Design method for cooling structure of turbine guide vane edge plate with spherical bulge micro-tube array

Abstract

The present invention provides a design method for a turbine guide vane lip plate cooling structure with a spherical bulge micro-tube array. By performing a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane blade body cooling structure, the high-temperature zone location of the spherical bulge micro-tube array cooling structure to be arranged is determined, and the cooling structure parameters are given. A three-dimensional model of the turbine guide vane with a cooling structure of a single horizontal row of spherical bulge micro-tube array tubes on the lip plate and a cooling structure on the blade body is constructed. Full three-dimensional fluid-thermal coupling calculation and analysis are then performed on the lip plate and the entire turbine guide vane. If the turbine guide vane temperature parameters meet predetermined temperature standards, the design of the turbine guide vane lip plate cooling structure with a spherical bulge micro-tube array is complete. The technical solution of the present invention can solve the problem of gas turbine high-pressure turbine guide vane lip plates being affected by the end region's lateral secondary flow and structural size space limitations, making it difficult for cooling air to reach them, leading to blade lip plate ablation. This prevents the blade from overheating and causing blade failure.

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 turbine guide vane edge plate cooling structure with a spherical bulge micro-tube array. 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 ones, turbine blades exhibit challenging cooling areas. This is particularly true at the endwalls and blade tips, where relatively small dimensions and complex flow conditions create cooling "blind spots" or even "dead zones." Metal temperatures in these locations approach the heat resistance limits of the blade alloy. Similar phenomena have been reported by researchers abroad during gas turbine design and testing. Transient liquid crystal measurements and numerical calculations of turbine blade surface temperature distributions obtained by Siemens and other companies reveal distinct localized high-temperature zones at the blade body, endwalls, and blade tips. These difficult-to-cool localized high-temperature zones can easily lead to localized ablation of the turbine blades, posing significant challenges to turbine blade cooling design. Furthermore, with the widening of engine operating environments and increasing performance requirements, turbine inlet temperatures continue to rise, further complicating the design of turbine blade cooling structures.

[0004] Therefore, when traditional large-scale cooling structures are unable to meet the cooling needs of "blind spots" and "dead zones", innovating and developing efficient cooling structures for turbine blades can further improve the cooling effect without increasing the amount of cooling air, 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 for a turbine guide vane edge plate with a spherical bulge micro-tube array, which 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, resulting in erosion of the blade edge plate, thereby avoiding the problem of over-temperature operation of the turbine blade, which causes the turbine blade to fail and become unable to work.

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

[0007] S101, determining a cooling structure of a turbine guide vane blade body, performing a full three-dimensional fluid-thermal coupling calculation analysis on the turbine guide vane blade body, and determining that temperature parameters of the turbine guide vane blade body meet predetermined temperature standards;

[0008] S102, determining a high-temperature area position in the turbine guide vane edge plate where a spherical bulge micro-tube array cooling structure is to be arranged based on the temperature field distribution and data of the turbine guide vane edge plate;

[0009] S103. According to the surface structure of the guide vane edge plate and in combination with the structural dimension parameters of the guide vane edge plate including at least thickness, width, and length, the cooling structure parameters of a transverse single-row spherical bulge micro-tube array are determined.

[0010] S104, setting a micro circular tube array and a spherical bulge on the guide vane edge plate, and constructing a three-dimensional model of a turbine guide vane with a cooling structure having a single row of spherical bulge micro tube arrays in the transverse direction of the edge plate and a blade with a cooling structure;

[0011] S105, extracting a three-dimensional model of a turbine guide vane edge plate with a transverse single-row spherical bulge micro-tube array cooling structure, and performing a full three-dimensional fluid-thermal coupling calculation and analysis on the three-dimensional model of the turbine guide vane edge plate to obtain temperature field distribution information of the turbine guide vane edge plate;

[0012] S106: If the temperature parameter of the turbine guide vane edge plate meets the predetermined temperature standard, proceed to the next step; otherwise, adjust the cooling structure parameters of the transverse single-row spherical microtube array, and repeat S103 to S105 until the temperature parameter of the turbine guide vane edge plate reaches the predetermined temperature standard;

[0013] S107. Perform a full three-dimensional heat-flow coupling calculation and analysis on the turbine guide vane blade body and the edge plate as a whole to obtain temperature field distribution information of the turbine guide vane with a spherical bulge micro-tube array cooling structure on the edge plate. If the temperature parameters of the turbine guide vane meet the predetermined temperature standard, the design of the turbine guide vane edge plate cooling structure with a spherical bulge micro-tube array is completed; otherwise, repeat the above steps until the temperature parameters of the turbine guide vane reach the predetermined temperature standard.

[0014] Furthermore, a full three-dimensional fluid-thermal coupling calculation analysis is performed on the turbine guide vane to determine whether the temperature parameters of the turbine guide vane blade body meet the predetermined temperature standards, including:

[0015] Construct a 3D model of the turbine guide vane, divide the fluid domain and solid domain meshes required for full 3D calculations, perform full 3D fluid-thermal coupling calculations and analysis of the turbine guide vane, and obtain the temperature field distribution and data of the turbine guide vane edge plate;

[0016] Obtain the convection heat transfer coefficient h of the turbine guide vane edge plate flow surface s,yb and convection heat transfer As boundary conditions for subsequent analysis;

[0017] If the temperature parameter of the turbine guide vane blade meets the predetermined temperature standard, that is, the maximum temperature T of the turbine guide vane blade Sblade,maxLower than the temperature resistance grade T of the metal material used S-M , T Sblade,max <T S-M , then execute S102; otherwise, re-determine the cooling structure of the turbine guide vane blade body until the temperature parameter of the turbine guide vane blade body reaches a predetermined standard.

[0018] Furthermore, the cooling structure parameters of the horizontal single-row spherical microtube array include:

[0019] The position of the centerline of the micro-spherical tubes arranged along the thickness direction of the guide vane edge plate, the position of the centerline of the micro-spherical tubes arranged along the width direction of the guide vane edge plate, the number of micro-spherical tube rows arranged along the width direction of the guide vane edge plate, the tube diameter and length of each micro-tube row, and the path of each micro-tube arranged along the length direction of the guide vane edge plate;

[0020] Among them, the position of the center line of the micro-spherical tube arranged along the thickness direction of the guide vane edge plate, that is, the distance from the center line of the micro-spherical tube to the flow surface of the edge plate; the position of the center line of the micro-spherical tube arranged along the width direction of the guide vane edge plate, that is, the distance from the center line of the micro-spherical tube to the side of the edge plate; the diameter of the micro-tube row includes the diameter of the through tube and the diameter of the spherical bulge.

[0021] Furthermore, a three-dimensional model of a turbine guide vane edge plate with a transverse single-row spherical bulge micro-tube array cooling structure is extracted, and a full three-dimensional fluid-thermal coupling calculation and analysis is performed on the three-dimensional model of the turbine guide vane edge plate to obtain the temperature field distribution information of the turbine guide vane edge plate, including:

[0022] Meshing a three-dimensional model of a turbine guide vane edge plate with a transverse single-row spherical bulge micro-tube array cooling structure is performed to divide the fluid domain and solid domain meshes required for full three-dimensional calculations. Based on the temperature field distribution and data of the turbine guide vane edge plate, the turbine guide vane edge plate convective heat transfer Nusselt number, the turbine guide vane edge plate convective heat transfer coefficient, as well as the cooling air flow rate and the cooling air inlet and outlet temperature and pressure boundary conditions, a full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane edge plate is performed to obtain the guide vane edge plate temperature field distribution and data.

[0023] The Nusselt number is:

[0024]

[0025] The convective heat transfer coefficient is:

[0026]

[0027] The cooling air flow rate is:

[0028]

[0029] Among them, Reynolds number Re=uD / ν, Prandtl number Pr=ν / α, u is the fluid velocity at the microtube inlet, ν is the fluid kinematic viscosity coefficient, D is the straight tube diameter, α is the thermal diffusion coefficient, L is the straight tube length, m is the flow heat transfer power index, n qg is the number of spherical bulges per microtube, d q is the diameter of the spherical bulge, G is the total mass flow rate of the microtube array, Q s,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 convection 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 convection heat transfer coefficient of the cooling air, n is the number of microtubes, λ is the thermal conductivity of the cooling air, and h is the depth of the spherical bulge.

[0030] Furthermore, the temperature parameter of the turbine guide vane edge plate meets the predetermined temperature standard, including:

[0031] If the maximum temperature of the turbine guide vane edge plate is higher 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 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 no less than 10°C.

[0032] Furthermore, adjusting the cooling structure parameters of the transverse single-row spherical microtube array includes:

[0033] The distance from the center line of the micro-spherical tube to the flow surface of the guide vane edge plate is reduced, the number of the micro-tube rows is increased, the diameter of the micro-tubes in the micro-tube rows is increased, and the number of spherical bulges in each micro-tube row is increased.

[0034] Furthermore, the diameter of the cooling circular tube section of the spherical micro-tube array cooling structure is between 0.3 mm and 0.7 mm, and the diameter of the spherical bulge is 1.5 to 2 times the diameter of the circular tube section.

[0035] Furthermore, the turbine guide vane edge plate is cooled by a horizontal single row of spherical micro-tube arrays, which reduces the diameter of the circular tubes of the micro-tube arrays and delivers cooling air to any position of the turbine guide vane edge plate, thereby achieving precise customized delivery of the cooling requirements of the turbine guide vane edge plate and targeted cooling of the high-temperature area of ​​the turbine guide vane edge plate.

[0036] 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.

[0037] The beneficial effects brought about by the present invention are as follows:

[0038] It can be seen from the above scheme that an embodiment of the present invention provides a method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge micro-tube array. By determining the cooling structure of the turbine guide vane blade body, a full three-dimensional fluid-thermal coupling calculation and analysis is performed on the turbine guide vane, and it is determined that the temperature parameters of the turbine guide vane blade body meet the predetermined temperature standards; the position of the high-temperature area in the turbine guide vane edge plate where the spherical bulge micro-tube array cooling structure is to be arranged is determined, and the cooling structure parameters of the transverse single-row spherical micro-tube array are given; a three-dimensional model of a turbine guide vane with a cooling structure of a transverse single-row spherical bulge micro-tube array on the edge plate and a blade body with a cooling structure is constructed; a full three-dimensional fluid-thermal coupling calculation and analysis is performed on the three-dimensional model of the turbine guide vane edge plate to obtain the temperature field distribution information of the turbine guide vane edge plate; a full three-dimensional fluid-thermal coupling calculation and analysis is performed on the turbine guide vane blade body and the edge plate as a whole to obtain the temperature field distribution information of the turbine guide vane. If the temperature parameters of the turbine guide vane meet the predetermined temperature standards, the design of the cooling structure of the turbine guide vane edge plate with the spherical bulge micro-tube array is completed. The technical solution of the present invention can solve the problem that the guide vane edge plate of the high-pressure turbine of the gas turbine is affected by the lateral secondary flow in the end area and the structural size and space are limited, making it difficult for cooling air to cover, resulting in erosion of the blade edge plate, thereby avoiding the problem of blade overheating and causing blade failure and inability to work. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 A flow chart showing a method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge microtube array according to an embodiment of the present invention. DETAILED DESCRIPTION

[0040] To make the objectives, technical solutions, and advantages of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0041] like Figure 1 As shown, Figure 1 A flow chart showing a method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge microtube array according to an embodiment of the present invention.

[0042] The figure shows a design method for a turbine guide vane edge plate cooling structure with a spherical bulge micro-tube array, including:

[0043] S101. Determine the cooling structure of the turbine guide vane blade body, perform full three-dimensional fluid-thermal coupling calculation analysis on the turbine guide vane blade body, and determine that the temperature parameters of the turbine guide vane blade body meet predetermined temperature standards.

[0044] In an embodiment of the present invention, based on the appearance obtained by the turbine aerodynamic design, the turbine guide vane and blade body cooling structure design is carried out, wherein the guide vane edge plate does not temporarily carry out cooling structure design such as film cooling, and the guide vane and blade body cooling structure is obtained.

[0045] Based on the inlet and outlet boundary conditions of the turbine guide vanes, a three-dimensional model of the turbine guide vanes was constructed, and the fluid and solid domains required for full three-dimensional calculations were meshed. A full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vanes was performed, and the temperature field distribution and data of the turbine guide vane edge plate were obtained. This served as a basis for subsequent analysis and comparison with the cooling design using a micro-tube array with spherical bulges.

[0046] Obtain the convection heat transfer coefficient h of the turbine guide vane edge plate flow surface s,yb and convection heat transfer As boundary conditions for subsequent analysis;

[0047] If the temperature parameter of the turbine guide vane blade meets the predetermined temperature standard, that is, the maximum temperature T of the turbine guide vane blade Sblade,max Lower than the temperature resistance grade T of the metal material used S-M , T Sblade,max <T S-M , then execute S102; otherwise, re-determine the cooling structure of the turbine guide vane blade body until the temperature parameter of the turbine guide vane blade body reaches a predetermined standard.

[0048] S102 : Determine the location of a high-temperature area in the turbine guide vane edge plate where a spherical bulge micro-tube array cooling structure is to be arranged based on the temperature field distribution and data of the turbine guide vane edge plate.

[0049] In the embodiment of the present invention, specific locations on the turbine guide vane edge plate that require enhanced cooling will subsequently be equipped with a micro-tube array cooling structure with spherical bulges at these high-temperature locations.

[0050] S103 , according to the surface structure of the guide vane edge plate and in combination with the structural dimension parameters of the guide vane edge plate including at least thickness, width, and length, the cooling structural parameters of the transverse single-row spherical bulge micro-tube array are given.

[0051] In an embodiment of the present invention, based on the determination of the specific position of the turbine guide vane edge plate that requires cooling, according to the structural characteristics of the turbine guide vane edge plate surface that is approximately a parallelogram, combined with structural dimension parameters such as the thickness, width, and length of the guide vane edge plate, the cooling structural parameters of a transverse single-row spherical micro-tube array are given: the position of the center line of the micro-spherical tubes arranged along the thickness direction of the guide vane edge plate, the position of the center line of the micro-spherical tubes arranged along the width direction of the guide vane edge plate, the number of micro-spherical tube rows arranged along the width direction of the guide vane edge plate, the diameter and length of each micro-tube row, and the path of each micro-tube arranged along the length direction of the guide vane edge plate.

[0052] Among them, the position of the center line of the micro-spherical tube arranged along the thickness direction of the guide vane edge plate, that is, the distance from the center line of the micro-spherical tube to the flow surface of the edge plate; the position of the center line of the micro-spherical tube arranged along the width direction of the guide vane edge plate, that is, the distance from the center line of the micro-spherical tube to the side of the edge plate; the diameter of the micro-tube row includes the diameter of the through tube and the diameter of the spherical bulge.

[0053] S104. Arrange a micro circular tube array and a spherical bulge on the guide vane edge plate to construct a cooling structure with a single row of spherical bulge micro tube arrays on the edge plate and a three-dimensional model of a turbine guide vane with a cooling structure on the blade body.

[0054] In an embodiment of the present invention, based on a three-dimensional model of a turbine guide vane, using given parameters of a transverse single-row spherical bulge micro-tube array cooling structure, a micro-circular tube row and a spherical bulge are arranged on the guide vane edge plate to construct a three-dimensional model of a turbine guide vane with a transverse single-row spherical bulge micro-tube array cooling structure on the edge plate and a blade body with a cooling structure.

[0055] S105. Extract a three-dimensional model of a turbine guide vane edge plate with a transverse single-row spherical bulge micro-tube array cooling structure, and perform a full three-dimensional fluid-thermal coupling calculation and analysis on the three-dimensional model of the turbine guide vane edge plate to obtain temperature field distribution information of the turbine guide vane edge plate.

[0056] S106. If the temperature parameters of the turbine guide vane edge plate meet the predetermined temperature standard, proceed to the next step; otherwise, adjust the cooling structure parameters of the transverse single-row spherical microtube array and repeat S103 to S105 until the temperature parameters of the turbine guide vane edge plate reach the predetermined temperature standard.

[0057] In an embodiment of the present invention, a three-dimensional model of a turbine guide vane edge plate with a transverse single-row spherical bulge micro-tube array cooling structure is meshed to divide the fluid domain and solid domain meshes required for full three-dimensional calculations. Based on the temperature field distribution and data of the turbine guide vane edge plate, the Nusselt number of the turbine guide vane edge plate for convective heat transfer, the convective heat transfer coefficient of the turbine guide vane edge plate, as well as the cooling air flow rate and the cooling air inlet and outlet temperature and pressure boundary conditions, a full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane edge plate is performed to obtain the temperature field distribution and data of the guide vane edge plate.

[0058] The Nusselt number is:

[0059]

[0060] The convective heat transfer coefficient is:

[0061]

[0062] The cooling air flow rate is:

[0063]

[0064] Among them, Reynolds number Re=uD / ν, Prandtl number Pr=ν / α, u is the fluid velocity at the microtube inlet, ν is the fluid kinematic viscosity coefficient, D is the straight tube diameter, α is the thermal diffusion coefficient, L is the straight tube length, m is the flow heat transfer power index, n qg is the number of spherical bulges per microtube, d q is the diameter of the spherical bulge, G is the total mass flow rate of the microtube array, Q s,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 convection 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 convection heat transfer coefficient of the cooling air, n is the number of microtubes, λ is the thermal conductivity of the cooling air, and h is the depth of the spherical bulge.

[0065] If the maximum temperature of the turbine guide vane edge plate is higher 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 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 no less than 10°C.

[0066] In an embodiment of the present invention, adjusting the cooling structure parameters of the transverse single-row spherical microtube array includes: reducing the distance from the center line of the microspherical tube to the flow surface of the guide vane edge plate, increasing the number of microtube rows, increasing the diameter of the microtubes in the microtube rows, and increasing the number of spherical bulges in each microtube row.

[0067] S107. Perform a full three-dimensional heat-flow coupling calculation and analysis on the turbine guide vane blade body and the edge plate as a whole to obtain temperature field distribution information of the turbine guide vane with a spherical bulge micro-tube array cooling structure on the edge plate. If the temperature parameters of the turbine guide vane meet the predetermined temperature standard, the design of the turbine guide vane edge plate cooling structure with a spherical bulge micro-tube array is completed; otherwise, repeat the above steps until the temperature parameters of the turbine guide vane reach the predetermined temperature standard.

[0068] In an embodiment of the present invention, the diameter of the cooling circular tube section of the spherical micro-tube array cooling structure is between 0.3mm and 0.7mm, and the diameter of the spherical bulge is 1.5 to 2 times the diameter of the circular tube section. The smaller diameter tube array, in conjunction with the spherical bulge-enhanced cooling structure, is conducive to exponentially increasing the heat exchange area of ​​the cooling channel and exponentially increasing the convective heat transfer coefficient, thereby achieving super cooling of the edge plate. Obviously, through the micro-tube array structure with spherical bulges, not only can full coverage of the high-pressure turbine guide vane edge plate cooling be achieved, but the edge plate cooling requirements can also be fully met. Therefore, the edge plate air film cooling can be eliminated. The problem of traditional edge plate air film cooling being affected by the lateral secondary flow in the end area and the spatial structure limitation, which makes it difficult for the air film to cover the cooling "dead zone", will no longer exist.

[0069] In another embodiment of the present invention, the turbine guide vane edge plate is cooled by a horizontal single row of spherical micro-tube arrays, the diameter of the circular tubes of the micro-tube array is reduced, and the cooling air is delivered to any position of the turbine guide vane edge plate, thereby achieving precise customized delivery of the cooling requirements of the turbine guide vane edge plate and targeted cooling of the high-temperature area of ​​the turbine guide vane edge plate.

[0070] 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.

[0071] In an embodiment of the present invention, by fully leveraging conventional full-three-dimensional flow-heat coupling calculation methods for turbine guide vanes, and based on the structural characteristics of gas turbine high-pressure turbine guide vane lip plates, the guide vane lip plate cooling structure design and temperature field calculation process are reorganized to target the high-temperature zone of the high-pressure turbine guide vane lip plate. This results in a highly efficient cooling structure design method for high-pressure turbine guide vane lip plates, addressing the difficulty in cooling high-pressure turbine guide vane lip plates. Specifically, by utilizing microtube arrays with relatively small diameters (0.3mm-0.7mm) combined with spherical bulges to enhance the cooling structure, the heat exchange area and convective heat transfer coefficient of the cooling channel are multiplied, achieving super-cooling of the lip plate. This not only achieves full cooling coverage of the high-pressure turbine guide vane lip plate, but also fully meets the lip plate cooling requirements. Consequently, film cooling of the lip plate can be eliminated, effectively resolving the cooling "dead zone" problem of conventional film cooling structures, which is difficult to cover due to the influence of lateral secondary flow near the lip plate and spatial structural limitations. This effectively addresses the problem of blade lip plate ablation.

[0072] In this embodiment of the present invention, cooling air is delivered to any location on the guide vane edge plate via a spherical micro-tube array, enabling precise and customized delivery to meet the cooling needs of the edge plate, enabling targeted cooling of the high-temperature area of ​​the edge plate, and meeting the local cooling requirements of the guide vane edge plate. The technical solution of the present invention fully utilizes the superior cooling effect of the spherical micro-tube array, eliminating the film hole cooling structure of the guide vane edge plate, thereby reducing the impact of the edge plate film cooling on the main flow, which is beneficial for reducing the mixing loss of hot and cold air on the turbine guide vane edge plate and improving turbine efficiency.

[0073] The guide vane plate cooling structure designed in this invention discharges cooling air directly through the rear side of the guide vane plate, not only facilitating cooling of downstream rotor blades but also ensuring a tight seal between the guide vanes and the blade plate, preventing gas from intruding into the high-pressure turbine disc cavity. The hollow interior of the turbine blade plate reduces the weight of the guide vanes and improves the engine's power-to-weight ratio.

[0074] In one embodiment of the present invention, a method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge microtube array includes:

[0075] Step 1: Determine the cooling structure of the turbine guide vane blade. Based on the guide vane shape obtained from the turbine aerodynamic design, carry out the cooling structure design of the turbine guide vane blade. The cooling structure design of the guide vane edge plate, such as film cooling, will not be carried out for the time being. A three-dimensional model of the guide vane with cooling structure is obtained.

[0076] Step 2: Perform full 3D fluid-thermal coupling calculation and analysis on the turbine guide vanes. Based on the turbine guide vane inlet and outlet boundary conditions, the constructed guide vane 3D model is imported into the meshing program to divide the fluid domain and solid domain meshes required for the full 3D calculation. Then, using the full 3D fluid-thermal coupling calculation and analysis program, the full 3D fluid-thermal coupling calculation and analysis of the turbine guide vanes is carried out to obtain the temperature field distribution and data of the turbine guide vane edge plate. This serves as a basis for subsequent analysis and comparison after adopting the spherical 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 temperature field distribution and data of the turbine guide vane blade body are obtained.

[0077] 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 turbine guide vane blade body meets the predetermined standard;

[0078] Step 3: Determine the locations on the turbine guide vane edge requiring enhanced cooling. Based on the temperature field distribution and data of the guide vane edge, determine the locations of the high-temperature areas on the turbine guide vane edge. These locations will then be equipped with micro-tube array cooling structures with spherical bulges.

[0079] Step 4. Given the cooling structural parameters of the spherical bulge micro-tube array of the turbine guide vane edge plate. On the basis of determining the specific position of the guide vane edge plate that needs to be cooled, according to the structural characteristics of the guide vane edge plate surface that is approximately a parallelogram, combined with the structural dimension parameters such as the thickness, width, and length of the guide vane edge plate, given the cooling structural parameters of the transverse single-row spherical micro-tube array: the position of the center line of the micro-spherical tube row set along the thickness direction of the edge plate (the distance H to the flow surface of the edge plate), the position of the center line of the micro-spherical tube row set along the width direction of the edge plate (the distance W to the side of the edge plate), the number n or distance Lk of the micro-spherical tube rows set along the width direction of the edge plate, the diameter of the micro-tube row (the through pipe diameter D and the spherical bulge diameter d q ), the length L of the cooling channel of each micro-tube row, the depth h of the spherical bulge, the number n of spherical bulges of each micro-tube row qg , the path of each microtube arranged along the length direction of the edge plate;

[0080] Step 5: Construct an overall 3D model of the turbine guide vane with a spherical bulge micro-tube array cooling structure on the edge plate. Based on the 3D model of the guide vane with a cooling structure, using the given parameters of the horizontal single-row spherical micro-tube array cooling structure, a micro-circular tube row and spherical bulge are set on the guide vane edge plate to construct a 3D model of the turbine guide vane with a horizontal single-row spherical micro-tube array cooling structure on the edge plate and a cooling structure on the blade body. By setting hollow micro-connecting pipes in the blade cavity position, the cooling channel is connected from front to back.

[0081] Step 6: Establish a three-dimensional fluid-thermal coupling calculation model for the cooling of the spherical micro-tube array on the edge plate. Using the three-dimensional model of the turbine guide vane, ignoring the cooling structure of the guide vane blade body, and only using the guide vane blade body shape, only the turbine guide vane edge plate model with a single row of spherical bulge micro-tube array cooling structure on the edge plate is extracted;

[0082] Step 7: Full 3D fluid-thermal coupling calculation and analysis of the turbine guide vane edge plate. Import the constructed 3D fluid-thermal coupling calculation model of the turbine guide vane edge plate spherical micro-tube array cooling into the meshing program, divide the fluid domain and solid domain meshes required for the full 3D calculation, and use the full 3D fluid-thermal coupling calculation and analysis program to carry out the full 3D fluid-thermal coupling calculation and analysis of the turbine guide vane edge plate based on the temperature and convective 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, and obtain the temperature field distribution and data of the guide vane edge plate;

[0083] If the temperature parameters of the turbine guide vane edge plate meet the predetermined temperature standard (if the maximum temperature of the turbine guide vane edge plate is higher 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 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), then proceed to the next step; if it does not meet the predetermined standard, adjust the cooling structure parameters of the transverse single-row spherical micro-tube array (reduce the distance from the centerline to the edge plate flow surface, increase the number of micro-tube rows, increase the diameter of the micro-tubes, and increase the number of spherical bulges in each micro-tube row), and repeat steps 4 to 7 until the temperature parameters of the turbine guide vane edge plate meet the predetermined standard;

[0084] Step 8: Full 3D fluid-thermal coupling calculation and analysis of the entire guide vane, blade body, and lip plate. Using the same turbine guide vane inlet and outlet boundary conditions as in Step 2, the overall 3D model of the turbine guide vane with the lip plate's spherical bulge micro-tube array cooling structure constructed in Step 5 is imported into the meshing program. The fluid and solid domain meshes required for the full 3D calculation are then divided. The full 3D fluid-thermal coupling calculation and analysis program is then used to perform full 3D fluid-thermal coupling calculation and analysis of the turbine guide vane, obtaining the temperature field distribution and data for the turbine guide vane (including the blade body and lip plate) after the spherical bulge micro-tube array cooling structure is added.

[0085] If the temperature parameter of the turbine guide vane (including the blade body and the edge plate) obtained in step 8 meets the predetermined temperature standard, the next step is executed; if it does not meet the predetermined standard, steps 1 to 8 are repeated until the temperature parameter of the turbine guide vane reaches the predetermined standard.

[0086] In another embodiment of the present invention, unlike the above-described embodiments, a method for designing a turbine guide vane lip plate cooling structure with a spherical microtube array is provided. The diameter of the cooling tubes in the spherical microtube array cooling structure is typically between 0.3 mm and 0.7 mm. The smaller diameter microtube array, combined with the spherical bulge to enhance the cooling structure, exponentially increases the heat exchange area of ​​the cooling channel and the convective heat transfer coefficient, thereby achieving super-cooling of the lip plate. Clearly, the spherical microtube array not only achieves full coverage of the high-pressure turbine guide vane lip plate cooling, but also fully meets the lip plate cooling requirements. Therefore, lip plate film cooling can be eliminated. The problem of traditional lip plate film cooling being affected by the end region's lateral secondary flow and spatial structure limitations, which results in the film having difficulty covering the cooling "dead zone," will no longer exist, making it easier to meet the cooling requirements of the high-pressure turbine guide vane lip plate of a gas turbine.

[0087] In another embodiment of the present invention, a method for designing a cooling structure for a turbine guide vane edge plate with a spherical bulge microtube array is different from the above two embodiments in that the turbine guide vane edge plate is cooled by a transverse single row of spherical microtube arrays. 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 microtube array (to a minimum of 0.3 mm), thereby achieving precise customized delivery of the edge plate cooling needs, and enhanced cooling through smaller-scale spherical bulge pipes (to a minimum of 0.2 mm), which can target the high-temperature area of ​​the edge plate.

[0088] In another embodiment of the present invention, a method for designing a cooling structure for a turbine guide vane edge plate with a spherical bulge microtube array is different from the above three embodiments in that the turbine guide vane edge plate is cooled by a transverse single row of spherical microtube arrays, and the guide vane edge plate air film hole cooling structure is eliminated, which is beneficial to weakening the impact of the edge plate air film cooling on the mainstream, reducing mixing losses, and improving turbine efficiency.

[0089] In another embodiment of the present invention, a method for designing a cooling structure for a turbine guide vane edge plate with a spherical bulge microtube array is different from the above four embodiments in that the turbine guide vane edge plate is cooled by a single row of spherical microtube arrays 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 2%.

[0090] The present invention proposes a method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge micro-tube array. The method is universal and is not limited to the design of high-pressure turbine guide vanes of gas turbines, but is also applicable to the design of high-pressure turbine guide vanes of aircraft engines.

[0091] The above is a preferred embodiment 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 the scope of protection of the present invention.

Claims

1. A method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge micro-tube array, characterized in that: The design method comprises: S101, determining a cooling structure of a turbine guide vane blade body, performing a full three-dimensional fluid-thermal coupling calculation analysis on the turbine guide vane blade body, and determining that temperature parameters of the turbine guide vane blade body meet predetermined temperature standards; S102, determining a high-temperature area position in the turbine guide vane edge plate where a spherical bulge micro-tube array cooling structure is to be arranged based on the temperature field distribution and data of the turbine guide vane edge plate; S103. According to the surface structure of the guide vane edge plate and in combination with the structural dimension parameters of the guide vane edge plate including at least thickness, width, and length, the cooling structure parameters of a transverse single-row spherical bulge micro-tube array are determined. S104, setting a micro circular tube array and a spherical bulge on the guide vane edge plate, and constructing a three-dimensional model of a turbine guide vane with a cooling structure having a single row of spherical bulge micro tube arrays in the transverse direction of the edge plate and a blade with a cooling structure; S105, extracting a three-dimensional model of a turbine guide vane edge plate with a transverse single-row spherical bulge micro-tube array cooling structure, and performing a full three-dimensional fluid-thermal coupling calculation and analysis on the three-dimensional model of the turbine guide vane edge plate to obtain temperature field distribution information of the turbine guide vane edge plate; S106: If the temperature parameter of the turbine guide vane edge plate meets the predetermined temperature standard, proceed to the next step; otherwise, adjust the cooling structure parameters of the transverse single-row spherical bulge micro-tube array on the edge plate, and repeat S103 to S105 until the temperature parameter of the turbine guide vane edge plate reaches the predetermined temperature standard; S107. Perform a full three-dimensional heat-flow coupling calculation and analysis on the turbine guide vane blade body and edge plate as a whole to obtain temperature field distribution information of the turbine guide vane with a spherical bulge micro-tube array cooling structure on the edge plate. If the temperature parameters of the turbine guide vane meet the predetermined temperature standard, the design of the turbine guide vane edge plate cooling structure with a spherical bulge micro-tube array is completed; otherwise, repeat steps S101 to S107 until the temperature parameters of the turbine guide vane reach the predetermined temperature standard.

2. The method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge micro-tube array according to claim 1, characterized in that: Perform full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vanes to determine whether the temperature parameters of the turbine guide vane blade body meet the predetermined temperature standards, including: Construct a 3D model of the turbine guide vane, divide the fluid domain and solid domain meshes required for full 3D calculations, perform full 3D fluid-thermal coupling calculations and analysis of the turbine guide vane, and obtain the temperature field distribution and data of the turbine guide vane edge plate; Obtain the convection heat transfer coefficient h of the turbine guide vane edge plate flow surface s,yb and convection heat transfer As boundary conditions for subsequent analysis; If the temperature parameter of the turbine guide vane blade meets the predetermined temperature standard, that is, the maximum temperature T of the turbine guide vane blade Sblade,max Lower than the temperature resistance grade T of the metal material used S-M , T Sblade,max <T S-M , then execute S102; otherwise, re-determine the cooling structure of the turbine guide vane blade body until the temperature parameter of the turbine guide vane blade body reaches a predetermined standard.

3. The method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge micro-tube array according to claim 1, characterized in that: The cooling structure parameters of the edged plate transverse single-row spherical bulge micro-tube array include: The position of the centerline of the micro-spherical tubes arranged along the thickness direction of the guide vane edge plate, the position of the centerline of the micro-spherical tubes arranged along the width direction of the guide vane edge plate, the number of micro-spherical tube rows arranged along the width direction of the guide vane edge plate, the tube diameter and length of each micro-tube row, and the path of each micro-tube arranged along the length direction of the guide vane edge plate; Among them, the position of the center line of the micro-spherical tube arranged along the thickness direction of the guide vane edge plate, that is, the distance from the center line of the micro-spherical tube to the flow surface of the edge plate; the position of the center line of the micro-spherical tube arranged along the width direction of the guide vane edge plate, that is, the distance from the center line of the micro-spherical tube to the side of the edge plate; the diameter of the micro-tube row includes the diameter of the through tube and the diameter of the spherical bulge.

4. The method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge micro-tube array according to claim 1, characterized in that: A three-dimensional model of a turbine guide vane edge plate with a transverse single-row spherical bulge micro-tube array cooling structure is extracted, and a full three-dimensional fluid-thermal coupling calculation and analysis is performed on the turbine guide vane edge plate three-dimensional model to obtain the temperature field distribution information of the turbine guide vane edge plate, including: Meshing a three-dimensional model of a turbine guide vane edge plate with a transverse single-row spherical bulge micro-tube array cooling structure is performed to divide the fluid domain and solid domain meshes required for full three-dimensional calculations. Based on the temperature field distribution and data of the turbine guide vane edge plate, the turbine guide vane edge plate convective heat transfer Nusselt number, the turbine guide vane edge plate convective heat transfer coefficient, as well as the cooling air flow rate and the cooling air inlet and outlet temperature and pressure boundary conditions, a full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane edge plate is performed to obtain the guide vane edge plate temperature field distribution and data. The Nusselt number is: The convective heat transfer coefficient is: The cooling air flow rate is: Among them, Reynolds number Re=uD / ν, Prandtl number Pr=ν / α, u is the fluid velocity at the microtube inlet, ν is the fluid kinematic viscosity coefficient, D is the straight tube diameter, α is the thermal diffusion coefficient, L is the straight tube length, m is the flow heat transfer power index, n qg is the number of spherical bulges per microtube, d q is the diameter of the spherical bulge, G is the total mass flow rate of the microtube array, Q s,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 convection 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 convection heat transfer coefficient of the cooling air, n is the number of microtubes, λ is the thermal conductivity of the cooling air, and h is the depth of the spherical bulge.

5. The method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge micro-tube array according to claim 1, characterized in that: The temperature parameters of the turbine guide vane edge plate satisfy the predetermined temperature standard, including: If the maximum temperature of the turbine guide vane edge plate is higher 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 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 no less than 10°C.

6. The method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge micro-tube array according to claim 3, characterized in that: Adjusting the cooling structure parameters of the edged plate transverse single-row spherical bulge microtube array includes: The distance from the center line of the micro-spherical tube to the flow surface of the guide vane edge plate is reduced, the number of micro-tube rows is increased, the diameter of the micro-tubes in the micro-tube rows is increased, and the number of spherical bulges in each micro-tube row is increased.

7. The method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge micro-tube array according to claim 1, characterized in that: The diameter of the cooling circular tube section of the edged plate transverse single-row spherical bulge micro-tube array cooling structure is between 0.3mm and 0.7mm, and the diameter of the spherical bulge is 1.5 to 2 times the diameter of the circular tube section.

8. The method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge micro-tube array according to claim 1, characterized in that: The turbine guide vane edge plate is cooled by a horizontal single-row spherical micro-tube array, which reduces the diameter of the circular tubes of the micro-tube array and delivers cooling air to any position of the turbine guide vane edge plate, thereby achieving precise customized delivery according to the cooling needs of the turbine guide vane edge plate and cooling the high-temperature area of ​​the turbine guide vane edge plate in a targeted manner.

9. The method for designing a cooling structure of a turbine guide vane edge plate with a spherical bulge micro-tube array according to claim 1, characterized in that: The three-dimensional modeling software of the computational domain adopts UG NX software, the full three-dimensional fluid-thermal coupling calculation and analysis software adopts CFX and Fluent software, and the meshing adopts ICEM CFD software.

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