Slot cooling design method for turbine vane endwall leading edge

Abstract

The application discloses a kind of slot cooling design methods of turbine guide vane end area leading edge, comprising the following steps: step 1, determine input calculation boundary;Step 2, calculate the cold effect demand of turbine guide vane end area leading edge gas film protection area L;Step 3, calculate the initial value of blade end wall required cold gas flow, the width of slot is obtained by cold gas flow conversion;Step 4, provide the jet angle of slot cold gas, the height of slot, the distance between slot cold gas outlet and blade;Step 5, calculate the simulation cold effect of end area leading edge;Step 6, judge whether simulation cold effect meets the cold effect demand;Step 7: output the final parameter that meets the cold effect demand.The slot cooling design method of turbine guide vane end area leading edge of the present application can obtain the slot cooling structure that meets the cold effect demand of end area leading edge under the premise of minimum cold gas demand, effectively prevent gas backflow, protect end wall area from being ablated, and play a heat protection role for end area leading edge gas film protection area.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular, to a slotted cooling design method for the leading edge of a turbine guide vane tip region. Background Technology

[0002] With the improvement of aero-engine cycle parameters, the gas temperature at the turbine blade endwall has increased significantly, causing the blade endwall metal temperature to exceed material limits, thus reducing blade lifespan. Effective protection measures are needed for the turbine blade endwall. Turbine guide vanes often employ a slotted cooling design at the leading edge of the end region. This structure not only prevents gas backflow and enhances convective heat transfer at the guide vane endwall, providing thermal protection for a portion of the endwall, but also effectively suppresses secondary flow in the blade cascade passage, reducing aerodynamic losses and improving turbine efficiency. Compared to slotless upstream film cooling structures, slotted film cooling holes suppress horseshoe vortex formation, cool the endwall between the holes, and improve endwall film cooling efficiency.

[0003] Existing turbine guide vane end-edge slotted cooling structure designs rely on engineering design experience to determine parameters such as the jet angle of the slotted cooling gas, the height of the slot, the width of the slot, and the initial value of the distance between the guide vane and the blade. However, these parameters are not optimal solutions and have the following problems: 1. If the width of the slot is too large, it will lead to excessive airflow, excessive temperature difference between the blade endwall and the blade body, and increased local stress, which is not conducive to the long service life of the blade. In addition, excessive cold air leakage will affect aerodynamic performance and turbine work capacity, thus affecting the overall performance of the engine. If the width of the slot is too small, the airflow will be insufficient, resulting in insufficient cooling of the blade endwall and causing blade endwall burning.

[0004] 2. If the height of the slot is too large, the outflow velocity of the air film will be too low. The cold air will be unable to resist the lateral pressure gradient in the blade channel and will mix with the mainstream. As the cold air continues to flow downstream, the heat insulation effect of the air film will weaken. The air film will not be able to cover the area of ​​the end wall close to the blade body. The local air film cooling effect is poor and local high temperature occurs. If the height of the slot is too small, the flow loss of the airflow inside the slot will be greater, the flow coefficient will be lower, and the amount of cold air will be insufficient. Summary of the Invention

[0005] This invention provides a slotted cooling design method for the leading edge of the turbine guide vane end region to solve the technical problem that the existing turbine guide vane film cooling structure has a poor overall film cooling effect, which leads to increased blade end wall temperature, poor thermal protection effect, and subsequent failures such as ablation and cracking, resulting in a reduction in blade life. The invention can provide a slotted cooling structure that meets the cooling efficiency requirements of the leading edge of the end region with the minimum amount of cooling gas required, ensuring that the end wall region is not ablated and effectively preventing backflow of combustion gas.

[0006] According to one aspect of the present invention, a slotted cooling design method for the leading edge of a turbine guide vane tip region is provided, comprising the following steps: Step 1: Determine the input calculation boundary and provide the cold air parameters and combustion gas parameters of the leading edge of the turbine guide vane; Step 2: Calculate the cooling effect requirement of the leading edge film protection region L of the turbine guide vane tip area. The cooling effect requirement includes the average cooling effect requirement. and minimum cooling efficiency requirements ; Step 3: Calculate the initial value of the required cooling airflow to the blade endwall. The width w of the groove is obtained by converting the cold air flow rate. Step 4: Provide the jet angle α of the cold air from the slot and the height of the slot. Distance between slotted air outlet and blade ; Step 5: Calculate the simulated cooling effect at the leading edge of the end region. The simulated cooling effect includes the simulated average cooling effect. and the cooling effect along the way ; Step 6: Determine if the simulated cooling effect meets the cooling requirement. If the simulated cooling effect obtained in Step 5 meets the cooling requirement, proceed to Step 7; if the simulated cooling effect does not meet the cooling requirement, reduce the height of the groove. and the distance between the air outlet and the blades Until the simulated cooling effect meets the cooling requirement; if the height of the groove Distance between the slotted air outlet and the blade If the simulated cooling effect still does not meet the cooling effect requirements even with the optimal structure, then increase the cold air inlet pressure and increase the flow rate until the simulated cooling effect meets the cooling effect requirements. Step 7: Output the final parameters that meet the cooling efficiency requirements. The final parameters include the final jet angle α of the cold air in the slot and the final height of the slot. The final width of the groove The final value of the distance between the coolant outlet and the blades. , final inlet pressure of cold air and the final inlet temperature of the air conditioner .

[0007] Furthermore, in step 1, the cooling air parameters include the static pressure at the inlet of the leading edge slot of the end region. The temperature of the cold air in the leading edge slot of the end area Gas parameters include mainstream gas flow rate The gas-side pressure at the root or tip of the turbine guide vane inlet Gas side temperature .

[0008] Furthermore, in step 2, the average operating temperature limit value of the turbine guide vane is...T av The average cooling demand of the leading edge region L is , ; The maximum operating temperature limit for turbine guide vanes is [value missing]. The minimum cooling efficiency requirement for the leading edge region L is , .

[0009] Furthermore, in step 3, the average cooling efficiency requirement at the leading edge of the end region is... hour, ; ; ; Where k is the isentropic exponent of air, and R is the gas constant of air. As the mainstream traffic, Mass flow rate ratio, The flow area of ​​the slot is the smallest at the lowest radius of the cold air inlet, which is where the cold air is intercepted. The value is selected based on the minimum radius of the cold air inlet. Determine the width w of the slot to be the minimum radius of the cold air inlet.

[0010] Furthermore, in step 4, the given angle value α of the cold air jet in the slot is 30°≤α≤60°.

[0011] Furthermore, in step 4, the height of the groove is Treating the slot as a concentric annular joint, the flow coefficient of the concentric annular joint is... , ; ; ; in, The dynamic viscosity coefficient of cold air. Cold air inlet speed, Inlet Reynolds number, Cold air density, The flow area of ​​the diversion channel; Let be the inner radius of the deflector. The radial height of the end wall. like If the value is ≥0.7, the airflow loss inside the groove is considered small, given the height of the groove. initial value To meet cooling requirements; if Then increase the height of the groove. The value, until ≥0.7.

[0012] Furthermore, in step 4, the distance between the cold air outlet and the blade... initial value The distance between the cool air outlet and the blades is determined by the engine turbine structure layout. The range of values ​​is .

[0013] Furthermore, in step 5, the average wall temperature of the leading edge of the turbine guide vane is obtained by numerical calculation of the model. The simulated average cooling effect at the leading edge of the end region is , ; Let a certain position of the leading edge end wall of the end region along the axial direction be... Then the wall temperature at that location is The cooling effect along the path at this location is , .

[0014] Furthermore, in step 6, if the average cooling efficiency of the leading edge of the end region obtained in step 5 is... And the cooling effect along the way If so, the cooling structure of the leading edge slot in the end region of the turbine guide vane is considered to meet the requirements; if and / or Therefore, it is believed that the leading edge slot structure of the turbine guide vane end region cannot meet the cooling requirements, and the height of the slot should be reduced. Simultaneously satisfy The requirement of ≥0.7 is met, and the distance between the air outlet and the blades is reduced. The value is taken until the average cooling effect. And the cooling effect along the way .

[0015] Furthermore, in step 6, if the height of the groove is reduced... Until =0.7, and the distance between the air outlet and the blades The value has been reduced to ,and and / or Then increase the width w of the groove until the average cooling efficiency is achieved. And the cooling effect along the way ; or, If the height of the groove is reduced Until =0.7, and the distance between the air outlet and the blades The value has been reduced to ,and and / or This increases the pressure at the air inlet. and reduce the temperature of the air inlet until the average cooling effect And the cooling effect along the way .

[0016] The present invention has the following beneficial effects: The slotted cooling design method for the leading edge of the turbine guide vane end region of the present invention, by controlling the jet angle of the slotted cooling gas, the height of the slot, the width of the slot, and the initial value of the distance between the guide vane and the blade, can obtain a slotted cooling structure that meets the cooling efficiency requirements of the leading edge of the end region under the premise of minimum cooling gas demand. This makes the simulated cooling efficiency value of the leading edge of the end region higher than the average cooling efficiency requirement value and the minimum cooling efficiency limit value along the blade, effectively preventing backflow of combustion gas, ensuring that the end wall area is not ablated, and playing a role in thermal protection for the gas film protection area of ​​the leading edge of the end region.

[0017] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0018] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a schematic diagram of the groove structure of a preferred embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of the air-supported membrane protection zone according to a preferred embodiment of the present invention; Figure 3 A schematic diagram of the minimum radius of the cold air inlet, the inner radius of the guide plate, and the radial height of the end wall in a preferred embodiment of the present invention. Detailed Implementation

[0019] 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 a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0020] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, and back), the orientation or positional relationship of the directional indications is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the embodiments according to this application and simplifying the description, and is not intended to indicate or imply that the device or unit referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation on the embodiments according to this application.

[0021] Furthermore, if the embodiments of this invention involve descriptions using terms such as "first," "second," and "third," these terms are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first," "second," or "third" may explicitly or implicitly include at least one of those features. The term "multiple" refers to two or more unless otherwise explicitly defined. Terms such as "installed," "connected," "attached," and "fixed" should be interpreted broadly. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; "attached" can be a direct connection or an indirect connection through an intermediate medium.

[0022] If the words "and / or" or "and / or" appear in the text, they mean three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution that satisfies both A and B. In addition, the technical solutions of various embodiments can be combined with each other, but this must be based on the ability of a person skilled in the art to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0023] To better understand the above technical solution, the following detailed explanation is provided in conjunction with the accompanying drawings.

[0024] like Figure 1 , Figure 2 and Figure 3 As shown, the slotted cooling design method for the leading edge of the turbine guide vane tip region in this embodiment includes the following steps: Step 1: Determine the input calculation boundary and provide the cold air parameters and combustion gas parameters of the leading edge of the turbine guide vane; Step 2: Calculate the cooling effect requirement of the leading edge film protection region L of the turbine guide vane tip area. The cooling effect requirement includes the average cooling effect requirement. and minimum cooling efficiency requirements ; Step 3: Calculate the initial value of the required cooling airflow to the blade endwall. The width w of the groove is obtained by converting the cold air flow rate. Step 4: Provide the jet angle α of the cold air from the slot and the height of the slot. Distance between slotted air outlet and blade ; Step 5: Calculate the simulated cooling effect at the leading edge of the end region. The simulated cooling effect includes the simulated average cooling effect. and cooling effect along the way ; Step 6: Determine if the simulated cooling effect meets the cooling requirement. If the simulated cooling effect obtained in Step 5 meets the cooling requirement, proceed to Step 7; if the simulated cooling effect does not meet the cooling requirement, reduce the height of the groove. and the distance between the air outlet and the blades Until the simulated cooling effect meets the cooling requirement; if the height of the groove Distance between the slotted air outlet and the blade If the simulated cooling effect still does not meet the cooling effect requirements even with the optimal structure, then increase the cold air inlet pressure and increase the flow rate until the simulated cooling effect meets the cooling effect requirements. Step 7: Output the final parameters that meet the cooling efficiency requirements. The final parameters include the final jet angle α of the cold air in the slot and the final height of the slot. The final width of the groove The final value of the distance between the coolant outlet and the blades. , final inlet pressure of cold air and the final inlet temperature of the air conditioner .

[0025] The slotted cooling design method for the leading edge of the turbine guide vane tip region in this embodiment controls the jet angle α of the slotted cooling air and the height of the slot. The width w of the slot and the initial value of the distance between the guide vane and the blade. Under the premise of minimum cooling demand, a slotted cooling structure that meets the cooling effect requirements of the leading edge of the end zone can be derived, so that the simulated cooling effect value of the leading edge of the end zone is higher than the average cooling effect requirement value and the minimum cooling effect limit value along the path, effectively preventing gas backflow, ensuring that the end wall area is not burned, and playing a role in thermal protection for the gas film protection area L at the leading edge of the end zone.

[0026] In this embodiment, the cooling air parameters in step 1 include the static pressure at the inlet of the end zone leading edge slot. The temperature of the cold air in the leading edge slot of the end area Gas parameters include mainstream gas flow rate The gas-side pressure at the root or tip of the turbine guide vane inlet Gas side temperature .

[0027] In this embodiment, in step 2, the design limit value for the leading edge wall temperature of the end region is combined with the given material of the turbine cooling blades. The turbine first-stage guide vane is made of a high-temperature alloy, and the average operating temperature limit value of the turbine guide vane is... T av The average cooling demand of the leading edge region L is , ; The maximum operating temperature limit for turbine guide vanes is [value missing]. The minimum cooling efficiency requirement for the leading edge region L is , .

[0028] In this embodiment, in step 3, the average cooling efficiency requirement at the leading edge of the end region is... At that time, the initial value of the cooling air flow rate required for the blade endwall is According to the mass flow rate calculation formula ; in, The flow area of ​​the slot is the smallest at the lowest radius of the cold air inlet, which is where the cold air is intercepted. Therefore, the value of is selected according to the lowest radius of the cold air inlet. k is the isentropic index (adiabatic index) of air, and k is taken as 1.4. R is the gas constant of air, and R is taken as 287 J / (kg·K). ; in, MFR Mass flow rate ratio, Mainstream traffic; ; The minimum radius of the cold air inlet is used to determine the width w of the slot.

[0029] The angle of the cold air jet in the slot has almost no effect on the cooling effect of the end wall surface after the slot within a certain range. In this embodiment, in step 4, the angle value α of the cold air jet in the slot is given, and the angle range is 30°≤α≤60°.

[0030] Seam height This will significantly affect the outlet film cooling efficiency and film extension, mainly due to the gap height. The smaller the value, the greater the outflow velocity of the film cooling system at this point, thus resisting the lateral pressure gradient within the blade channel. This allows the film cooling system at the slot outlet to be evenly distributed, maintaining a high level of film cooling efficiency; while the slot height... The smaller the value, the greater the flow loss of airflow inside the slot, and the lower the flow coefficient. In this embodiment, in step 4, the height of the slot is... Treating the slot as a concentric annular joint, the flow coefficient of the concentric annular joint is... , ; ; ; in, The dynamic viscosity coefficient of cold air. Cold air inlet speed, Inlet Reynolds number, Cold air density, The flow area of ​​the diversion channel; The inner radius of the deflector is [value]. The radial height of the end wall. like If the value is ≥0.7, the airflow loss inside the groove is considered small, given the height of the groove. initial value To meet cooling requirements; if Then increase the height of the groove. The value, until ≥0.7.

[0031] After being guided by the guide vane, the cold air forms an air film on the blade endwall, enhancing convective heat transfer and providing thermal protection to a portion of the endwall. As the cold air flows downstream, it mixes with the mainstream airflow, and the insulating effect of the air film gradually weakens. With the decrease in the distance X between the guide vane and the blade, the rate of decrease in the air film cooling efficiency along the flow direction significantly decreases. In this embodiment, in step 4, the distance X between the cold air outlet and the blade... initial value The distance between the cool air outlet and the blades is determined by the engine turbine structure layout. The range of values ​​is .

[0032] In this embodiment, in step 5, since step 3 provides the initial value of the flow inlet, step 4 determines the slot cool gas jet inclination angle α, step 6 provides the initial value of the slot height δ, and step 7 provides the initial value of the distance X between the slot cool gas outlet and the blade, and based on the temperature and pressure distribution and cool gas input parameters of the leading edge side provided in step 1, numerical calculations are performed on the model of the turbine guide vane leading edge to obtain the average wall temperature of the leading edge endwall. The simulated average cooling effect at the leading edge of the end region is , ; Let a certain position of the leading edge end wall of the end region along the axial direction be... Then the wall temperature at that location is The cooling effect along the path at this location is , .

[0033] In this embodiment, in step 6, if the average cooling efficiency of the leading edge of the end region obtained in step 5 is... And the cooling effect along the way If so, the cooling structure of the leading edge slot in the end region of the turbine guide vane is considered to meet the requirements; if and / or Therefore, it is believed that the leading edge slot structure of the turbine guide vane end region cannot meet the cooling efficiency requirements, and the height of the slot should be reduced. Simultaneously satisfy The requirement of ≥0.7 is met, and the distance between the air outlet and the blades is reduced. The value is taken until the average cooling effect. And the cooling effect along the way .

[0034] In this embodiment, in step 6, if the height of the groove is reduced... Until =0.7, and the distance between the air outlet and the blades The value has been reduced to ,and and / or If the groove structure at the leading edge of the turbine guide vane is considered optimal, then the mass flow ratio can be increased by increasing the groove width w. MFR until the average cooling effect And the cooling effect along the way The advantage of adjusting the gap width w is that the solution is simple and easy to implement, but the adjustment range is limited by the overall layout of the engine.

[0035] In this embodiment, in step 6, if the height of the groove is reduced... Until =0.7, and the distance between the air outlet and the blades The value has been reduced to ,and and / or If the turbine guide vane tip leading edge slot structure is considered to be the optimal structure, then the cold air inlet pressure can be increased. and reduce the temperature of the air inlet Improve the mass flow ratio MFR until the average cooling effect And the cooling effect along the way By changing the location of the air intake, the air inlet pressure can be increased. It can improve the quality of cooling gas, increase the flow rate and speed up the flow. The speed of the air film outflow in the leading edge air film protection area L is greater, thereby resisting the lateral pressure gradient in the blade channel. This allows the air film cooling efficiency at the slot outlet to be evenly distributed at the slot outlet, thus maintaining a high level of air film cooling efficiency.

[0036] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for designing a slotted cooling system for the leading edge of a turbine guide vane, characterized in that, Includes the following steps: Step 1: Determine the input calculation boundary and provide the cold air parameters and combustion gas parameters of the leading edge of the turbine guide vane; Step 2: Calculate the cooling effect requirement of the leading edge film protection region L of the turbine guide vane tip area. The cooling effect requirement includes the average cooling effect requirement. and minimum cooling efficiency requirements ; Step 3: Calculate the initial value of the required cooling airflow to the blade endwall. The width w of the groove is obtained by converting the cold air flow rate. Step 4: Provide the jet angle α of the cold air from the slot and the height of the slot. Distance between slotted air outlet and blade ; Step 5: Calculate the simulated cooling effect at the leading edge of the end region. The simulated cooling effect includes the simulated average cooling effect. and cooling effect along the way ; Step 6: Determine if the simulated cooling effect meets the cooling requirement. If the simulated cooling effect obtained in Step 5 meets the cooling requirement, proceed to Step 7; if the simulated cooling effect does not meet the cooling requirement, reduce the height of the groove. and the distance between the air outlet and the blades Until the simulated cooling effect meets the cooling requirement; if the height of the groove Distance between the slotted air outlet and the blade If the structure is already optimal but the simulated cooling effect still does not meet the cooling effect requirements, adjust the cooling air parameters, the width w of the slot, or the mass flow rate ratio (MFR) until the simulated cooling effect meets the cooling effect requirements. Step 7: Output the final parameters that meet the cooling efficiency requirements. The final parameters include the final jet angle α of the cold air in the slot and the final height of the slot. The final width of the groove The final value of the distance between the coolant outlet and the blades. , final inlet pressure of cold air and the final inlet temperature of the air conditioner .

2. The slotted cooling design method for the leading edge of the turbine guide vane end region as described in claim 1, characterized in that, In step 1, the cold air parameters include the static pressure at the inlet of the end zone leading edge slot. The temperature of the cold air in the leading edge slot of the end area Gas parameters include mainstream gas flow rate Gas side pressure at the root or tip of the turbine guide vane inlet Gas side temperature .

3. The slotted cooling design method for the leading edge of the turbine guide vane end region as described in claim 2, characterized in that, In step 2, the average operating temperature limit value of the turbine guide vane is... T av The average cooling demand of the leading edge region L is , ; The maximum operating temperature limit for turbine guide vanes is [value missing]. The minimum cooling efficiency requirement for the leading edge region L is , .

4. The slotted cooling design method for the leading edge of the turbine guide vane end region as described in claim 3, characterized in that, ； ； ； Where k is the isentropic exponent of air, and R is the gas constant of air. MFR Mass flow rate ratio, The flow area of ​​the slot. Determine the width w of the slot to be the minimum radius of the cold air inlet.

5. The slotted cooling design method for the leading edge of the turbine guide vane end region as described in claim 4, characterized in that, In step 4, the tilt angle value α of the cold air jet in the slot is given, and the angle range is 30°≤α≤60°.

6. The slotted cooling design method for the leading edge of the turbine guide vane end region as described in claim 5, characterized in that, In step 4, the height of the groove is Treating the slot as a concentric annular joint, the flow coefficient of the concentric annular joint is... , ； ； ； in, The dynamic viscosity coefficient of cold air. Cold air inlet speed, Inlet Reynolds number, Cold air density, The flow area of ​​the diversion channel. The inner radius of the deflector is [value]. The radial height of the end wall; like If the value is ≥0.7, the airflow loss inside the groove is considered small, given the height of the groove. initial value To meet cooling requirements; if Then increase the height of the groove. The value, until ≥0.

7.

7. The slotted cooling design method for the leading edge of the turbine guide vane end region as described in claim 6, characterized in that, In step 4, the distance between the cold air outlet and the blade initial value The distance between the cool air outlet and the blades is determined by the engine turbine structure layout. The range of values ​​is .

8. The slotted cooling design method for the leading edge of the turbine guide vane end region as described in claim 7, characterized in that, In step 5, the average surface temperature of the endwall of the turbine guide vane leading edge is obtained by numerical calculation of the model. The simulated average cooling effect at the leading edge of the end region is , ; Let a certain position of the leading edge end wall of the end region along the axial direction be... Then the wall temperature at that location is The cooling effect along the path at this location is , .

9. The slotted cooling design method for the leading edge of the turbine guide vane end region as described in claim 8, characterized in that, In step 6, if the average cooling efficiency of the leading edge of the end region obtained in step 5 is... And the cooling effect along the way If so, the cooling structure of the leading edge slot in the end region of the turbine guide vane is considered to meet the requirements; if and / or Therefore, it is believed that the leading edge slot structure of the turbine guide vane end region cannot meet the cooling requirements, and the height of the slot should be reduced. Simultaneously satisfy ≥ The requirement of 0.7 was met, and the distance between the air outlet and the blades was reduced. The value is taken until the average cooling effect. And the cooling effect along the way .

10. The slotted cooling design method for the leading edge of the turbine guide vane end region as described in claim 9, characterized in that, In step 6, if the height of the groove is reduced... Until =0.7, and the distance between the air outlet and the blades The value has been reduced to ,and and / or This increases the width w of the groove, thereby improving the mass flow rate ratio. MFR until the average cooling effect And the cooling effect along the way ; or, If the height of the groove is reduced Until =0.7, and the distance between the air outlet and the blades The value has been reduced to ,and and / or This increases the pressure at the air inlet. and reduce the temperature of the air inlet Improve the mass flow ratio MFR until the average cooling effect And the cooling effect along the way .

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