Design method for cooling structure of double-row circular micro-tube array on turbine guide vane edge plate

Abstract

The present invention provides a method for designing a double-row circular micro-tube array cooling structure of a turbine guide vane edge plate. By designing a high-pressure turbine guide vane blade cooling structure, the position of the high-pressure turbine guide vane edge plate to be enhanced is determined. Given the parameters of the double-row micro-tube array cooling structure of the high-pressure turbine guide vane edge plate, a three-dimensional model of the high-pressure turbine guide vane with a micro-tube array cooling structure with double rows of staggered arrangements is constructed. A three-dimensional fluid-thermal coupling calculation model for the micro-tube array cooling of the high-pressure turbine guide vane edge plate is established, and the full three-dimensional fluid-thermal coupling calculation of the high-pressure turbine guide vane edge plate is performed; the full three-dimensional fluid-thermal coupling calculation of the high-pressure turbine guide vane blade body and the edge plate is performed. If the temperature parameters of the turbine guide vane meet the predetermined temperature standard, the design is completed. The technical solution of the present invention can solve the problem that the blade body temperature distribution of the high-pressure turbine guide vane blade of a gas turbine is uneven due to the limitation of the structural size space and the amount of cooling air used, and the cooling air is difficult to cover, resulting in ablation of the blade edge plate, causing the blade to fail and fail to work.

Description

Technical Field

[0001] The invention belongs to the technical field of gas turbine design, and in particular relates to a design method for a double-row circular micro-tube array cooling structure of a turbine guide vane edge plate. Background Art

[0002] With the continuous improvement of gas turbine performance indicators and the continuous expansion of their operating boundaries, the turbine inlet temperature continues to increase, which puts higher requirements on the temperature resistance grade of turbine blade materials and cooling structure design for long-term continuous operation under high load conditions.

[0003] During the operation of existing engines and the development of new engines, there are areas in turbine blades that are difficult to cool, especially the end walls and blade tops with relatively small dimensions and relatively complex flows, which are prone to forming cooling "blind spots" or even "dead spots". The metal temperatures at these locations are close to the heat resistance limit of the blade alloy. Similar phenomena have also been reported by foreign researchers when conducting gas turbine design and testing. The surface temperature distribution of turbine blades obtained by transient liquid crystal measurement and numerical calculation by Siemens and other companies shows that obvious local high-temperature areas appear at the blade body, end wall and blade top. These local high-temperature areas that are difficult to cool can easily cause local ablation of turbine blades, which brings great difficulties to the cooling design of turbine blades. In addition, with the expansion of the engine use environment and the improvement of performance requirements, the turbine inlet temperature continues to increase, further increasing the design difficulty of the turbine blade cooling structure.

[0004] Therefore, when traditional large-scale cooling structures are unable to meet the cooling needs of "blind spots" and "dead spots", innovating and developing efficient cooling structures for turbine blades can further improve the cooling effect without increasing the amount of cold air used, which has important scientific significance and practical value for the development of advanced high-performance gas turbine engines. Summary of the invention

[0005] An embodiment of the present invention provides a method for designing a double-row circular micro-tube array cooling structure for a turbine guide vane edge plate, which can solve the problem that the blade body of a high-pressure turbine guide vane of a gas turbine is limited by the structural size space and the amount of cooling air used, resulting in uneven temperature distribution on the blade body, difficulty in cooling air coverage, resulting in erosion of the blade edge plate, and causing the blade to fail and unable to work.

[0006] In an embodiment of the present invention, a method for designing a double-row circular micro-tube array cooling structure of a turbine guide vane edge plate is provided, comprising:

[0007] S101. According to the appearance of the turbine guide vane blade, determine the cooling structure of the turbine guide vane blade without the micro-tube array cooling channel, perform full three-dimensional fluid-heat coupling calculation and analysis on the turbine guide vane, determine the temperature field distribution and data information of the guide vane edge plate, obtain the convective heat transfer coefficient of the high-pressure turbine guide vane edge plate, and obtain the temperature field distribution and data information of the high-pressure turbine guide vane blade;

[0008] S102, determining the position of the high temperature area of ​​the turbine guide vane edge plate where the enhanced cooling structure is to be arranged;

[0009] S103, according to the surface structure of the guide vane edge plate, combined with the structural dimension parameters of the turbine guide vane edge plate including at least the thickness, width and length of the guide vane edge plate, the cooling structural parameters of the upper and lower rows of circular micro-tube arrays of the turbine guide vane edge plate are given;

[0010] S104, constructing an overall three-dimensional model of a high-pressure turbine guide vane with a micro-tube array cooling structure having a double-row staggered arrangement on the guide vane edge plate, and establishing a three-dimensional fluid-thermal coupling calculation model for the micro-tube array cooling of the high-pressure turbine guide vane edge plate;

[0011] S105, based on the three-dimensional model of the turbine guide vane edge plate, divide the fluid domain and solid domain grids required for the full three-dimensional calculation, carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane edge plate, and obtain the temperature field distribution and temperature data of the turbine guide vane edge plate. If the temperature field parameters of the turbine guide vane edge plate meet the first predetermined temperature standard, the design process ends; otherwise, repeat S101 to S105 until the temperature parameters of the turbine guide vane edge plate reach the first predetermined temperature standard;

[0012] S106. Perform full three-dimensional heat-flow coupling calculation and analysis on the turbine guide vane body and edge plate as a whole, and obtain temperature field parameters and data information of the turbine guide vane including the blade body and edge plate after adding a micro-tube array cooling structure with a double-row staggered arrangement; if the temperature field parameters of the turbine guide vane meet the first predetermined temperature standard, the design process ends; otherwise, repeat S101 to S106 until the temperature parameters of the turbine guide vane reach the first predetermined temperature standard.

[0013] Further, according to the surface structure of the guide vane edge plate, combined with the structural dimension parameters of the turbine guide vane edge plate at least including the thickness, width and length of the guide vane edge plate, the cooling structural parameters of the upper and lower rows of circular micro-tube arrays of the turbine guide vane edge plate are given, including:

[0014] Based on the specific position of the turbine guide vane edge plate that needs enhanced cooling, according to the structural characteristics of the guide vane edge plate surface that is approximately parallelogram, combined with structural dimension parameters including at least the thickness, width and length of the turbine guide vane edge plate, the cooling structural parameters of the upper and lower rows of circular micro-tube arrays are given;

[0015] Among them, the cooling structure parameters of the upper and lower rows of circular micro-tube arrays include: the distance from the position of the upper and lower rows of micro-circular tubes set along the thickness direction of the edge plate to the flow surface of the edge plate, the distance from the position of the upper and lower rows of micro-circular tubes set along the width direction of the edge plate to the side of the edge plate, the number of upper and lower rows of micro-circular tubes set along the width direction of the edge plate, and the diameter of each micro-tube in the upper and lower rows.

[0016] Furthermore, based on the full three-dimensional fluid-thermal coupling calculation and analysis of the high-pressure turbine guide vane edge plate, the fluid domain and solid domain meshes required for the full three-dimensional calculation are divided to obtain the temperature field distribution and temperature data of the guide vane edge plate, including:

[0017] The three-dimensional heat-flow coupling calculation model of the micro-tube array cooling of the turbine guide vane edge plate is imported into the meshing program, and the fluid domain and solid domain meshes required for the full three-dimensional calculation are divided. According to the temperature and convection heat transfer coefficient of the turbine guide vane edge plate and the blade body, as well as the temperature and pressure boundary conditions of the cooling air inlet and outlet, the full three-dimensional heat-flow coupling calculation and analysis program is used to carry out the full three-dimensional heat-flow coupling calculation and analysis of the turbine guide vane edge plate, and the temperature field distribution and data of the turbine guide vane edge plate are obtained.

[0018] If the temperature parameters of the turbine guide vane edge plate meet the second predetermined temperature standard, execute the next step; otherwise, adjust the cooling structure parameters of the horizontal single-row circular micro-tube array by at least reducing the distance from the center line of the upper and lower rows of tubes to the flow surface of the edge plate, increasing the number of tubes in the two micro-tube rows, increasing the tube diameters of the two micro-tube rows, and reducing the distance between the upper and lower rows of tubes, and repeat S102 to S105 until the temperature parameters of the turbine guide vane edge plate reach the second predetermined temperature standard.

[0019] Furthermore, the design method comprises:

[0020] If the maximum temperature of the turbine guide vane edge plate is higher than the temperature resistance grade of the metal material used, then the second predetermined temperature standard is: the maximum temperature of the turbine guide vane edge plate is lower than the temperature resistance grade of the metal material used;

[0021] If the maximum temperature of the turbine guide vane edge plate is lower than the temperature resistance grade of the metal material used, the predetermined temperature standard is: the maximum temperature of the turbine guide vane edge plate is reduced by not less than 10°C.

[0022] Furthermore, the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane blade body and edge plate is carried out to obtain the temperature field parameters and data information of the turbine guide vane including the blade body and edge plate after adding the micro-tube array cooling structure with double-row staggered arrangement, including:

[0023] Based on the inlet and outlet boundary conditions of the turbine guide vane, the overall three-dimensional model of the high-pressure turbine guide vane with a turbine guide vane edge plate and a double-row staggered micro-tube array cooling structure is imported into the meshing program to divide the fluid domain and solid domain meshes required for the full three-dimensional calculation. The full three-dimensional fluid-thermal coupling calculation and analysis program is used to carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane, and the temperature field distribution parameters and data information of the high-pressure turbine guide vane including the blade body and edge plate after adding the double-row micro-tube array cooling structure are obtained.

[0024] Furthermore, a full three-dimensional fluid-thermal coupling calculation and analysis is performed on the turbine guide vanes, including:

[0025] The constructed three-dimensional model of the guide vane is imported into the meshing program to divide the fluid domain and solid domain meshes required for the full three-dimensional calculation. The full three-dimensional fluid-thermal coupling calculation and analysis program is used to carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane, and the temperature field distribution and data of the turbine guide vane edge plate are obtained as a basis for subsequent analysis and comparison after adopting the micro-tube array cooling design;

[0026] The convective heat transfer coefficient of the turbine guide vane edge plate is obtained as the boundary condition for subsequent analysis, and the blade temperature field distribution and data of the turbine guide vane are obtained.

[0027] Furthermore, the circular micro-tube array cooling structure has a diameter of 0.2 mm to 0.6 mm. The micro-tube array structure can increase the heat exchange area of ​​the cooling channel and increase the convection heat transfer coefficient.

[0028] Furthermore, the method comprises:

[0029] The turbine guide vane edge plate is cooled by a double row of circular fine tube arrays to block the heat transfer of high-temperature combustion gas in the guide vane blade grid channel to the outside of the edge plate; by reducing the diameter of the circular tubes of the fine tube array, the cooling air is delivered to any position of the turbine guide vane edge plate, thereby achieving precise customized delivery of the edge plate cooling needs and targeted cooling of the high-temperature area of ​​the edge plate.

[0030] Furthermore, UG NX software is used as the three-dimensional modeling software for the computational domain, CFX and Fluent software are used as the full three-dimensional fluid-thermal coupling calculation and analysis software, and ICEM CFD software is used for meshing.

[0031] The beneficial effects brought by the present invention are as follows:

[0032] It can be seen from the above scheme that the embodiment of the present invention provides a design method for the cooling structure of the double-row circular micro-tube array of the turbine guide vane edge plate. By designing the cooling structure of the high-pressure turbine guide vane blade body, the high-pressure turbine guide vane is subjected to full three-dimensional fluid-heat coupling calculation and analysis, and the position of the high-pressure turbine guide vane edge plate that needs enhanced cooling is determined. Given the parameters of the double-row micro-tube array cooling structure of the high-pressure turbine guide vane edge plate, an overall three-dimensional model of the high-pressure turbine guide vane with a micro-tube array cooling structure with double rows of staggered arrangements is constructed. A three-dimensional fluid-heat coupling calculation model for the micro-tube array cooling of the high-pressure turbine guide vane edge plate is established, and the full three-dimensional fluid-heat coupling calculation and analysis of the high-pressure turbine guide vane edge plate and the full three-dimensional fluid-heat coupling calculation and analysis of the high-pressure turbine guide vane blade body and edge plate as a whole are performed. The technical scheme of the present invention can solve the problem that the high-pressure turbine guide vane blade body of the gas turbine is limited by the structural size space and the amount of cooling air, resulting in uneven temperature distribution of the blade body, and the cooling air is difficult to cover, resulting in ablation of the blade edge plate, causing the blade to fail and fail to work. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 A flow chart showing a method for designing a double-row circular micro-tube array cooling structure for a turbine guide vane edge plate according to an embodiment of the present invention. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution in the embodiment of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiment of the present invention. Obviously, the described embodiment is a part of the embodiment of the present invention, not all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] In an embodiment of the present invention, a method for designing a cooling structure of a double-row circular micro-tube array of a turbine guide vane edge plate can solve the problem that the high-pressure turbine guide vane edge plate of a gas turbine is affected by the lateral secondary flow in the end area and is limited by the structural size space, making it difficult for cooling air to cover it, resulting in ablation of the blade edge plate. Further, a method for designing a cooling structure of a high-pressure turbine guide vane edge plate with a lateral double-row circular micro-tube array suitable for a gas turbine high-pressure turbine guide vane and having excellent cooling and heat insulation effects is provided, thereby avoiding the problem of blade over-temperature operation, which causes the blade to fail and be unable to work.

[0036] like Figure 1 As shown, Figure 1 A flow chart showing a method for designing a double-row circular micro-tube array cooling structure for a turbine guide vane edge plate according to an embodiment of the present invention.

[0037] In the figure, a design method for a double-row circular micro-tube array cooling structure of a turbine guide vane edge plate includes:

[0038] S101. According to the appearance of the turbine guide vane, determine the cooling structure of the turbine guide vane without micro-tube array cooling channels, perform full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane, determine the temperature field distribution and data information of the guide vane edge plate, obtain the convective heat transfer coefficient of the high-pressure turbine guide vane edge plate, and obtain the temperature field distribution and data information of the high-pressure turbine guide vane blade.

[0039] In an embodiment of the present invention, based on the guide vane shape obtained by the turbine aerodynamic design, the cooling structure design of the turbine guide vane blade body is carried out, and the cooling structure design such as film cooling is not carried out on the guide vane edge plate for the time being, so as to obtain a three-dimensional model of a high-pressure turbine guide vane with a cooling structure.

[0040] A full three-dimensional fluid-thermal coupling calculation and analysis is performed on the turbine guide vanes. According to the inlet and outlet boundary conditions of the turbine guide vanes, the constructed three-dimensional guide vane model is imported into the meshing program to divide the fluid domain and solid domain meshes required for the full three-dimensional calculation. Then, the full three-dimensional fluid-thermal coupling calculation and analysis program is used to carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vanes, and the temperature field distribution and data of the high-pressure turbine guide vane edge plate are obtained as a basis for subsequent analysis and comparison after adopting the double-row micro-tube array cooling design. The convective heat transfer coefficient of the high-pressure turbine guide vane edge plate is obtained as the boundary condition for subsequent analysis, and the blade temperature field distribution and data of the high-pressure turbine guide vane are obtained.

[0041] If the temperature parameter of the turbine guide vane blade body meets the predetermined temperature standard, that is, the maximum temperature of the turbine guide vane blade body is lower than the temperature resistance grade of the metal material used, the next step is executed; if it does not meet the predetermined standard, the above steps are repeated until the temperature parameter of the guide vane blade body reaches the predetermined standard.

[0042] S102, determining the position of the high temperature area of ​​the turbine guide vane edge plate where the enhanced cooling structure is to be arranged.

[0043] In the embodiment of the present invention, the position of the turbine guide vane edge plate that needs enhanced cooling is determined. According to the temperature field distribution and data of the guide vane edge plate, the position of the high temperature area of ​​the turbine guide vane edge plate is judged, that is, the specific position of the turbine guide vane edge plate that needs enhanced cooling, and the micro-tube array cooling structure will be arranged at these high temperature positions later.

[0044] S103. According to the surface structure of the guide vane edge plate and in combination with the structural dimension parameters of the turbine guide vane edge plate including at least the thickness, width and length of the guide vane edge plate, cooling structural parameters of the upper and lower rows of circular micro-tube arrays of the turbine guide vane edge plate are given.

[0045] In an embodiment of the present invention, based on the specific position of the turbine guide vane blade body that requires enhanced cooling, according to the structural characteristics of the guide vane edge plate surface that is approximately a parallelogram, combined with structural dimensional parameters including at least the thickness, width, and length of the turbine guide vane edge plate, the cooling structural parameters of the lateral single-row circular micro-tube array are given.

[0046] Among them, the cooling structure parameters of the upper and lower rows of circular micro-tube arrays include: the distance from the position of the upper and lower rows of micro-circular tubes set along the thickness direction of the edge plate to the flow surface of the edge plate, the distance from the position of the upper and lower rows of micro-circular tubes set along the width direction of the edge plate to the side of the edge plate, the number of upper and lower rows of micro-circular tubes set along the width direction of the edge plate, and the diameter of each micro-tube in the upper and lower rows.

[0047] In the embodiment of the present invention, for the upper row of tubes, the following include: the distance H1 from the position of the micro-circular tubes arranged along the thickness direction of the edge plate to the flow surface of the edge plate, the distance W from the position of the micro-circular tubes arranged along the width direction of the edge plate to the side of the edge plate, the number N or the spacing L of the micro-circular tubes arranged along the width direction of the edge plate, the tube diameter φ of each micro-tube, and the path of each micro-tube arranged along the length direction of the edge plate. For the lower row of tubes, the following include: the distance H2 from the position of the micro-circular tubes arranged along the thickness direction of the edge plate to the flow surface of the edge plate, the distance Q from the position of the micro-circular tubes arranged along the width direction of the edge plate to the side of the edge plate, the number S or the spacing T of the micro-circular tubes arranged along the width direction of the edge plate, the tube diameter ψ of each micro-tube, and the path of each micro-tube arranged along the length direction of the edge plate.

[0048] S104. Construct an overall three-dimensional model of a high-pressure turbine guide vane with a micro-tube array cooling structure having a guide vane edge plate with double rows of staggered arrangements, and establish a three-dimensional fluid-thermal coupling calculation model for the micro-tube array cooling of a high-pressure turbine guide vane edge plate.

[0049] In an embodiment of the present invention, a three-dimensional model of a guide vane with a cooling structure utilizes given transverse double-row circular micro-tube array cooling structure parameters to set two rows of micro-circular cross-section tube rows whose center lines are parallel to the side wall of the edge plate on the high-pressure turbine guide vane edge plate, thereby constructing a three-dimensional model of a high-pressure turbine guide vane in which the edge plate has a double-row circular micro-tube array cooling structure that is staggered in a transverse manner, and the blade body has a cooling structure, and a hollow micro-connecting pipe is set at the blade cavity position to connect the cooling channel front to back.

[0050] Based on the turbine guide vane three-dimensional model, the guide vane blade cooling structure is ignored, only the guide vane blade shape is used, and only the high-pressure turbine guide vane edge plate model with a double-row circular micro-tube array cooling structure arranged laterally staggered is extracted.

[0051] S105. Based on the three-dimensional model of the turbine guide vane edge plate, divide the fluid domain and solid domain grids required for the full three-dimensional calculation, carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane edge plate, and obtain the temperature field distribution and temperature data of the turbine guide vane edge plate. If the temperature field parameters of the turbine guide vane edge plate meet the first predetermined temperature standard, the design process ends; otherwise, repeat S101 to S105 until the temperature parameters of the turbine guide vane edge plate reach the first predetermined temperature standard.

[0052] In an embodiment of the present invention, the constructed three-dimensional fluid-thermal coupling calculation model for cooling of the micro-tube array of the high-pressure turbine guide vane edge plate is imported into the meshing program, and the fluid domain and solid domain meshes required for the full three-dimensional calculation are divided. According to the temperature and convective heat transfer coefficient of the high-pressure turbine guide vane edge plate and the blade body obtained in step 2, as well as the inlet and outlet temperature and pressure boundary conditions of the cooling air, a full three-dimensional fluid-thermal coupling calculation and analysis program is used to carry out a full three-dimensional fluid-thermal coupling calculation and analysis of the high-pressure turbine guide vane edge plate, and obtain the temperature field distribution and data of the high-pressure turbine guide vane edge plate.

[0053] If the temperature parameters of the turbine guide vane edge plate meet the second predetermined temperature standard, execute the next step; otherwise, adjust the cooling structure parameters of the horizontal single-row circular micro-tube array by at least reducing the distance from the center line of the upper and lower rows of tubes to the flow surface of the edge plate, increasing the number of tubes in the two micro-tube rows, increasing the tube diameters of the two micro-tube rows, and reducing the distance between the upper and lower rows of tubes, and repeat S102 to S105 until the temperature parameters of the turbine guide vane edge plate reach the second predetermined temperature standard.

[0054] In the embodiment of the present invention, if the maximum temperature of the turbine guide vane edge plate is higher than the temperature resistance grade of the metal material used, then the second predetermined temperature standard is: the maximum temperature of the turbine guide vane edge plate is lower than the temperature resistance grade of the metal material used;

[0055] If the maximum temperature of the turbine guide vane edge plate is lower than the temperature resistance grade of the metal material used, the predetermined temperature standard is: the maximum temperature of the turbine guide vane edge plate is reduced by not less than 10°C.

[0056] S106. Perform full three-dimensional heat-flow coupling calculation and analysis on the turbine guide vane body and edge plate as a whole to obtain the temperature field parameters and data information of the turbine guide vane including the blade body and edge plate after adding the micro-tube array cooling structure; if the temperature field parameters of the turbine guide vane meet the first predetermined temperature standard, the design process ends; otherwise, repeat S101 to S106 until the temperature parameters of the turbine guide vane reach the first predetermined temperature standard.

[0057] In an embodiment of the present invention, the same high-pressure turbine guide vane inlet and outlet boundary conditions are adopted, and the constructed edge plate with a double-row staggered micro-tube array cooling structure of the high-pressure turbine guide vane overall three-dimensional model is imported into the meshing program, and the fluid domain and solid domain meshes required for the full three-dimensional calculation are divided. Then, the full three-dimensional fluid-thermal coupling calculation and analysis program is used to carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the high-pressure turbine guide vane, and the temperature field distribution and data of the high-pressure turbine guide vane (including the blade body and edge plate) after adding the double-row micro-tube array cooling structure are obtained.

[0058] In the embodiment of the present invention, the diameter of the cooling tube of the circular micro-tube array cooling structure is usually between 0.2mm and 0.6mm. The smaller diameter tube array is conducive to doubling the heat exchange area of ​​the cooling channel and doubling the convective heat transfer coefficient, thereby realizing super cooling of the edge plate. Obviously, through the micro-tube array, not only can the full coverage of the high-pressure turbine guide vane edge plate cooling be achieved, but also the edge plate cooling requirements can be fully met. Therefore, the edge plate air film cooling can be cancelled. The traditional edge plate air film cooling is affected by the lateral secondary flow in the end area and the space structure is limited. The problem that the air film is difficult to cover the cooling "dead zone" will no longer exist, and the cooling and cooling requirements of the high-pressure turbine guide vane edge plate of the gas turbine can be more easily met.

[0059] In another embodiment of the present invention, the high-pressure turbine guide vane edge plate is cooled by a transverse double-row circular micro-tube array. The cooling air can be delivered to any position of the guide vane edge plate by reducing the diameter of the circular tubes of the micro-tube array (to a minimum of 0.2 mm), thereby achieving precise customized delivery of the edge plate cooling needs and specifically cooling the high-temperature area of ​​the edge plate.

[0060] The high-pressure turbine guide vane edge plate is cooled by a double-row circular micro-tube array in a transverse direction and adopts a double-row structure, which completely blocks the heat transfer from the high-temperature combustion gas in the guide vane cascade channel to the outside of the edge plate, further reducing the temperature of the outside of the edge plate. On the one hand, it reduces the stress of the edge plate, and on the other hand, it reduces the temperature of the air used for cooling the guide vane blade body, which helps to improve the cooling effect of the blade body, reduce the blade body temperature, and increase the blade body life.

[0061] According to the technical solution of the present invention, the high-pressure turbine guide vane edge plate is cooled by a double-row circular micro-tube array in a transverse direction, and the interior of the guide vane edge plate is a hollow structure, which can reduce the weight of the guide vane by 1%.

[0062] In another embodiment of the present invention, the computational domain three-dimensional modeling software adopts UG NX software, the full three-dimensional fluid-heat coupling calculation and analysis software adopts CFX and Fluent software, and the meshing adopts ICEM CFD software.

[0063] In an embodiment of the present invention, a double-row circular micro-tube array cooling design method for a high-pressure turbine guide vane edge plate is universal and is not only limited to the design of high-pressure turbine guide vanes for gas turbines, but is also applicable to the design of high-pressure turbine guide vanes for aircraft engines.

[0064] In another embodiment of the present invention, a double-row circular micro-tube array cooling design method for a high-pressure turbine guide vane edge plate, based on full utilization of the conventional high-pressure turbine guide vane full three-dimensional fluid-thermal coupling calculation method, according to the structural characteristics of the high-pressure turbine guide vane edge plate of the gas turbine, focuses on the high-temperature zone of the high-pressure turbine guide vane edge plate, reorganizes the guide vane edge plate cooling structure design and temperature field calculation process, and proposes a transverse double-row circular micro-tube array cooling design method suitable for the high-pressure turbine guide vane edge plate of the gas turbine, obtains an efficient cooling structure design method for the high-pressure turbine guide vane edge plate, and solves the problem that the high-pressure turbine guide vane edge plate of the gas turbine is difficult to cool.

[0065] In the embodiment of the present invention, the heat exchange area and convection heat transfer coefficient of the cooling channel are multiplied by the micro-tube row with a smaller diameter (0.2mm-0.6mm), thereby realizing super cooling of the edge plate. Not only can the full coverage of the cooling of the high-pressure turbine guide vane edge plate be achieved, but also the edge plate cooling requirements can be fully met. Therefore, the edge plate air film cooling can be eliminated, effectively solving the problem of cooling "dead zone" that is difficult to be covered by the air film due to the influence of the lateral secondary flow in the end area near the edge plate and the limitation of the spatial structure of the traditional air film cooling structure, thereby effectively solving the problem of blade edge plate ablation.

[0066] In an embodiment of the present invention, cooling air is delivered to any position of the guide vane edge plate through a micro-tube array, thereby achieving precise customized delivery according to the cooling needs of the edge plate, thereby achieving targeted cooling of the high-temperature area of ​​the edge plate and meeting the local cooling and temperature reduction needs of the guide vane edge plate.

[0067] The present invention proposes a method for designing a double-row circular micro-tube array cooling structure for a turbine guide vane edge plate. The double-row structure is adopted to completely block the heat transfer from the high-temperature combustion gas in the guide vane cascade channel to the outside of the edge plate, thereby reducing the temperature of the outside of the edge plate, which is beneficial to reducing the stress of the edge plate, reducing the cooling air temperature of the guide vane blade body, improving the cooling effect of the blade body, reducing the blade body temperature, and increasing the blade body life.

[0068] In an embodiment of the present invention, a method for designing a double-row circular micro-tube array cooling structure for a turbine guide vane edge plate is provided, which gives full play to the better cooling effect of the micro-tube array and cancels the air film hole cooling structure of the guide vane edge plate, thereby reducing the influence of the air film cooling of the edge plate on the mainstream, which is beneficial to reducing the cold and hot mixing loss of the turbine guide vane edge plate and improving the turbine efficiency. The designed guide vane edge plate cooling structure can directly discharge the cooling air through the rear side of the guide vane edge plate, which is not only beneficial to the cooling of the downstream moving blades, but also beneficial to the sealing between the guide vanes and the moving blade edge plates, avoiding the "invasion" of the gas into the high-pressure turbine wheel cavity. The designed guide vane edge plate has a hollow structure inside, which is beneficial to reducing the weight of the guide vanes and improving the power-to-weight ratio of the engine.

[0069] The above are preferred embodiments of the present invention. It should be pointed out that, for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as within the scope of protection of the present invention.

Claims

1. A method for designing a double-row circular micro-tube array cooling structure for a turbine guide vane edge plate, characterized in that: The design method comprises: S101. According to the appearance of the turbine guide vane blade, determine the cooling structure of the turbine guide vane blade without the micro-tube array cooling channel, perform full three-dimensional fluid-heat coupling calculation and analysis on the turbine guide vane, determine the temperature field distribution and data information of the guide vane edge plate, obtain the convective heat transfer coefficient of the high-pressure turbine guide vane edge plate, and obtain the temperature field distribution and data information of the high-pressure turbine guide vane blade; S102, determining the position of the high temperature area of ​​the turbine guide vane edge plate where the enhanced cooling structure is to be arranged; S103, according to the surface structure of the guide vane edge plate, combined with the structural dimension parameters of the turbine guide vane edge plate including at least the thickness, width and length of the guide vane edge plate, the cooling structural parameters of the upper and lower rows of circular micro-tube arrays of the turbine guide vane edge plate are given; S104, constructing an overall three-dimensional model of a high-pressure turbine guide vane with a micro-tube array cooling structure having a double-row staggered arrangement on the guide vane edge plate, and establishing a three-dimensional fluid-thermal coupling calculation model for the micro-tube array cooling of the high-pressure turbine guide vane edge plate; S105, based on the three-dimensional model of the turbine guide vane edge plate, divide the fluid domain and solid domain grids required for the full three-dimensional calculation, carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane edge plate, and obtain the temperature field distribution and temperature data of the turbine guide vane edge plate. If the temperature field parameters of the turbine guide vane edge plate meet the first predetermined temperature standard, the design process ends; otherwise, repeat S101 to S105 until the temperature parameters of the turbine guide vane edge plate reach the first predetermined temperature standard; S106. Perform full three-dimensional heat-flow coupling calculation and analysis on the turbine guide vane body and edge plate as a whole, and obtain temperature field parameters and data information of the turbine guide vane including the blade body and edge plate after adding a micro-tube array cooling structure with a double-row staggered arrangement; if the temperature field parameters of the turbine guide vane meet the first predetermined temperature standard, the design process ends; otherwise, repeat S101 to S106 until the temperature parameters of the turbine guide vane reach the first predetermined temperature standard.

2. The method for designing a double-row circular micro-tube array cooling structure of a turbine guide vane edge plate according to claim 1, characterized in that: According to the surface structure of the guide vane edge plate, combined with the structural dimension parameters of the turbine guide vane edge plate including at least the thickness, width and length of the guide vane edge plate, the cooling structural parameters of the upper and lower rows of circular micro-tube arrays of the turbine guide vane edge plate are given, including: Based on the specific position of the turbine guide vane edge plate that needs enhanced cooling, according to the structural characteristics of the guide vane edge plate surface that is approximately parallelogram, combined with structural dimension parameters including at least the thickness, width and length of the turbine guide vane edge plate, the cooling structural parameters of the upper and lower rows of circular micro-tube arrays are given; Among them, the cooling structure parameters of the upper and lower rows of circular micro-tube arrays include: the distance from the position of the upper and lower rows of micro-circular tubes set along the thickness direction of the edge plate to the flow surface of the edge plate, the distance from the position of the upper and lower rows of micro-circular tubes set along the width direction of the edge plate to the side of the edge plate, the number of upper and lower rows of micro-circular tubes set along the width direction of the edge plate, and the diameter of each micro-tube in the upper and lower rows.

3. The method for designing a double-row circular micro-tube array cooling structure of a turbine guide vane edge plate according to claim 1, characterized in that: Based on the three-dimensional model of the turbine guide vane edge plate, the fluid domain and solid domain meshes required for full three-dimensional calculation are divided, and the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane edge plate are carried out to obtain the temperature field distribution and temperature data of the guide vane edge plate, including: The three-dimensional heat-flow coupling calculation model of the micro-tube array cooling of the turbine guide vane edge plate is imported into the meshing program, and the fluid domain and solid domain meshes required for the full three-dimensional calculation are divided. According to the temperature and convection heat transfer coefficient of the turbine guide vane edge plate and the blade body, as well as the temperature and pressure boundary conditions of the cooling air inlet and outlet, the full three-dimensional heat-flow coupling calculation and analysis program is used to carry out the full three-dimensional heat-flow coupling calculation and analysis of the turbine guide vane edge plate, and the temperature field distribution and data of the turbine guide vane edge plate are obtained. If the temperature parameters of the turbine guide vane edge plate meet the second predetermined temperature standard, execute the next step; otherwise, adjust the cooling structure parameters of the horizontal single-row circular micro-tube array by at least reducing the distance from the center line of the upper and lower rows of tubes to the flow surface of the edge plate, increasing the number of tubes in the two micro-tube rows, increasing the tube diameters of the two micro-tube rows, and reducing the distance between the upper and lower rows of tubes, and repeat S102 to S105 until the temperature parameters of the turbine guide vane edge plate reach the second predetermined temperature standard.

4. The method for designing a double-row circular micro-tube array cooling structure of a turbine guide vane edge plate according to claim 3, characterized in that: The design method comprises: If the maximum temperature of the turbine guide vane edge plate is higher than the temperature resistance grade of the metal material used, then the second predetermined temperature standard is: the maximum temperature of the turbine guide vane edge plate is lower than the temperature resistance grade of the metal material used; If the maximum temperature of the turbine guide vane edge plate is lower than the temperature resistance grade of the metal material used, the predetermined temperature standard is: the maximum temperature of the turbine guide vane edge plate is reduced by not less than 10°C.

5. The method for designing a double-row circular micro-tube array cooling structure of a turbine guide vane edge plate according to claim 1, characterized in that: The full three-dimensional heat-flow coupling calculation and analysis of the turbine guide vane blade and edge plate is carried out to obtain the temperature field parameters and data information of the turbine guide vane including the blade body and edge plate after adding a micro-tube array cooling structure with a double-row staggered arrangement, including: Based on the inlet and outlet boundary conditions of the turbine guide vane, the overall three-dimensional model of the high-pressure turbine guide vane with a turbine guide vane edge plate and a double-row staggered micro-tube array cooling structure is imported into the meshing program to divide the fluid domain and solid domain meshes required for the full three-dimensional calculation. The full three-dimensional fluid-thermal coupling calculation and analysis program is used to carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane, and the temperature field distribution parameters and data information of the high-pressure turbine guide vane including the blade body and edge plate after adding the double-row micro-tube array cooling structure are obtained.

6. The method for designing a double-row circular micro-tube array cooling structure of a turbine guide vane edge plate according to claim 1, characterized in that: Perform full 3D fluid-thermal coupling calculation and analysis on turbine guide vanes, including: The constructed three-dimensional model of the guide vane is imported into the meshing program to divide the fluid domain and solid domain meshes required for the full three-dimensional calculation. The full three-dimensional fluid-thermal coupling calculation and analysis program is used to carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane, and the temperature field distribution and data of the turbine guide vane edge plate are obtained as a basis for subsequent analysis and comparison after adopting the micro-tube array cooling design; The convective heat transfer coefficient of the turbine guide vane edge plate is obtained as the boundary condition for subsequent analysis, and the blade temperature field distribution and data of the turbine guide vane are obtained.

7. The method for designing a double-row circular micro-tube array cooling structure for a turbine guide vane edge plate according to claim 1, characterized in that: The circular micro-tube array cooling structure is used for cooling, and the diameter of the circular tube is between 0.2 mm and 0.6 mm. The micro-tube array structure can increase the heat exchange area of ​​the cooling channel and increase the convection heat transfer coefficient.

8. The method for designing a double-row circular micro-tube array cooling structure of a turbine guide vane edge plate according to claim 1, characterized in that: The method comprises: The turbine guide vane edge plate is cooled by a double row of circular fine tube arrays to block the heat transfer of high-temperature combustion gas in the guide vane blade grid channel to the outside of the edge plate; by reducing the diameter of the circular tubes of the fine tube array, the cooling air is delivered to any position of the turbine guide vane edge plate, thereby achieving precise customized delivery of the edge plate cooling needs and targeted cooling of the high-temperature area of ​​the edge plate.

9. The method for designing a double-row circular micro-tube array cooling structure for a turbine guide vane edge plate according to claim 1, characterized in that: The 3D modeling software of the computational domain adopts UG NX software, the full 3D fluid-heat coupling calculation and analysis software adopts CFX and Fluent software, and the meshing adopts ICEM CFD software.

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