internationally focuses on optimizing single structural parameters of the slots, combining multiple structural parameters, and the influence of slot arrangement on slot cooling. It also incorporates real-world conditions such as mainstream turbulence and non-uniform airflow to ensure the research is more closely aligned with practical realities.

[0003] However, while the adiabatic cooling efficiency of the cooling slots for the first-stage guide vanes can be improved through single-parameter and multi-parameter optimization of structural parameters, continuous parameter adjustments are impractical in real-world applications due to factors such as manufacturing and assembly, as well as the actual application process. Structural parameters cannot be extensively modified solely for end-wall considerations; integrated matching design is necessary. Currently, there is a lack of research on structural improvements from the structural level itself. Modifications to the structure itself can significantly impact slot performance, and this area of ​​research is somewhat lacking. Such design is crucial for improving the cooling performance of turbine end-walls, achieving better coverage under the same cooling gas conditions. Modified end-wall slot design is therefore essential for end-wall cooling.

[0004] In summary, designing a novel slot structure for turbine guide vane inlet that significantly improves gas coverage on the endwall, enhances wall cooling performance near the endwall, and ensures a simple and easy-to-manufacture novel cooling structure is a problem that urgently needs to be solved in this field. Summary of the Invention

[0005] The purpose of this invention is to provide a slot structure for guide vane leakage flow to solve the problems existing in the prior art.

[0006] To achieve the above objectives, the present invention provides the following solution: The present invention provides a slot structure applied to guide vane leakage flow, comprising: A first groove surface and a second groove surface, with a cooling channel formed between the first groove surface and the second groove surface, the cooling channel being used to conduct cooling gas; The first groove surface has a plurality of grooves continuously distributed along the direction perpendicular to the flow of the cooling gas. A protrusion is formed between two adjacent grooves. The protrusion includes two side edges. The two side edges extend away from the first groove surface and intersect to form an end point. The plurality of end points are located on the same plane and are parallel to each other with respect to the second groove surface. The grooves and the protrusions are symmetrical with respect to the center line of the side edges.

[0007] Preferably, the two sides are transitioned by rounded chamfers to form the endpoints.

[0008] Preferably, the endpoint is the tip formed by the intersection of the two sides.

[0009] Preferably, the length of the groove along the axial direction is 20mm-50mm.

[0010] Preferably, the distance between two adjacent end points on a plane parallel to the second groove surface is 20mm-26mm.

[0011] Preferably, the depth of the groove is 2mm-4mm.

[0012] Preferably, the angle of the tip formed by the intersection of the two sides is 120°-160°.

[0013] A cooling device, comprising: The turbine stator inner casing and the turbine stator outer casing, wherein a turbine leading edge plate is fixedly connected to one side of the turbine stator inner casing; Turbine blades are disposed between the inner casing of the turbine stator and the outer casing of the turbine stator; A straight groove is formed between the outer casing of the turbine stator and the outer wall of the flame tube. A slotted structure for guide vane leakage flow is formed between the turbine leading edge plate and the inner wall of the flame tube; The inner and outer walls of the flame tube form a gas flow channel. The inner and outer casings of the turbine stator and the turbine blades form a turbine flow channel. The gas flows through the turbine flow channel to generate thrust for the engine. The straight slot and the slot structure together form a cooling channel. The cooling gas rushes out from the slot structure and protects the leading edge endwall of the turbine blade.

[0014] Preferably, the slot structure is located at a position of 0.13-0.15 axial chord length on one side of the turbine blade.

[0015] Preferably, the angle between the slot structure and the inner wall of the flame tube is 30°-90°.

[0016] This invention discloses the following technical effects: It enables cooling gas to better cover the surfaces of the turbine guide vane edge plate and end wall, providing better circumferential coverage and improved cooling effect. While achieving the same cooling efficiency, it reduces the amount of cooling gas required and complements the design of end wall film cooling. The invention's configuration design for the first-stage guide vane edge plate is simple in structure and easy to manufacture, and can be applied to the machining of turbine guide vanes for aero-engines, thereby improving cooling performance. Attached Figure Description

[0017] 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.

[0018] Figure 1 This is an axial view of Embodiment 1 of the present invention.

[0019] Figure 2 This is the right view in Embodiment 1 of the present invention.

[0020] Figure 3 This is a cross-sectional view of BB in Embodiment 1 of the present invention.

[0021] Figure 4 This is a cross-sectional view of AA in Embodiment 1 of the present invention.

[0022] Figure 5 This is the distribution curve of the spanwise average film cooling efficiency along the axial direction in Embodiment 1 of the present invention.

[0023] Figure 6 This is the distribution curve of the air film cooling efficiency along the y direction at x=-0.01m in Embodiment 1 of the present invention.

[0024] Figure 7 This is an axial view of Embodiment 2 of the present invention.

[0025] Figure 8 This is the right view in Embodiment 2 of the present invention.

[0026] Figure 9 This is a cross-sectional view of BB in Embodiment 2 of the present invention.

[0027] Figure 10 This is a cross-sectional view of AA in Embodiment 2 of the present invention.

[0028] Figure 11 This is the distribution curve of the spanwise average film cooling efficiency along the axial direction in Embodiment 2 of the present invention.

[0029] Figure 12 This is the distribution curve of the air film cooling efficiency along the y direction at x=-0.01m in Embodiment 2 of the present invention.

[0030] Among them, 1. inner casing of turbine stator; 2. turbine blade; 3. turbine leading edge flange; 4. outer casing of turbine stator; 5. outer wall of flame tube; 6. inner wall of flame tube. Detailed Implementation

[0031] 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.

[0032] 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.

[0033] Example 1 Reference Figures 1-6 A slotted structure for guide vane leakage flow, comprising: A first groove surface and a second groove surface are separated by a cooling channel, which is used to conduct cooling gas. The first groove surface has a number of grooves continuously distributed along the direction perpendicular to the flow of the cooling gas. A protrusion is formed between two adjacent grooves. The protrusion includes two sides. The two sides extend away from the first groove surface and intersect to form an end point. The multiple end points are located on the same plane and are parallel to each other with respect to the second groove surface. The grooves and protrusions are symmetrical with respect to the center line of the side.

[0034] The two sides are transitioned by rounded chamfers to form the end points, so that the groove structure in this embodiment forms a corrugated groove.

[0035] Since traditional guide vane slot cooling almost always uses straight slots, this embodiment designs a corrugated slot surface configuration for the turbine leading edge plate 3. After being spliced ​​with the combustion chamber flame tube outlet, it forms a corrugated slot structure, which helps the cooling gas blown out of the slot. The circumferential momentum is less uniform than that of the original straight slot, and is concentrated at the trough of the corrugated slot (i.e., the groove). The cooling gas can better cover the surface of the turbine blade 2 edge plate and end wall, with better circumferential coverage and better cooling effect. While achieving the same cooling efficiency, it can reduce the amount of cooling gas used, and it is also a supplement to the design of end wall film cooling. This embodiment designs the configuration of the first-stage guide vane edge plate, which has the characteristics of simple structure and easy processing, and can be applied to the processing of turbine guide vanes of aero-engines to improve the cooling effect.

[0036] The length of the groove along the axial direction is 20mm-50mm.

[0037] The distance between two adjacent end points on a plane parallel to the second groove surface is 20mm-26mm.

[0038] The depth of the groove is 2mm-4mm.

[0039] To illustrate the structural dimensions, a specific embodiment is used for explanation. In this embodiment, the corrugated slot structure is mainly described by the slot inclination angle α, slot length L, and groove depth. In this embodiment, the specific value of the slot inclination angle α is 45°, the slot length L is 30mm, the groove opening length is 23.2mm, and the groove depth is 3mm. It should be noted that in this embodiment, to compare the differences between the original structure and the corrugated slot structure, except for the slot edges on the three sides of the turbine leading edge plate, the rest of the structure is completely identical, and the flow channel area of ​​the straight slot is the same as that of the corrugated slot. Furthermore, to ensure consistency with the actual working environment during simulation, the mainstream temperature is selected as 810K, the secondary flow cooling gas is 500K, and the blowing ratio is calculated according to the formula... Defined as a blowing ratio of 1.

[0040] Figure 5 These are curves showing the axial distribution of the spanwise average adiabatic film cooling effect under straight and corrugated slots, respectively. Figure 6 The curves show the distribution of the cooling effect of the adiabatic film along the y-axis at the intersection of the cross section and the flow channel at x=-0.01m. The two figures demonstrate the improvement in end-wall cooling brought about by the new corrugated slot in two dimensions.

[0041] Figure 5 and Figure 6 In the diagram, the solid line represents the film cooling efficiency under straight slots, while the dashed line represents the film cooling efficiency under corrugated slots. Figure 5Among them, the corrugated slots, represented by the dashed lines, consistently exhibit a greater spanwise average adiabatic film cooling efficiency in the axial direction than ordinary straight slots, with a strong consistency in gain level along the axial direction. Under the condition of a blowing ratio of 1, the spanwise average film cooling efficiency in the axial direction is enhanced by approximately 0.025, with the overall film cooling level around 0.2. Overall, the corrugated slots improve the average cooling efficiency by approximately 12% to 15%, indicating that the designed corrugated slots can effectively increase the coverage area of ​​the secondary flow cooling air on the wall and leading edge plate, resulting in a superior axial cooling effect. Figure 6 This represents the distribution of film cooling efficiency along the spanwise direction. It can be seen that the film cooling efficiency along the spanwise direction is higher with the new type of cooling slot. This indicates that the corrugated slots provide a wider coverage area of ​​cooling gas along the spanwise direction, meaning that more cooling gas will cover the leading edge of the blade. As shown in the figure, the film cooling efficiency of the corrugated slots is higher than that of the straight slots almost throughout the entire y-direction. (Summary) Figure 5 and Figure 6 It can be seen that under low blowing ratio conditions, the corrugated groove significantly improves the cooling efficiency of the groove near the entire end wall and has a strong covering effect on the upstream of the vortex channel. As it is transported downstream, the cooling air is gradually lifted away from the wall by the secondary flow, and the cooling efficiency gradually decreases. However, compared with the straight groove, it still has a higher cooling efficiency improvement.

[0042] This invention improves the configuration of the cooling groove for slotted cooling by generating a corrugated arc, making the momentum of the leaking flow more concentrated and providing better coverage in the axial and circumferential directions. A corrugated slotted structure for use at the inlet of a turbine guide vane is designed, and a flow guiding method is proposed. The improvement effect of this new slotted structure is verified by numerical simulation technology. The quantitative analysis shows that the corrugated slotted structure has a better effect on improving the end-wall film cooling effect. By changing the momentum characteristics of the outflowing cold gas, the spanwise cooling gas coverage effect is increased, thereby better isolating the high-temperature combustion gas from thermal erosion of the wall surface.

[0043] Example 2 Reference Figures 7-12 A slotted structure for guide vane leakage flow, comprising: A first groove surface and a second groove surface are separated by a cooling channel, which is used to conduct cooling gas. The first groove surface has a number of grooves continuously distributed along the direction perpendicular to the flow of the cooling gas. A protrusion is formed between two adjacent grooves. The protrusion includes two sides. The two sides extend away from the first groove surface and intersect to form an end point. The multiple end points are located on the same plane and are parallel to each other with respect to the second groove surface. The grooves and protrusions are symmetrical with respect to the center line of the side.

[0044] The endpoint is a pointed tip formed by the intersection of the two sides, which makes the slot structure in this embodiment form a triangular slot.

[0045] Traditional guide vane slot cooling almost always uses straight slots. By designing a triangular slot configuration for the turbine leading edge rim 3, and splicing it with the combustion chamber flame tube outlet, a triangular slot structure is formed. This helps to change the angle of attack of the cooling gas as it exits the triangular slot, allowing the cooling gas to better cover the surfaces of the turbine blade rim 2 and endwall, resulting in better circumferential coverage and cooling effect. While achieving the same cooling efficiency, it can reduce the amount of cooling gas used, and it also complements the endwall film cooling design. This embodiment features a simple structure and easy machining of the first-stage guide vane rim, which can be applied to the machining of aero-engine turbine guide vanes to improve cooling performance.

[0046] The length of the groove along the axial direction is 20mm-50mm.

[0047] The distance between two adjacent end points on a plane parallel to the second groove surface is 20mm-26mm.

[0048] The depth of the groove is 2mm-4mm.

[0049] The angle of the apex formed by the intersection of the two sides is 120°-160°, which is the angle of the vertex of the triangle.

[0050] To illustrate the structural dimensions, a specific embodiment is used. In this embodiment, the triangular slot structure is mainly described by the slot angle α, slot length L, and groove depth. In this embodiment, the slot angle α is 45°, the slot length L is 30mm, the groove opening length is 23.2mm, the groove depth is 3mm, and the apex angle is 135°. It should be noted that in this embodiment, to compare the differences between the original structure and the triangular slot structure, except for the slot edges on the three sides of the turbine leading edge plate, the rest of the structure is identical, and the flow channel area of ​​the straight slot is the same as that of the triangular slot. Furthermore, to ensure consistency with the actual working environment during simulation, the mainstream temperature is 810K, the secondary flow cooling gas is 500K, and the blowing ratio is calculated according to the formula... Defined as a blowing ratio of 1.

[0051] Figure 11 These are curves showing the axial distribution of the spanwise average adiabatic film cooling effect under straight and triangular slots, respectively. Figure 12 The curves show the distribution of the cooling effect of the adiabatic film along the y-axis at the intersection of the cross section and the flow channel at x=-0.01m. The two figures demonstrate the improvement in end-wall cooling brought about by the new triangular slot in two dimensions.

[0052] Figure 11 and Figure 12 In the diagram, the solid line represents the film cooling efficiency under a straight slot, and the dashed line represents the film cooling efficiency under a triangular slot. Figure 5 Among them, the triangular slots represented by the dashed lines consistently exhibit a greater spanwise average adiabatic film cooling efficiency in the axial direction than ordinary straight slots, with a strong consistency in gain level along the axial direction. Under the condition of a blowing ratio of 1, the spanwise average film cooling efficiency in the axial direction is enhanced by approximately 0.025, with the overall film cooling level around 0.2. Overall, the triangular slots improve the average cooling efficiency by approximately 12% to 15%, indicating that the designed triangular slots can effectively increase the coverage area of ​​the secondary flow cooling air on the wall and leading edge plate, resulting in superior axial cooling performance. Figure 6 This represents the distribution of film cooling efficiency along the spanwise direction. It can be seen that the film cooling efficiency is higher along the spanwise direction below the cooling slot. This indicates that the triangular slot design broadens the coverage of the cooling gas along the spanwise direction, meaning more cooling gas will cover the leading edge of the blade. As shown in the figure, the film cooling efficiency of the triangular slot is higher than that of the straight slot almost throughout the entire y-direction. (Summary) Figure 11 and Figure 12 It can be seen that under low blowing ratio conditions, the triangular slot significantly improves the cooling efficiency of the slot near the entire end wall and has a strong covering effect on the upstream of the vortex channel. As the cooling air is transported downstream, it is gradually lifted away from the wall by the secondary flow, and the cooling efficiency gradually decreases. However, compared with the straight slot, it still has a higher cooling efficiency improvement.

[0053] This invention improves the configuration of the cooling groove for slotted cooling by generating a triangular arc, making the momentum of the leaking flow more concentrated and providing better coverage in the axial and circumferential directions. A novel triangular slotted structure for use at the inlet of a turbine guide vane is designed, and a flow guiding method is proposed. The improvement effect of the novel slotted structure is verified by numerical simulation technology. The quantitative analysis shows that the triangular slotted structure has a better effect on improving the end-wall film cooling effect. By changing the momentum characteristics of the outflowing cold gas, the spanwise cooling gas coverage effect is increased, thereby better isolating the wall surface from the thermal erosion of high-temperature combustion gas.

[0054] Example 3 A cooling device, comprising: The inner casing 1 and the outer casing 4 of the turbine stator are provided. A turbine leading edge plate 3 is fixedly connected to one side of the inner casing 1. Turbine blades 2 are disposed between the inner casing 1 and the outer casing 4 of the turbine stator; A straight groove is formed between the outer casing 4 of the turbine stator and the outer wall 5 of the flame tube; A slotted structure is formed between the turbine leading edge rim 3 and the inner wall surface 6 of the flame tube for use in guide vane leakage flow; The inner wall 6 and outer wall 5 of the flame tube form a gas flow channel. The inner casing 1 of the turbine stator, the outer casing 4 of the turbine stator, and the turbine blades 2 form a turbine flow channel. Gas flows through the inside of the turbine flow channel to generate thrust for the engine. The straight slots and slot structures together form a cooling channel. Cooling gas rushes out from the slot structure and protects the leading edge end wall of the turbine blades 2.

[0055] The gas flow channel and the turbine flow channel are combined to form the main channel of high-temperature gas, through which the gas flows downstream to complete the Bretton cycle.

[0056] High-temperature combustion gases flow out of the combustion chamber formed by the inner wall surface 6 and the outer wall surface 5 of the flame tube, and then enter the turbine channel formed by the inner casing 1 of the turbine stator, the outer casing 4 of the turbine stator, and the turbine blade 2 wall, impacting the turbine blade 2 and the end wall surface. Cooling gas flows into the cooling channel formed by the slotted structure of the inner wall surface 6 of the flame tube and the turbine leading edge plate 3 in the secondary flow channel, and then flows into the turbine channel, covering the end wall surface, isolating the high-temperature mainstream, and protecting the end wall from high-temperature erosion. The slotted structure improves the coverage effect of the cooling gas on the end wall surface by changing the momentum distribution characteristics of the cooling gas when it flows out, thereby improving the adiabatic cooling efficiency and thus improving the cooling design effect.

[0057] The slot structure is set at a position of 0.13-0.15 axial chord length on one side of turbine blade 2.

[0058] The slot structure is located upstream of the turbine leading edge plate 3, and the first slot surface is located on the turbine leading edge plate 3.

[0059] The angle between the slot structure and the inner wall surface 6 of the flame tube is 30°-90°, i.e., the slot inclination angle α.

[0060] The combustion gas flows into the flame tube channel from the combustion chamber, and then into the turbine channel composed of the outer casing 4 of the turbine stator, the inner casing 1 of the turbine stator, and the turbine blades 2, forming a high-temperature combustion gas mainstream. The inner wall surface 6 of the flame tube and the turbine leading edge plate 3 together form a slot structure, which serves as a corrugated or triangular slot for the guide vane leakage flow. The cooling gas flows into the turbine channel from the corrugated or triangular slot formed by the inner wall surface 6 of the flame tube and the turbine leading edge plate 3, covering the lower end wall surface and the inner wall surface of the inner casing 1 of the turbine stator.

[0061] This invention also provides a novel slot structure flow guiding method for guide vane leakage flow. It adopts any of the slot structures described above for guide vane leakage flow. High-pressure cold air from the high-pressure compressor enters from the slot structure inlet. After flowing a certain distance inside the slot structure, the momentum of the fluid is redistributed within the corrugated or triangular slot structure. After flowing out of the slot structure, a cooling gas film is formed inside the turbine stator casing, isolating the high-temperature mainstream from the wall surface and protecting the wall surface from erosion by the high-temperature mainstream.

[0062] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0063] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A slot structure for guide vane leakage flow, characterized in that, include: A first groove surface and a second groove surface, with a cooling channel formed between the first groove surface and the second groove surface, the cooling channel being used to conduct cooling gas; The first groove surface has a plurality of grooves continuously distributed along the direction perpendicular to the flow of the cooling gas. A protrusion is formed between two adjacent grooves. The protrusion includes two side edges. The two side edges extend away from the first groove surface and intersect to form an end point. The plurality of end points are located on the same plane and are parallel to the second groove surface. The grooves and the protrusion are symmetrical with respect to the center line of the side edge. The two sides are transitioned by rounded chamfers to form the end portions; The length of the groove along its axial direction is 20mm-50mm; The distance between two adjacent end points on a plane parallel to the second groove surface is 20mm-26mm; The depth of the groove is 2mm-4mm; Or the endpoint is the tip formed by the intersection of the two sides; The length of the groove along its axial direction is 20mm-50mm; The distance between two adjacent end points on a plane parallel to the second groove surface is 20mm-26mm; The depth of the groove is 2mm-4mm; The angle of the tip formed by the intersection of the two sides is 120°-160°.

2. A cooling device, characterized in that, include: The turbine stator inner casing (1) and the turbine stator outer casing (4) are provided with a turbine leading edge plate (3) fixedly connected to one side of the turbine stator inner casing (1). Turbine blades (2) are disposed between the inner casing (1) of the turbine stator and the outer casing (4) of the turbine stator; A straight groove is formed between the outer casing (4) of the turbine stator and the outer wall surface (5) of the flame tube; A slot structure as described in claim 1 for guide vane leakage flow is formed between the turbine leading edge plate (3) and the inner wall surface (6) of the flame tube; The inner wall surface (6) and outer wall surface (5) of the flame tube form a gas flow channel. The inner casing (1), outer casing (4) of the turbine stator and the turbine blade (2) form a turbine flow channel. The gas flows through the inside of the turbine flow channel to generate thrust for the engine. The straight slot and the slot structure together form a cooling channel. The cooling gas rushes out from the slot structure and protects the leading edge end wall of the turbine blade (2). The slot structure is located at a position of 0.13-0.15 axial chord length on one side of the turbine blade (2); The angle between the slotted structure and the inner wall surface (6) of the flame tube is 30°-90°.

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