A docking hole cooling structure and turbine guide vane

Abstract

This invention relates to the field of aero-engine and gas turbine technology, and discloses a docking hole cooling structure and a turbine guide. The docking hole cooling structure includes: a first blind hole disposed on the outer side of the upper end wall of the turbine guide; the first blind hole introduces cooling air; a second blind hole is disposed on the side of the upper end wall of the turbine guide; the bottom end of the first blind hole and the bottom end of the second blind hole are connected and connected. This application adopts a blind hole docking structure to guide cooling air to the side of the upper end wall, significantly reducing the operating temperature of the side of the upper end wall. Because the total length of the first and second blind holes is relatively longer, the cooling air stays inside the first and second blind holes for a longer time, resulting in better cooling effect; it does not damage the internal cooling cavity structure of the blade, avoiding disruption of the cooling function design of the blade area. This application's docking hole cooling structure significantly reduces the risk of high-temperature oxidation failure at the side of the upper end wall of the turbine guide, thereby significantly extending the service life of the turbine guide.

Description

Technical Field

[0001] This invention relates to the field of aero-engine and gas turbine technology, specifically to a docking hole cooling structure and a turbine guide. Background Technology

[0002] Aero engines and gas turbines, collectively known as the "two engines," are high-end power equipment relying on gas turbine technology and hailed as the "crown jewel of modern industry." Aero engines primarily provide power for aircraft and are core components of national defense and civil aviation; gas turbines are widely used in power generation, ship propulsion, and pipeline pressurization, making them crucial energy equipment. Both share a common technological origin and integrate dozens of cutting-edge disciplines, including materials science, aerodynamics, combustion, and control, making their development extremely challenging. As a national strategic industry, their development directly impacts national defense security, energy security, and industrial competitiveness.

[0003] Aero engines are the "heart" of aircraft, primarily providing propulsion for flight. Based on their working principles and structure, they are mainly classified into turbojet engines, turbofan engines, turboprop engines, and turboshaft engines. Gas turbines, also known as gas turbine engines, are internal combustion engines that use a continuously flowing gas as the working fluid. Through fuel combustion, they generate high-temperature, high-pressure gas that drives a high-speed rotating impeller, converting the chemical energy of the fuel into mechanical work. Aero engines and gas turbines share fundamentally the same core working principles and are highly similar in key technologies such as high-temperature materials, aerodynamic design, and combustion technology, exhibiting a close "technological origin." The main differences lie in their application scenarios and design focuses: aero engines prioritize high thrust-to-weight ratio, high reliability, and adaptability, serving as the core power source for aircraft; gas turbines, on the other hand, emphasize high thermal efficiency, long lifespan, and low emissions, and are widely used in energy, industrial drives, and ship propulsion. This shared origin and different applications have led to mutual promotion in technological development and industrial upgrading between the two.

[0004] As the temperature in front of the turbines in advanced aero-engines increases, the challenges in cooling design technology for turbine guide vanes also become increasingly significant. Turbine guide vanes can generally be categorized into three types: single-unit guide vane structures, multi-unit guide vane structures, and full-ring guide vane structures. In high-performance aero-engines, multi-unit turbine guide vane structures are typically used. A multi-unit turbine guide vane structure consists of several turbine guide vanes forming a turbine guide ring. To prevent thermal expansion and subsequent compression between adjacent turbine guide vane components, a certain lateral clearance is generally maintained between adjacent turbine guide vanes. To further prevent high-temperature combustion gases from leaking through this lateral clearance, grooves are typically provided on the side walls of the turbine guide vane, and sealing plates are placed within these grooves to block the leakage of high-temperature combustion gases.

[0005] Because the high-temperature combustion gases pass over the side wall of the turbine guide vane, the side wall is subjected to high-temperature attack. Furthermore, because the side wall of the turbine guide vane is far from the blade area, the internal cooling airflow and the external film cooling airflow in the blade area have difficulty reaching the side wall. Due to these conditions, high-temperature oxidation failure easily occurs at the side wall of the turbine guide vane, severely reducing its service life.

[0006] The principle of internal cooling airflow is that cool air flows through serpentine channels or multi-cavity structures inside the blades, increasing turbulence and heat transfer area through structures such as fins and turbulence columns. Multi-cavity design increases the contact time and area between the cool air and the wall surface, but also increases flow resistance and manufacturing difficulty. The principle of film cooling is that cool air is ejected from holes or gaps on the blade surface, forming a low-temperature protective film on the wall surface, preventing high-temperature combustion gases from directly contacting the metal surface. Film cooling achieves a temperature reduction of approximately 200 to 300 degrees Celsius, making it one of the most effective methods for reducing wall temperature. Summary of the Invention

[0007] In view of this, the present invention provides a docking hole cooling structure to solve the problem that in the existing turbine guide, the end wall side of the turbine guide is attacked by high-temperature gas passing through it; and the end wall side of the turbine guide is far from the blade area of ​​the turbine guide, making it difficult for the internal cooling airflow of the blade area and the external film cooling airflow to reach the end wall side of the turbine guide, which makes it easy for high-temperature oxidation failure to occur at the end wall side of the turbine guide, seriously reducing the service life of the turbine guide.

[0008] In a first aspect, the present invention provides a docking hole cooling structure, suitable for being disposed on the upper end wall of a turbine guide, the docking hole cooling structure comprising: A first blind hole is provided on the outer side of the upper end wall of the turbine guide along the radial direction of the turbine guide; the opening of the first blind hole is provided on the outer side of the upper end wall of the turbine guide, and the opening of the first blind hole is adapted to introduce external cooling air; A second blind hole is disposed on the upper end wall side of the turbine guide, with its opening located on the upper end wall side of the turbine guide. The bottom end of the first blind hole is connected to the bottom end of the second blind hole. The diameter of the first blind hole is larger than that of the second blind hole. The airflow area of ​​the first and second blind holes at the connection point is not less than that of the second blind hole. Beneficial effects: Compared with other turbine guide cooling structures, this application, by adopting the above technical solution, uses a blind hole connection structure on the outer side of the upper end wall and the upper end wall side of the turbine guide, diverting external cooling air to the upper end wall side, significantly reducing the operating temperature of the upper end wall side, and the structure is simple and easy to implement. Simultaneously, because the total length of the first and second blind holes is relatively longer, the residence time of the cooling air inside the first and second blind holes is relatively longer, resulting in better cooling effect. Furthermore, the connection hole cooling structure described in this application will not damage the internal cooling cavity structure of the blade, avoiding disruption of the cooling function design of the blade area. The cooling structure of the mating hole described in this application significantly reduces the risk of high-temperature oxidation failure at the upper end wall side of the turbine guide, thereby significantly extending the service life of the turbine guide. Furthermore, the first blind hole in this application can introduce external cooling air from a position below the depth of the original sealing groove of the turbine guide, and then exhaust the cooling air from a position away from the sealing groove and close to the flow channel surface of the upper end wall, to cool the upper end wall side of the turbine guide. This bypassing of the sealing groove allows the cooling air to bypass the obstruction of the existing sealing strip located on the sealing groove.

[0009] Optionally, both the first blind hole and the second blind hole are cylindrical holes; or both the first blind hole and the second blind hole are irregularly shaped holes.

[0010] Optionally, the cross-sections of the first blind hole and the second blind hole are both square; or the cross-sections of the first blind hole and the second blind hole are both elliptical; or the shapes of the first blind hole and the second blind hole are both trumpet-shaped.

[0011] Optionally, when both the first blind hole and the second blind hole are cylindrical holes, assuming the diameter of the second blind hole is S, the diameter of the first blind hole is 1.5S to 2S.

[0012] Optionally, the range of S is 0.4 mm to 2 mm.

[0013] Optionally, the angle between the first blind hole and the outer surface of the upper end wall of the turbine guide is in the range of 80° to 100°; the angle between the second blind hole and the side surface of the upper end wall of the turbine guide is in the range of 40° to 70°.

[0014] Optionally, the number of the first blind holes is multiple, and the number of the second blind holes is multiple corresponding to the first blind holes. Beneficial effect: This application adopts the above technical solution, which significantly improves cooling efficiency.

[0015] Optionally, a sealing groove is provided on the upper wall side of the turbine guide, the distance between the sealing groove and the second blind hole is in the range of 1S to 2S; the distance between the edge of the first blind hole and the bottom of the sealing groove is in the range of 5S to 10S. Beneficial effects: By adopting the above technical solution, this application sets the distance between the sealing groove and the second blind hole to 1S to 2S, ensuring a certain distance between the second blind hole and the sealing groove, preventing the second blind hole from weakening the strength of the sealing groove and thus affecting the subsequent fixing of the sealing plate; and by setting the distance between the edge of the first blind hole and the bottom of the sealing groove to 5S to 10S, it prevents the first blind hole from weakening the strength of the sealing groove and thus affecting the subsequent fixing of the sealing plate.

[0016] Optionally, an upper endwall flow channel surface is provided on the upper endwall of the turbine guide near the blade of the turbine guide; the distance between the upper endwall flow channel surface and the second blind hole is in the range of 1S to 2S. Beneficial effect: By adopting the above technical solution, this application prevents the setting of the second blind hole from affecting the strength and reliability of the upper endwall flow channel surface by setting the distance between the upper endwall flow channel surface and the second blind hole to the range of 1S to 2S, thereby preventing any impact on the flow condition of the fluid on the upper endwall flow channel surface.

[0017] Secondly, the present invention also provides a turbine guide, including the aforementioned docking hole cooling structure. Beneficial effects: Compared with other turbine guide cooling structures, this application, employing the above-mentioned technical solution, uses a blind hole docking structure on the outer side and side surface of the upper end wall of the turbine guide, guiding external cooling air to the side surface of the upper end wall, significantly reducing the operating temperature of the side surface of the upper end wall, and the structure is simple and easy to implement. Simultaneously, because the total length of the first blind hole combined with the second blind hole is relatively longer, the residence time of cooling air inside the first and second blind holes is relatively longer, resulting in better cooling effect; and the docking hole cooling structure described in this application will not damage the internal cooling cavity structure of the blade, avoiding damage to the cooling function design of the blade area. The docking hole cooling structure described in this application significantly reduces the risk of high-temperature oxidation failure at the side surface of the upper end wall of the turbine guide, thereby significantly extending the service life of the turbine guide. Furthermore, the first blind hole in this application can introduce external cooling air from a position below the depth of the original sealing groove of the turbine guide, and then lead the cooling air out from a position on the side of the upper end wall that is far from the sealing groove and close to the flow channel surface of the upper end wall, so as to cool the side of the upper end wall of the turbine guide. The above-mentioned method of bypassing the sealing groove allows the cooling air to bypass the obstruction of the existing sealing plate on the sealing groove. Attached Figure Description

[0018] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the docking hole cooling structure provided in an embodiment of the present invention. Figure 1 ; Figure 2 for Figure 1 Schematic diagram of the cross-sectional structure at point AA; Figure 3 This is a schematic diagram of the docking hole cooling structure provided in an embodiment of the present invention. Figure 2 .

[0020] Explanation of reference numerals in the attached figures: 1. Blade body inner cavity; 2. First blind hole; 3. Second blind hole; 4. Outer side of upper end wall; 5. Blade body; 6. Sealing groove; 7. Side of upper end wall; 8. Flow channel surface of upper end wall; 9. Upper end wall. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, 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, 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.

[0022] A turbine guide vane is a stationary component in an aero-engine turbine assembly. It mainly consists of an inner ring, an outer ring, and a set of guide vanes. The turbine guide vane guides and accelerates the flow of high-temperature gas towards the impeller. Often called a "stator" or "turbine nozzle," it is located between the combustion chamber and the turbine rotor and is a key component of a gas turbine engine. The main functions of the turbine guide vane include: 1. Guiding airflow direction: It guides high-temperature, high-pressure gas from the combustion chamber into the turbine, directing the airflow in a specific direction towards the impeller, providing the required airflow conditions for turbine operation. 2. Energy conversion and acceleration: It converts thermal energy into kinetic energy, allowing some of the airflow's thermal energy to drive the impeller; it also accelerates and pressurizes the gas as it flows through the converging channel, increasing its speed and decreasing its pressure, allowing it to enter the turbine rotor blade passage at a suitable angle and high speed. 3. Optimizing flow performance: It reduces losses; a well-designed system can reduce airflow vortices and losses, improving engine efficiency; and it ensures balanced distribution, allowing the airflow to be evenly distributed among the blades, avoiding flow deviation and guaranteeing stable turbine operation.

[0023] Based on the applicant's creative thinking and analysis, for turbine guide vanes, when the gas temperature is low, a dedicated cooling structure is typically not installed on the side wall of the turbine guide vane. Instead, the improved material properties of the turbine guide vane itself are used to resist the attack of high-temperature gas; in this case, the turbine guide vane is generally made of expensive high-temperature alloy materials. When the gas temperature is high, there are generally two approaches in the existing technology. The first approach is to open a cooling hole one on the side wall of the turbine guide vane, which leads directly to the inner cavity of the turbine guide vane's blade area. The second approach is to open a second cooling hole along the radial direction of the turbine guide vane, which leads directly to the outer side of the turbine guide vane's end wall. However, with the first approach, when the cooling hole one leads directly to the inner cavity of the turbine guide vane's blade area, it is easy to damage the cooling structure of the blade's inner cavity, thereby compromising the function and strength of the turbine guide vane's existing pre-designed cooling system. In the second approach, when cooling holes two are opened on the end wall of the turbine guide vane along the radial direction of the turbine guide vane, and these two cooling holes lead to the outer side of the end wall of the turbine guide vane, the cooling air in the two cooling holes is easily blocked by the sealing plate, making it difficult to achieve the cooling function of the side wall of the turbine guide vane. Cooling technology is generally used in conjunction with thermal barrier coatings. Thermal barrier coatings can further reduce the substrate temperature of the metal, allowing the turbine inlet temperature to be further increased. For the above reasons, this application proposes a butt hole cooling structure to effectively cool the side wall of the turbine guide vane.

[0024] Reference Figures 1 to 3 The diagram shows a specific embodiment of the docking hole cooling structure, which is adapted to be installed on the upper end wall 9 of the turbine guide. The docking hole cooling structure includes: a first blind hole 2 and a second blind hole 3.

[0025] Reference Figure 1 and Figure 2As shown, the first blind hole 2 is disposed on the outer side 4 of the upper end wall of the turbine guide along the radial direction of the turbine guide; the opening of the first blind hole 2 is disposed on the outer side 4 of the upper end wall of the turbine guide, and the opening of the first blind hole 2 is suitable for introducing external cooling air. The second blind hole 3 is disposed on the side 7 of the upper end wall of the turbine guide, and the opening of the second blind hole 3 is disposed on the side 7 of the upper end wall of the turbine guide; the bottom end of the first blind hole 2 is connected to the bottom end of the second blind hole 3; the diameter of the first blind hole 2 is larger than the diameter of the second blind hole 3; the flow area of ​​cooling air at the connection point of the first blind hole 2 and the second blind hole 3 is not less than the flow area of ​​cooling air of the second blind hole 3. This application, using the above embodiment, compared with other turbine guide cooling structures, by adopting a blind hole connection structure on the outer side 4 and the side 7 of the upper end wall of the turbine guide, external cooling air is diverted to the side 7 of the upper end wall, significantly reducing the operating temperature of the side 7 of the upper end wall, and the structure is simple and easy to implement. Meanwhile, since the total length of the first blind hole 2 combined with the second blind hole 3 is relatively longer, the residence time of cooling air inside the first blind hole 2 and the second blind hole 3 is relatively longer, resulting in better cooling effect. Furthermore, the docking hole cooling structure described in this application will not damage the cooling cavity structure of the blade body 5's internal blade cavity 1, avoiding disruption of the cooling function design of the area of ​​the blade body 5. The docking hole cooling structure described in this application significantly reduces the risk of high-temperature oxidation failure at the upper end wall side surface 7 of the turbine guide vane, thereby significantly extending the service life of the turbine guide vane. Further, the first blind hole 2 of this application can introduce external cooling air from a position below the depth of the original sealing groove 6 of the turbine guide vane, and then draw the cooling air out from a position away from the sealing groove 6 and close to the upper end wall flow channel surface 8 on the upper end wall side surface 7 to cool the upper end wall side surface 7 of the turbine guide vane. This bypassing of the sealing groove 6 allows the cooling air to bypass the obstruction of the existing sealing sheet on the sealing groove 6.

[0026] Reference Figure 2 As shown, the first blind hole 2 of this application can introduce external cooling air from a position below the depth of the original sealing groove 6 of the turbine guide, and then draw the cooling air out from a position away from the sealing groove 6 and close to the upper end wall flow channel surface 8 on the upper end wall side surface 7 to cool the upper end wall side surface 7 of the turbine guide. The above-mentioned bypassing of the sealing groove 6 allows the cooling air to bypass the obstruction of the existing sealing sheet on the sealing groove 6.

[0027] In one specific implementation, refer to Figure 1 and Figure 3 As shown, the first blind hole 2 is also known as the large blind hole, and the second blind hole 3 is also known as the small blind hole. Figure 1The second blind hole 3 is indicated by a thin solid line, showing that it is located inside the turbine guide.

[0028] In some specific embodiments, the bottom end of the first blind hole 2 and the bottom end of the second blind hole 3 can be vertically connected; of course, the bottom end of the first blind hole 2 and the bottom end of the second blind hole 3 can also be non-vertically connected.

[0029] In one specific implementation, refer to Figure 1 and Figure 2 As shown, both the first blind hole 2 and the second blind hole 3 are cylindrical holes.

[0030] In one specific embodiment, both the first blind hole 2 and the second blind hole 3 are irregularly shaped holes. Irregularly shaped holes refer to holes that are non-standard in shape and non-circular in shape.

[0031] In one specific embodiment, both the first blind hole 2 and the second blind hole 3 have square cross-sections.

[0032] In one specific embodiment, the cross-sections of the first blind hole 2 and the second blind hole 3 are both elliptical.

[0033] In one specific embodiment, the cross-sections of the first blind hole 2 and the second blind hole 3 are both polygonal.

[0034] In one specific embodiment, the cross-sections of the first blind hole 2 and the second blind hole 3 are both irregular shapes.

[0035] In one specific embodiment, both the first blind hole 2 and the second blind hole 3 are trumpet-shaped.

[0036] In one specific embodiment, when both the first blind hole 2 and the second blind hole 3 are cylindrical holes, assuming the diameter of the second blind hole 3 is S, the diameter of the first blind hole 2 is 1.5S to 2S.

[0037] In one specific embodiment, the range of S is 0.4 mm to 2 mm, that is, the diameter of the second blind hole 3 is in the range of 0.4 mm to 2 mm, and the diameter of the first blind hole 2 is in the range of 0.6 mm to 4 mm.

[0038] In one specific implementation, refer to Figure 1 and Figure 2 As shown, the angle between the first blind hole 2 and the outer surface 4 of the upper end wall of the turbine guide is in the range of 80° to 100°; the angle between the second blind hole 3 and the side surface 7 of the upper end wall of the turbine guide is in the range of 40° to 70°.

[0039] In one specific implementation, refer to Figure 1 and Figure 2 As shown, the first blind hole 2 is arranged in a direction parallel to the upper end wall side 7, and the angle between the edge of the first blind hole 2 near the upper end wall side 7 and the outer surface of the upper end wall 4 of the turbine guide is in the range of 80° to 100°.

[0040] In one specific implementation, refer to Figure 1 and Figure 2 As shown, the second blind hole 3 is arranged in a direction parallel to the surface of the outer side of the upper end wall 4, and the angle between the edge of the second blind hole 3 near the outer side of the upper end wall 4 and the side surface of the upper end wall 7 of the turbine guide is in the range of 40° to 70°.

[0041] In one specific implementation, refer to Figure 1 and Figure 3 As shown, there are multiple first blind holes 2, and multiple second blind holes 3 corresponding to the first blind holes 2. This application employs the above-described embodiment to significantly improve cooling efficiency.

[0042] In one specific implementation, refer to Figure 1 and Figure 3 As shown, multiple first blind holes 2 can be located on the same straight line; multiple second blind holes 3 can be located on the same straight line.

[0043] In one specific implementation, refer to Figure 1 As shown, the first blind hole 2 is a row of holes spaced apart from the edge of the inner cavity 1 of the blade; the row of first blind holes 2 consists of four holes spaced apart.

[0044] In one specific implementation, refer to Figure 3 As shown, the second blind hole 3 is a row of holes spaced apart from the sealing groove 6; the row of second blind holes 3 consists of four holes spaced apart.

[0045] In one specific implementation, refer to Figure 2 and Figure 3As shown, a sealing groove 6 is provided on the upper wall side 7 of the turbine guide. The distance between the sealing groove 6 and the second blind hole 3 ranges from 1S to 2S; the distance between the edge of the first blind hole 2 and the bottom of the sealing groove 6 ranges from 5S to 10S. When the range of S is 0.4 mm to 2 mm, the distance between the sealing groove 6 and the second blind hole 3 ranges from 0.4 mm to 4 mm; the distance between the edge of the first blind hole 2 and the bottom of the sealing groove 6 ranges from 2 mm to 20 mm. This application adopts the above embodiment. By setting the distance between the sealing groove 6 and the second blind hole 3 to 1S to 2S, the second blind hole 3 is kept at a certain distance from the sealing groove 6, preventing the second blind hole 3 from weakening the strength of the sealing groove 6 and thus affecting the subsequent fixing of the sealing plate. Furthermore, by setting the distance between the edge of the first blind hole 2 and the bottom of the sealing groove 6 to 5S to 10S, the first blind hole 2 is prevented from weakening the strength of the sealing groove 6 and thus affecting the subsequent fixing of the sealing plate.

[0046] In one specific implementation, refer to Figure 2 As shown, the bottom of the sealing groove 6 is provided with a rounded corner.

[0047] In one specific implementation, refer to Figure 2 As shown, the first blind hole 2 is perpendicular to the direction in which the sealing groove 6 is set, and the depth direction of the sealing groove 6 is parallel to the surface of the outer side 4 of the upper end wall. The distance between the edge of the first blind hole 2 near the side surface 7 of the upper end wall and the bottom of the sealing groove 6 is in the range of 5S to 10S.

[0048] In one specific implementation, refer to Figure 2 As shown, the sealing groove 6 has a certain depth, and its cross-section is parallel to the direction in which the second blind hole 3 is set. Furthermore, the sealing groove 6 is closer to the outer side of the upper wall 4 than the second blind hole 3. The distance between the surface of the sealing groove 6 away from the outer side of the upper wall 4 and the edge of the second blind hole 3 near the outer side of the upper wall 4 ranges from 1 second to 2 seconds.

[0049] In one specific embodiment, a sealing plate is adapted to be placed within the sealing groove 6. The mating hole cooling structure of this application bypasses the sealing plate within the sealing groove 6, introducing external cooling air into the upper end wall side 7 of the turbine guide to significantly and effectively cool the upper end wall side 7.

[0050] In one specific implementation, refer to Figure 2 and Figure 3As shown, an upper end wall flow channel surface 8 is provided on the upper end wall 9 of the turbine guide near the blade 5 of the turbine guide; the distance between the upper end wall flow channel surface 8 and the second blind hole 3 ranges from 1S to 2S. When the range of S is 0.4 mm to 2 mm, the distance between the upper end wall flow channel surface 8 and the second blind hole 3 ranges from 0.4 mm to 4 mm. This application adopts the above embodiment, by setting the distance between the upper end wall flow channel surface 8 and the second blind hole 3 to 1S to 2S, preventing the setting of the second blind hole 3 from affecting the strength and reliability of the upper end wall flow channel surface 8, thereby preventing any impact on the flow of fluid on the upper end wall flow channel surface 8.

[0051] In one specific implementation, refer to Figure 2 and Figure 3 As shown, the upper end wall flow channel surface 8 is parallel to the setting direction of the second blind hole 3, and the upper end wall flow channel surface 8 is parallel to the surface of the outer side of the upper end wall 4; the distance between the upper end wall flow channel surface 8 and the edge of the second blind hole 3 away from the outer side of the upper end wall 4 is in the range of 1S to 2S.

[0052] In one specific implementation, refer to Figure 1 As shown, an inner cavity 1 is provided on the blade 5. An internal cooling airflow is provided within the inner cavity 1, forming a cooling structure within the region of the blade 5. The docking hole cooling structure described in this application provides better cooling for the upper end wall side 7 of the turbine guide vane and does not affect the cooling structure within the region of the turbine guide vane 5.

[0053] This application also provides a turbine guide, including the aforementioned docking hole cooling structure. Compared to other turbine guide cooling structures, this application, using the above-described embodiment, employs a blind hole docking structure on the outer side 4 and side 7 of the upper end wall of the turbine guide, directing external cooling air to the side 7 of the upper end wall, significantly reducing the operating temperature of the side 7 of the upper end wall, and the structure is simple and easy to implement. Simultaneously, because the total length of the first blind hole 2 combined with the second blind hole 3 is relatively longer, the residence time of cooling air inside the first blind hole 2 and the second blind hole 3 is relatively longer, resulting in better cooling effect; furthermore, the docking hole cooling structure described in this application does not damage the cooling cavity structure of the inner cavity 1 of the blade 5, avoiding damage to the cooling function design of the area of ​​the blade 5. The docking hole cooling structure described in this application significantly reduces the risk of high-temperature oxidation failure at the location of the side 7 of the upper end wall of the turbine guide, thereby significantly extending the service life of the turbine guide. Furthermore, the first blind hole 2 of this application can introduce external cooling air from a position below the depth of the original sealing groove 6 of the turbine guide, and then draw the cooling air out from a position away from the sealing groove 6 and close to the upper end wall flow channel surface 8, so as to cool the upper end wall side surface 7 of the turbine guide. The above-mentioned bypassing of the sealing groove 6 allows the cooling air to bypass the obstruction of the existing sealing plate on the sealing groove 6.

[0054] Turbine guide vanes are an important component of turbines in thermodynamic devices such as aero engines and gas turbines. Turbine guide vanes are usually installed in front of the turbine and are mainly composed of guide vanes and other structures. Their function is to guide the high-temperature and high-pressure gas output from the combustion chamber, so that the high-temperature and high-pressure gas enters the working blades of the turbine in a certain direction and angle. This allows the thermal energy and pressure energy of the high-temperature and high-pressure gas to be effectively converted into the mechanical energy of the turbine, driving the turbine to rotate at high speed, and in turn driving the compressor and other components to work.

[0055] The turbine guide with the docking hole cooling structure described in this application, after actual testing and inspection, showed that the working temperature of the end wall side of the turbine guide dropped by about 80°C, and the end wall side area of ​​the turbine guide was undamaged after the test, thus fully achieving the intended purpose of the technical solution of this application.

[0056] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by this application.

Claims

1. A docking hole cooling structure, suitable for installation on the upper end wall (9) of a turbine guide, characterized in that, The cooling structure for the docking hole includes: A first blind hole (2) is provided on the outer side (4) of the upper end wall of the turbine guide along the radial direction of the turbine guide; the opening of the first blind hole (2) is provided on the outer side (4) of the upper end wall of the turbine guide, and the opening of the first blind hole (2) is suitable for introducing external cooling air; The second blind hole (3) is provided on the upper end wall side (7) of the turbine guide, and the opening of the second blind hole (3) is provided on the upper end wall side (7) of the turbine guide; the bottom end of the first blind hole (2) is connected to the bottom end of the second blind hole (3); the diameter of the first blind hole (2) is larger than the diameter of the second blind hole (3); the flow area of ​​the cooling air between the first blind hole (2) and the second blind hole (3) at the connection point is not less than the flow area of ​​the cooling air of the second blind hole (3).

2. The cooling structure for the mating hole according to claim 1, characterized in that, The first blind hole (2) and the second blind hole (3) are both cylindrical holes; or the first blind hole (2) and the second blind hole (3) are both irregularly shaped holes.

3. The cooling structure for the mating hole according to claim 2, characterized in that, The cross-sections of the first blind hole (2) and the second blind hole (3) are both square; or the cross-sections of the first blind hole (2) and the second blind hole (3) are both elliptical; or the shapes of the first blind hole (2) and the second blind hole (3) are both trumpet-shaped.

4. The cooling structure for the mating hole according to claim 2, characterized in that, When both the first blind hole (2) and the second blind hole (3) are cylindrical holes, assuming the diameter of the second blind hole (3) is S, the diameter of the first blind hole (2) is 1.5S to 2S.

5. The cooling structure for the mating hole according to claim 4, characterized in that, The range of S is 0.4 mm to 2 mm.

6. The cooling structure for the mating hole according to any one of claims 1-5, characterized in that, The angle between the first blind hole (2) and the outer surface (4) of the upper end wall of the turbine guide is 80° to 100°; the angle between the second blind hole (3) and the side surface (7) of the upper end wall of the turbine guide is 40° to 70°.

7. The cooling structure for the mating hole according to any one of claims 1-5, characterized in that, There are multiple first blind holes (2), and multiple second blind holes (3) corresponding to the first blind holes (2).

8. The cooling structure for the mating hole according to claim 4 or 5, characterized in that, A sealing groove (6) is provided on the upper end wall side (7) of the turbine guide. The distance between the sealing groove (6) and the second blind hole (3) is 1S to 2S. The distance between the edge of the first blind hole (2) and the bottom of the sealing groove (6) is 5S to 10S.

9. The cooling structure for the mating hole according to claim 8, characterized in that, An upper end wall flow channel surface (8) is provided on the upper end wall (9) of the turbine guide near the blade (5) of the turbine guide; the distance between the upper end wall flow channel surface (8) and the second blind hole (3) is in the range of 1S to 2S.

10. A turbine guide, characterized in that, include: The docking hole cooling structure according to any one of claims 1-9.

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