Design method for cooling structure of horizontal single-row circular micro-tube array on turbine blade edge

Abstract

The present invention provides a design method for a horizontal single-row circular micro-tube array cooling structure of a turbine moving blade edge plate. The method determines the location of the high-temperature zone where the enhanced cooling structure is to be arranged by performing a full three-dimensional fluid-heat coupling calculation and analysis on the turbine moving blade; establishes a three-dimensional fluid-heat coupling calculation model for the micro-tube array cooling of the turbine moving blade edge plate, performs a full three-dimensional fluid-heat coupling calculation and analysis on the moving blade edge plate, and obtains the temperature field distribution and temperature data of the moving blade edge plate; performs a full three-dimensional fluid-heat coupling calculation on the turbine moving blade body and edge plate as a whole, and obtains the temperature field parameters and data information of the turbine moving blade after adding the micro-tube array cooling structure. If the temperature parameters of the turbine moving blade meet the predetermined temperature standard, the design is completed. The technical solution of the present invention can solve the problem that the blade body of the high-pressure turbine moving blade of a gas turbine is limited by the structural size space and the amount of cooling air, resulting in uneven temperature distribution of the blade body, which is difficult to cover with cooling air, leading to ablation of the blade edge plate, and 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 cooling structure of a transverse single-row circular micro-tube array on a turbine blade 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 cooling structure of a transverse single-row circular micro-tube array on a turbine blade edge plate, which can solve the problem that the blade body of a high-pressure turbine blade 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 cooling structure of a turbine blade edge plate with a transverse single-row circular micro-tube array is provided, comprising:

[0007] S101. Determine the cooling structure of the turbine blade body without a micro-tube array cooling channel according to the appearance of the turbine blade body, perform full three-dimensional fluid-heat coupling calculation and analysis on the turbine blade, and determine the temperature field distribution and data information of the blade body, which will serve as a comparison basis for subsequent analysis and design using a circular micro-tube array cooling structure;

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

[0009] S103, according to the surface structure of the moving blade edge plate, combined with the dimensional parameters of the moving blade edge plate including at least the thickness, width and length of the moving blade edge plate, the cooling structure parameters of the turbine moving blade edge plate with the micro-tube array are given;

[0010] S104, constructing an overall three-dimensional model of a turbine blade with an edge plate micro-tube array cooling structure, and establishing a three-dimensional fluid-thermal coupling calculation model for turbine blade edge plate micro-tube array cooling;

[0011] S105. Based on the three-dimensional model of the turbine blade edge plate, the fluid domain and solid domain grids required for the full three-dimensional calculation are divided, and the full three-dimensional fluid-thermal coupling calculation and analysis of the blade edge plate are carried out to obtain the temperature field distribution and temperature data of the blade edge plate. If the temperature field parameters of the turbine blade edge plate meet the first predetermined temperature standard, that is, the maximum temperature T of the turbine blade edge plate Ryb,max Lower than the temperature resistance grade T of the metal material used S-M , T Ryb,max <T S-M , the design process ends; otherwise, S101 to S105 are repeated until the temperature parameter of the turbine blade edge plate reaches the first predetermined temperature standard;

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

[0013] Further, according to the surface structure of the moving blade edge plate, combined with the dimensional parameters of the moving blade edge plate including at least the thickness, width and length of the moving blade edge plate, the cooling structure parameters of the turbine moving blade edge plate with the micro-tube array are given, including:

[0014] Based on the specific position of the turbine blade body that needs enhanced cooling, according to the structural characteristics of the blade edge plate surface that is approximately parallelogram, combined with structural dimension parameters including at least the thickness, width and length of the turbine blade edge plate, the cooling structural parameters of the transverse single-row circular micro-tube array are given;

[0015] The cooling structure parameters of the horizontal single-row circular micro-tube array include: the distance H 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 distance L of the micro-circular tubes arranged along the width direction of the edge platek , the diameter φ of each row of microtubes.

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

[0017] The three-dimensional fluid-thermal coupling calculation model of the turbine blade edge plate micro-tube array cooling is imported into the meshing program to divide the fluid domain and solid domain meshes required for the full three-dimensional calculation. r,yb , as well as the cooling air inlet and outlet temperature and pressure boundary conditions, use the full three-dimensional fluid-thermal coupling calculation and analysis program to carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine blade edge plate, and obtain the temperature field distribution and data of the blade edge plate;

[0018] If the temperature parameters of the turbine blade edge plate meet the second predetermined temperature standard, the next step is executed; otherwise, the cooling structure parameters of the transverse single-row circular micro-tube array are adjusted by at least reducing the distance from the center line of the tube row to the flow surface of the edge plate, increasing the number of micro-tube rows and increasing the diameter of the micro-tubes, and S102 to S105 are repeated until the temperature parameters of the turbine blade edge plate reach the second predetermined temperature standard.

[0019] Furthermore, the design method comprises:

[0020] If the maximum temperature of the turbine blade 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 blade edge plate is lower than the temperature resistance grade of the metal material used;

[0021] If the maximum temperature of the turbine blade 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 blade edge plate is reduced by not less than 10°C.

[0022] Furthermore, the full three-dimensional heat-flow coupling calculation and analysis of the turbine blade body and edge plate is carried out to obtain the temperature field parameters and data information of the turbine blade including the blade body and edge plate after adding the micro-tube array cooling structure, including:

[0023] Based on the inlet and outlet boundary conditions of the turbine moving blade, the overall three-dimensional model of the turbine moving blade with a transverse single-row circular micro-tube array cooling structure of the turbine moving blade edge plate is imported into the meshing program to divide the fluid domain and solid domain meshes required for the full three-dimensional calculation. Based on the temperature field distribution and data of the moving blade edge plate, the Nusselt number of the turbine moving blade edge plate convective heat transfer, the convective heat transfer coefficient of the turbine moving blade edge plate, as well as the cooling air flow rate and the cooling air inlet and outlet temperature and pressure boundary conditions, the full three-dimensional fluid-heat coupling calculation and analysis of the turbine moving blade edge plate is performed to obtain the temperature field distribution and data of the moving blade edge plate.

[0024] The Nusselt number is:

[0025]

[0026] The convective heat transfer coefficient is:

[0027]

[0028] The cooling air flow rate is:

[0029]

[0030] Among them, Reynolds number Re=uD / ν, rotation number Ro=ΩD / u, density ratio DR=α v (T w -T c ), u is the fluid velocity at the microtube inlet, ν is the fluid kinematic viscosity coefficient, Ω is the rotation speed, α v is the volume expansion coefficient, T w is the wall temperature of the microtube, D is the diameter of the microtube, L is the length of the microtube, C1, C2, C3, C4 are the flow heat transfer power indexes, m is the total mass flow rate of the microtube array, Q r,yb is the heat transferred from the gas to the edge plate, Cp is the constant pressure specific heat capacity of the cold gas, T g is the gas temperature on the edge plate side, h g is the convective heat transfer coefficient of the gas on the edge plate side, A is the heat transfer area on the gas side of the edge plate, T c is the cooling air inlet temperature of the microtube array, h c is the convective heat transfer coefficient of the cooling air, n is the number of microtubes, and λ is the thermal conductivity of the cooling air.

[0031] Furthermore, the constructed three-dimensional model of the moving blade is imported into the meshing program, and the fluid domain and solid domain meshes required for the full three-dimensional calculation are divided. The full three-dimensional fluid-heat coupling calculation and analysis program is used to carry out the full three-dimensional fluid-heat coupling calculation and analysis of the turbine moving blade, and the temperature field distribution and data of the turbine moving blade 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 moving blade edge plate is obtained as the boundary condition for subsequent analysis, and the blade body temperature field distribution and data of the turbine moving blade are obtained.

[0032] Furthermore, the circular micro-tube array cooling structure has a diameter of 0.1 mm to 1 mm. The micro-tube array structure can increase the heat exchange area of ​​the cooling channel and increase the convection heat transfer coefficient.

[0033] Furthermore, the method comprises:

[0034] The turbine blade edge plate is cooled by a single-row circular micro-tube array in a transverse direction. By reducing the diameter of the circular tubes of the micro-tube array, cooling air is delivered to any position of the turbine blade edge plate, thereby achieving precise customized delivery to meet the cooling needs of the edge plate and cooling the high-temperature area of ​​the edge plate in a targeted manner.

[0035] 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.

[0036] The beneficial effects brought by the present invention are as follows:

[0037] It can be seen from the above scheme that an embodiment of the present invention provides a design method for a transverse single-row circular micro-tube array cooling structure of a turbine moving blade edge plate. By performing a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine moving blade, the position of the high-temperature area of ​​the turbine moving blade edge plate where the enhanced cooling structure is to be arranged is determined; an overall three-dimensional model of the turbine moving blade with an edge plate micro-tube array cooling structure is constructed, and a three-dimensional fluid-thermal coupling calculation model for the turbine moving blade edge plate micro-tube array cooling is established; the fluid domain and solid domain grids required for the full three-dimensional calculation are divided, and a full three-dimensional fluid-thermal coupling calculation and analysis of the moving blade edge plate is carried out to obtain the temperature field distribution and temperature data of the moving blade edge plate; the overall full three-dimensional fluid-thermal coupling calculation and analysis of the turbine moving blade body and edge plate is performed to obtain the temperature field parameters and data information of the turbine moving blade including the blade body and edge plate after the micro-tube array cooling structure is added. If the temperature parameters of the turbine moving blade meet the predetermined temperature standards, the design of the transverse single-row circular micro-tube array cooling structure of the turbine moving blade edge plate is completed. The technical solution of the present invention can solve the problem that the blade body of the high-pressure turbine of the gas turbine is limited by the structural size space and the amount of cooling air used, resulting in uneven temperature distribution of the blade body, difficulty in cooling air coverage, resulting in erosion of the blade edge plate, and causing the blade to fail and fail to work. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 A flow chart showing a method for designing a cooling structure of a turbine blade edge plate with a transverse single-row circular micro-tube array according to an embodiment of the present invention. DETAILED DESCRIPTION

[0039] 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.

[0040] like Figure 1 As shown, Figure 1A flow chart showing a method for designing a cooling structure of a turbine blade edge plate with a transverse single-row circular micro-tube array according to an embodiment of the present invention.

[0041] In the figure, a design method for a cooling structure of a turbine blade edge plate with a transverse single-row circular micro-tube array includes:

[0042] S101. Determine the cooling structure of the turbine blade body without a micro-tube array cooling channel according to the appearance of the turbine blade body, perform a full three-dimensional heat-flow coupling calculation and analysis on the turbine blade, and determine the temperature field distribution and data information of the blade body, which will serve as a basis for subsequent analysis and comparison after adopting a circular micro-tube array cooling structure design.

[0043] In an embodiment of the present invention, based on the outer shape of the moving blade obtained by the turbine aerodynamic design, the cooling structure design of the turbine moving blade body is carried out, and the cooling structure design such as film cooling is not carried out for the moving blade edge plate for the time being, so as to obtain a three-dimensional model of the turbine moving blade with a cooling structure. The turbine moving blade is subjected to full three-dimensional fluid-thermal coupling calculation and analysis. According to the inlet and outlet boundary conditions of the turbine moving blade, the constructed three-dimensional moving blade model is imported into the meshing program, and the fluid domain and solid domain mesh 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 turbine moving blade, and the temperature field distribution and data of the turbine moving blade edge plate are obtained as the basis for subsequent analysis and comparison after adopting the micro-tube array cooling design, and the convective heat transfer coefficient of the turbine moving blade edge plate is obtained as the boundary condition for subsequent analysis, and the temperature field distribution and data of the turbine moving blade body are obtained.

[0044] If the temperature parameter of the turbine blade body meets the predetermined temperature standard, that is, the maximum temperature of the turbine 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 turbine blade body reaches the predetermined standard.

[0045] S102, determining the position of the high temperature area of ​​the turbine blade edge plate where the enhanced cooling structure is to be arranged.

[0046] In the embodiment of the present invention, the position of the turbine blade edge plate that needs enhanced cooling is determined. According to the temperature field distribution and data of the blade edge plate, the position of the high temperature area of ​​the turbine blade edge plate is determined, that is, the specific position of the turbine blade edge plate that needs enhanced cooling, and the micro-tube array cooling structure will be arranged at these high temperature positions later.

[0047] S103. According to the surface structure of the moving blade edge plate and in combination with the dimensional parameters of the moving blade edge plate including at least the thickness, width and length of the moving blade edge plate, cooling structure parameters of the turbine moving blade edge plate with a micro-tube array are given.

[0048] In an embodiment of the present invention, based on the specific position of the turbine blade body that requires enhanced cooling, according to the structural characteristics of the blade edge plate surface that is approximately a parallelogram, combined with structural dimensional parameters including at least the thickness, width, and length of the turbine blade edge plate, the cooling structural parameters of a horizontal single-row circular micro-tube array are given.

[0049] The cooling structure parameters of the horizontal single-row circular micro-tube array include: the distance H 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 distance L of the micro-circular tubes arranged along the width direction of the edge plate k , the diameter φ of each row of microtubes.

[0050] S104. Construct an overall three-dimensional model of a turbine blade with an edge plate micro-tube array cooling structure, and establish a three-dimensional fluid-thermal coupling calculation model for turbine blade edge plate micro-tube array cooling.

[0051] In an embodiment of the present invention, a three-dimensional model of a moving blade with a cooling structure utilizes given transverse single-row circular micro-tube array cooling structure parameters to set a micro-circular cross-section tube row whose center line is parallel to the side wall of the edge plate on the moving blade edge plate, thereby constructing a three-dimensional model of a turbine moving blade with a transverse single-row circular micro-tube array cooling structure on the edge plate and a blade body with a cooling structure, and by setting a hollow micro-connecting pipe at the blade cavity position, the cooling channel is connected front to back.

[0052] Based on the turbine moving blade three-dimensional model, the moving blade body cooling structure is ignored, only the moving blade body shape is used, and only the turbine moving blade edge plate three-dimensional model with a transverse single-row circular micro-tube array cooling structure of the edge plate is extracted.

[0053] S105. Based on the three-dimensional model of the turbine blade edge plate, the fluid domain and solid domain grids required for the full three-dimensional calculation are divided, and the full three-dimensional fluid-thermal coupling calculation and analysis of the blade edge plate are carried out to obtain the temperature field distribution and temperature data of the blade edge plate. If the temperature field parameters of the turbine blade edge plate meet the first predetermined temperature standard, that is, the maximum temperature T of the turbine blade edge plate Ryb,max Lower than the temperature resistance grade T of the metal material used S-M , T Ryb,max <T S-M , the design process ends; otherwise, S101 to S105 are repeated until the temperature parameter of the turbine blade edge plate reaches the first predetermined temperature standard.

[0054] In an embodiment of the present invention, the constructed three-dimensional fluid-thermal coupling calculation model of the turbine moving blade plate micro-tube array cooling 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 moving blade plate and the blade body, and 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 the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine moving blade plate, and obtain the temperature field distribution and data of the moving blade plate.

[0055] If the temperature parameters of the turbine blade edge plate meet the second predetermined temperature standard, the next step is executed; otherwise, the cooling structure parameters of the transverse single-row circular micro-tube array are adjusted by at least reducing the distance from the center line of the tube row to the flow surface of the edge plate, increasing the number of micro-tube rows and increasing the diameter of the micro-tubes, and S102 to S105 are repeated until the temperature parameters of the turbine blade edge plate reach the second predetermined temperature standard.

[0056] In an embodiment of the present invention, if the maximum temperature of the turbine blade edge plate is higher than the temperature resistance grade of the metal material used, the second predetermined temperature standard is: the maximum temperature of the turbine blade edge plate is lower than the temperature resistance grade of the metal material used; if the maximum temperature of the turbine blade 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 blade edge plate is reduced by no less than 10°C.

[0057] S106. Carry out full three-dimensional heat-flow coupling calculation and analysis of the turbine rotor blade body and edge plate as a whole, and obtain the temperature field parameters and data information of the turbine rotor blade including the blade body and edge plate after adding the micro-tube array cooling structure; if the temperature field parameters of the turbine rotor blade meet the first predetermined temperature standard, the design process ends; otherwise, repeat S101 to S106 until the temperature parameters of the turbine rotor blade reach the first predetermined temperature standard.

[0058] In an embodiment of the present invention, the same turbine blade inlet and outlet boundary conditions are used, and the overall three-dimensional model of the turbine blade with the constructed edge plate and spherical 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. Then, the full three-dimensional fluid-heat coupling calculation and analysis program is used to carry out the full three-dimensional fluid-heat coupling calculation and analysis of the turbine blade, and the temperature field parameter distribution and data information of the turbine blade (including the blade body and edge plate) after adding the micro-tube array cooling structure are obtained.

[0059] In the embodiment of the present invention, the circular micro-tube array cooling structure is cooled, and the diameter of the circular tube is between 0.1mm and 1mm. The micro-tube array structure can increase the heat exchange area of ​​the cooling channel and increase 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 blade 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 blade edge plate of the gas turbine can be more easily met.

[0060] In another embodiment of the present invention, the turbine blade edge plate is cooled by a transverse single-row circular micro-tube array. The cooling air can be delivered to any position of the blade edge plate by reducing the diameter of the circular tubes of the micro-tube array (to a minimum of 0.1 mm), thereby achieving precise customized delivery of the edge plate cooling needs and specifically cooling the high-temperature area of ​​the edge plate.

[0061] The turbine blade edge plate is cooled by a horizontal single-row circular micro-tube array, and the blade edge plate air film hole cooling structure is eliminated, which is beneficial to weaken the influence of the edge plate air film cooling on the mainstream, reduce mixing loss, and improve turbine efficiency.

[0062] According to the technical solution of the present invention, the turbine blade edge plate is cooled by a horizontal single-row circular micro-tube array, and the interior of the blade edge plate is a hollow structure, which can reduce the weight of the blade by 1%.

[0063] 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.

[0064] A design method for cooling a turbine blade edge plate with a transverse single-row circular micro-tube array is universal and is not limited to the design of high-pressure turbine blades of gas turbines, but is also applicable to the design of high-pressure turbine blades of aircraft engines.

[0065] In an embodiment of the present invention, a cooling design method for a turbine blade edge plate with a transverse single-row circular micro-tube array, based on full utilization of a conventional turbine blade full three-dimensional fluid-thermal coupling calculation method, is provided. According to the structural characteristics of a high-pressure turbine blade edge plate of a gas turbine, the cooling structure design and temperature field calculation process of the blade edge plate are reorganized with emphasis on the high-temperature zone of the high-pressure turbine blade edge plate. A cooling design method for a transverse single-row circular micro-tube array cooling suitable for a high-pressure turbine blade edge plate of a gas turbine is proposed, and an efficient cooling structure design method for a high-pressure turbine blade edge plate is obtained, thereby solving the problem that a high-pressure turbine blade edge plate of a gas turbine is difficult to cool.

[0066] 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 (0.1mm-1mm), thereby realizing super cooling of the edge plate. Not only can the full coverage of the cooling of the high-pressure turbine blade 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.

[0067] In the embodiment of the present invention, the cooling air is delivered to any position of the blade edge plate through the micro-tube array, thereby realizing the precise customized delivery of the edge plate cooling demand, thereby realizing the targeted key cooling of the high temperature area of ​​the edge plate, and meeting the local cooling and temperature reduction demand of the blade edge plate. The technical scheme of the present invention can give full play to the better cooling effect of the micro-tube array, eliminate the film hole cooling structure of the blade edge plate, thereby reducing the influence of the edge plate film cooling on the mainstream, which is beneficial to reduce the cold and hot mixing loss of the turbine blade edge plate and improve the turbine efficiency.

[0068] The invention proposes a method for designing cooling of a turbine blade edge plate with a horizontal single-row circular micro-tube array. The cooling structure of the blade edge plate designed can directly discharge cooling air through the rear side of the blade edge plate, which is not only beneficial to the cooling of the downstream low-pressure turbine guide vanes, but also beneficial to the sealing between the high-pressure turbine blades and the low-pressure turbine guide vane edge plate, avoiding the "invasion" of the high-pressure turbine wheel cavity by gas. The interior of the blade edge plate designed is a hollow structure, which is beneficial to reducing the weight of the blades 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 design method for a turbine blade edge plate transverse single-row circular micro-tube array cooling structure, characterized in that: The design method comprises: S101. Determine the cooling structure of the turbine blade body without a micro-tube array cooling channel according to the appearance of the turbine blade body, perform full three-dimensional fluid-heat coupling calculation and analysis on the turbine blade, and determine the temperature field distribution and data information of the blade body, which will serve as a comparison basis for subsequent analysis and design using a circular micro-tube array cooling structure; S102, determining the position of the high temperature area of ​​the turbine blade edge plate where the enhanced cooling structure is to be arranged; S103, according to the surface structure of the moving blade edge plate, combined with the dimensional parameters of the moving blade edge plate including at least the thickness, width and length of the moving blade edge plate, the cooling structure parameters of the turbine moving blade edge plate with the micro-tube array are given; S104, constructing an overall three-dimensional model of a turbine blade with an edge plate micro-tube array cooling structure, and establishing a three-dimensional fluid-thermal coupling calculation model for turbine blade edge plate micro-tube array cooling; S105. Based on the three-dimensional model of the turbine blade edge plate, the fluid domain and solid domain grids required for the full three-dimensional calculation are divided, and the full three-dimensional fluid-thermal coupling calculation and analysis of the blade edge plate are carried out to obtain the temperature field distribution and temperature data of the blade edge plate. If the temperature field parameters of the turbine blade edge plate meet the first predetermined temperature standard, that is, the maximum temperature T of the turbine blade edge plate Ryb,max Lower than the temperature resistance grade T of the metal material used S-M , T Ryb,max <T S-M , the design process ends; otherwise, S101 to S105 are repeated until the temperature parameter of the turbine blade edge plate reaches the first predetermined temperature standard; S106. Carry out full three-dimensional heat-flow coupling calculation and analysis of the turbine rotor blade body and edge plate as a whole, and obtain the temperature field parameters and data information of the turbine rotor blade including the blade body and edge plate after adding the micro-tube array cooling structure; if the temperature field parameters of the turbine rotor blade meet the first predetermined temperature standard, the design process ends; otherwise, repeat S101 to S106 until the temperature parameters of the turbine rotor blade reach the first predetermined temperature standard.

2. The method for designing a cooling structure of a turbine blade edge plate with a transverse single-row circular micro-tube array according to claim 1, characterized in that: According to the surface structure of the moving blade edge plate, combined with the dimensional parameters of the moving blade edge plate including at least the thickness, width and length of the moving blade edge plate, the cooling structure parameters of the turbine moving blade edge plate with the micro-tube array are given, including: Based on the specific position of the turbine blade edge plate that needs enhanced cooling, according to the structural characteristics of the blade edge plate surface that is approximately parallelogram, combined with structural dimension parameters including at least the thickness, width and length of the turbine blade edge plate, the cooling structural parameters of the transverse single-row circular micro-tube array are given; The cooling structure parameters of the horizontal single-row circular micro-tube array include: the distance H 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 distance L of the micro-circular tubes arranged along the width direction of the edge plate k , the diameter φ of each row of microtubes.

3. The method for designing a cooling structure of a turbine blade edge plate with a transverse single-row circular micro-tube array according to claim 1, characterized in that: Based on the three-dimensional model of the turbine blade edge plate, the fluid domain and solid domain grids required for full three-dimensional calculation are divided, and the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine blade edge plate are carried out to obtain the temperature field distribution and temperature data of the blade edge plate, including: The three-dimensional fluid-thermal coupling calculation model of the turbine blade edge plate micro-tube array cooling is imported into the meshing program to divide the fluid domain and solid domain meshes required for the full three-dimensional calculation. r,yb , as well as the cooling air inlet and outlet temperature and pressure boundary conditions, use the full three-dimensional fluid-thermal coupling calculation and analysis program to carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine blade edge plate, and obtain the temperature field distribution and data of the blade edge plate; If the temperature parameters of the turbine blade edge plate meet the second predetermined temperature standard, the next step is executed; otherwise, the cooling structure parameters of the transverse single-row circular micro-tube array are adjusted by at least reducing the distance from the center line of the tube row to the flow surface of the edge plate, increasing the number of micro-tube rows and increasing the diameter of the micro-tubes, and S102 to S105 are repeated until the temperature parameters of the turbine blade edge plate reach the second predetermined temperature standard.

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

5. The method for designing a cooling structure of a turbine blade edge plate with a transverse single-row circular micro-tube array according to claim 1, characterized in that: The full three-dimensional heat-flow coupling calculation and analysis of the turbine blade body and edge plate is carried out to obtain the temperature field parameters and data information of the turbine blade including the blade body and edge plate after adding the micro-tube array cooling structure, including: Based on the inlet and outlet boundary conditions of the turbine moving blade, the overall three-dimensional model of the turbine moving blade with a transverse single-row circular micro-tube array cooling structure of the turbine moving blade edge plate is imported into the meshing program to divide the fluid domain and solid domain meshes required for the full three-dimensional calculation. Based on the temperature field distribution and data of the moving blade edge plate, the Nusselt number of the turbine moving blade edge plate convective heat transfer, the convective heat transfer coefficient of the turbine moving blade edge plate, as well as the cooling air flow rate and the cooling air inlet and outlet temperature and pressure boundary conditions, the full three-dimensional fluid-heat coupling calculation and analysis of the turbine moving blade edge plate is performed to obtain the temperature field distribution and data of the moving blade edge plate. The Nusselt number is: The convective heat transfer coefficient is: The cooling air flow rate is: Among them, Reynolds number Re=uD / ν, rotation number Ro=ΩD / u, density ratio DR=α v (T w -T c ), u is the fluid velocity at the microtube inlet, ν is the fluid kinematic viscosity coefficient, Ω is the rotation speed, α v is the volume expansion coefficient, T w is the wall temperature of the microtube, D is the diameter of the microtube, L is the length of the microtube, C1, C2, C3, C4 are the flow heat transfer power indexes, m is the total mass flow rate of the microtube array, Q r,yb is the heat transferred from the gas to the edge plate, C p is the constant pressure specific heat capacity of the cold air, T g is the gas temperature on the edge plate side, h g is the convective heat transfer coefficient of the gas on the edge plate side, A is the heat transfer area on the gas side of the edge plate, T c is the cooling air inlet temperature of the microtube array, h c is the convective heat transfer coefficient of the cooling air, n is the number of microtubes, and λ is the thermal conductivity of the cooling air.

6. The method for designing a cooling structure of a turbine blade edge plate with a transverse single-row circular micro-tube array according to claim 1, characterized in that: The constructed three-dimensional model of the moving blade 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-heat coupling calculation and analysis program is used to carry out the full three-dimensional fluid-heat coupling calculation and analysis of the turbine moving blade, and the temperature field distribution and data of the turbine moving blade 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 moving blade edge plate is obtained as the boundary condition for subsequent analysis, and the blade body temperature field distribution and data of the turbine moving blade are obtained.

7. The method for designing a cooling structure of a turbine blade edge plate with a transverse single-row circular micro-tube array according to claim 1, characterized in that: The circular micro-tube array cooling structure has a circular tube diameter ranging from 0.1 mm to 1 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 cooling structure of a turbine blade edge plate with a transverse single-row circular micro-tube array according to claim 1, characterized in that: The method comprises: The turbine blade edge plate has a single-row circular micro-tube array transversely, which delivers cooling air to any position of the turbine blade edge plate by reducing the diameter of the circular tubes of the micro-tube array, thereby achieving precise customized delivery of the edge plate cooling needs and cooling the high-temperature area of ​​the edge plate in a targeted manner.

9. The method for designing a cooling structure of a turbine blade edge plate with a transverse single-row circular micro-tube array 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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