Design method for cooling structure of turbine guide vane blade with bamboo-shaped microtube array

Abstract

The present invention provides a design method for the cooling structure of a turbine guide vane edge plate with a bamboo-shaped microtube array. Through the full three-dimensional fluid-thermal coupling calculation and analysis of the cooling structure of the turbine guide vane body, the position of the high-temperature area in the turbine guide vane edge plate where the bamboo-shaped microtube array cooling structure is 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 having a transverse single-row bamboo-shaped microtube array on the edge plate and a cooling structure on the vane body is constructed, and the full three-dimensional fluid-thermal coupling calculation and analysis of the edge plate, the turbine guide vane body, and the overall edge plate are carried out respectively. If the temperature parameters of the turbine guide vane meet the predetermined temperature standard, the design of the cooling structure of the turbine guide vane edge plate with a bamboo-shaped microtube array is completed. The technical solution of the present invention can solve the problems that the edge plate of the high-pressure turbine guide vane of a gas turbine is affected by the transverse secondary flow in the end region and the limitation of the structural dimension space, and it is difficult for the cooling air to cover, resulting in the ablation of the blade edge plate, and avoid the problem that the blade fails to work due to over-temperature operation of the blade.

Description

Technical Field

[0001] The present invention belongs to the technical field of gas turbine design, and particularly relates to a design method for a turbine guide vane edge plate cooling structure with a bamboo-shaped microtube array. Background Art

[0002] With the continuous improvement of the performance indicators of gas turbines and the continuous expansion of their working boundaries, the turbine inlet temperature has been continuously increasing, posing higher requirements for the temperature resistance level of turbine blade materials and the design of cooling structures under high-load conditions for long-term continuous operation.

[0003] During the operation of existing engines and the development of new engines, there are areas on turbine blades that are difficult to cool. In particular, positions such as the end wall and blade tip with relatively small size spaces and complex flows are extremely prone to forming cooling "blind spots" or even "dead zones". The metal temperatures at these positions are close to the heat resistance limit of the blade alloy. Similar phenomena have also been reported by foreign researchers during the design and testing of gas turbines. The surface temperature distribution of turbine rotor blades obtained by Siemens and other companies through transient liquid crystal measurement and numerical calculation shows that obvious local high-temperature areas appear at the blade body, end wall, and blade tip. These difficult-to-cool local high-temperature areas are extremely prone to causing local ablation of turbine blades, bringing great difficulties to the cooling design of turbine blades. In addition, with the expansion of the engine's operating environment and the improvement of performance requirements, the turbine inlet temperature has been continuously increasing, further increasing the design difficulty of the turbine blade cooling structure.

[0004] Therefore, in the case where traditional large-scale cooling structures are difficult to meet the cooling requirements of "blind spots" and "dead zones", innovating and developing efficient cooling structures for turbine blades to further improve the cooling effect without increasing the cooling air consumption 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 design method for a turbine guide vane edge plate cooling structure with a bamboo-shaped microtube array, which can solve the problem that the cooling air of the high-pressure turbine guide vane edge plate of a gas turbine is difficult to cover due to the influence of the end region transverse secondary flow and the limitation of the structural dimension space, resulting in the ablation of the blade edge plate, and avoid the problem that the turbine blade operates at an over-temperature, causing the turbine blade to fail and unable to work.

[0006] In an embodiment of the present invention, a design method for a turbine guide vane edge plate cooling structure with a bamboo-shaped microtube array is provided, including:

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

[0008] S102. Determine the position of the high-temperature area in the turbine guide vane edge plate where the bamboo-joint-shaped microtube array cooling structure is to be arranged according to the temperature field distribution and data of the turbine guide vane edge plate;

[0009] S103. Given the cooling structure parameters of the single-row transverse bamboo-joint-shaped microtube array according to the surface structure of the guide vane edge plate, combined with the structural dimension parameters of the guide vane edge plate including at least thickness, width, and length;

[0010] S104. Set up micro circular tube rows and bamboo-joint-shaped bulges on the guide vane edge plate to construct a three-dimensional model of the turbine guide vane with a single-row transverse bamboo-joint-shaped bulge microtube array cooling structure on the edge plate and a cooling structure on the blade body;

[0011] S105. Extract the three-dimensional model of the turbine guide vane edge plate with a single-row transverse bamboo-joint-shaped microtube 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 the temperature field distribution information of the turbine guide vane edge plate;

[0012] 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 single-row transverse bamboo-joint-shaped microtube array, and repeat S103 to S105 until the temperature parameters of the turbine guide vane edge plate reach the predetermined temperature standard;

[0013] S107. Perform a full three-dimensional fluid-thermal coupling calculation and analysis on the entire blade body and edge plate of the turbine guide vane to obtain the temperature field distribution information of the turbine guide vane with a bamboo-joint-shaped microtube array cooling structure on the edge plate. If the temperature parameters of the turbine guide vane meet the predetermined temperature standard, the cooling structure design of the turbine guide vane edge plate with a bamboo-joint-shaped microtube array is completed; otherwise, repeat the above steps until the temperature parameters of the turbine guide vane reach the predetermined temperature standard.

[0014] Further, performing a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane to determine that the temperature parameters of the blade body of the turbine guide vane meet the predetermined temperature standard includes:

[0015] Construct a three-dimensional model of the turbine guide vane, divide the grids of the fluid domain and solid domain required for the full three-dimensional calculation, and perform a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane to obtain the temperature field distribution and data of the turbine guide vane edge plate;

[0016] Obtain the convective heat transfer coefficient h s,yb and the convective heat transfer amount of the flow-through surface of the turbine guide vane edge plate as the boundary conditions for subsequent analysis;

[0017] If the temperature parameters of the blade body of the turbine guide vane meet the predetermined temperature standard, that is, the maximum temperature T of the blade body of the turbine guide vane Sblade,maxLower than the temperature resistance level 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 until the temperature parameter of the turbine guide vane blade reaches the predetermined standard.

[0018] Further, the cooling structure parameters of the transverse single-row bamboo joint-shaped microtube array include:

[0019] The position of the center line of the micro bamboo joint-shaped tube arranged along the thickness direction of the guide vane flange, the position of the center line of the micro bamboo joint-shaped tube arranged along the width direction of the guide vane flange, the number of rows of the micro bamboo joint-shaped tubes arranged along the width direction of the guide vane flange, the diameter and length of each row of microtubes, and the path of each microtube arranged along the length direction of the guide vane flange;

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

[0021] Further, extract the three-dimensional model of the turbine guide vane flange with a transverse single-row bamboo joint-shaped microtube 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 flange to obtain the temperature field distribution information of the turbine guide vane flange, including:

[0022] Perform grid division on the three-dimensional model of the turbine guide vane flange with a transverse single-row bamboo joint-shaped microtube array cooling structure, divide the grids of the fluid domain and the solid domain required for the full three-dimensional calculation, and based on the temperature field distribution and data of the turbine guide vane flange, the Nusselt number of the convective heat transfer of the turbine guide vane flange, the convective heat transfer coefficient of the turbine guide vane flange, as well as the cooling air flow rate, the temperature and pressure boundary conditions at the inlet and outlet of the cooling air, perform a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane flange to obtain the temperature field distribution and data of the guide vane flange;

[0023] Among them, the Nusselt number is:

[0024]

[0025] The convective heat transfer coefficient is:

[0026]

[0027] The cooling air flow rate is:

[0028]

[0029] Among them, the Reynolds number Re = uD / ν, the Prandtl number Pr = ν / α, where u is the fluid velocity at the inlet of the microtube, ν is the kinematic viscosity coefficient of the fluid, D is the diameter of the straight tube, α is the thermal diffusivity, L is the length of the straight tube, m is the flow and heat transfer power exponent, n ZJ is the number of bamboo joints of each microtube, l is the length of each bamboo joint, d is the diameter of the bamboo joint, G is the total mass flow rate of the microtube array, Q s,yb is the heat transferred from the gas to the flange, Cp is the specific heat capacity at constant pressure of the cold air, T g is the gas temperature on the flange side, h g is the convective heat transfer coefficient of the gas on the flange side, A is the heat transfer area on the gas side of the flange, T c is the cold air inlet temperature of the microtube array, h c is the convective heat transfer coefficient of the cold air, n is the number of microtubes, and λ is the thermal conductivity of the cooling air.

[0030] Furthermore, the temperature parameters of the turbine guide vane flange meet the predetermined temperature standard, including:

[0031] If the highest temperature of the turbine guide vane flange is higher than the heat-resistant grade of the metal material it uses, the predetermined temperature standard is: the highest temperature of the turbine guide vane flange is lower than the heat-resistant grade of the metal material it uses; if the highest temperature of the turbine guide vane flange is lower than the heat-resistant grade of the metal material it uses, the predetermined temperature standard is: the highest temperature of the turbine guide vane flange is reduced by no less than 10°C.

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

[0033] Reducing the distance from the center line of the micro bamboo joint-shaped tube to the flow-through surface of the guide vane flange, increasing the number of microtube rows, increasing the diameter of the microtubes in the microtube rows, and increasing the number of bamboo joint shapes in each microtube row.

[0034] Furthermore, for the cooling of the transverse single-row bamboo joint-shaped microtube array of the turbine guide vane flange, the diameter of the cooling circular tube section of the microtube array is taken as 0.4 mm to 0.8 mm, and the diameter of the bamboo joint tube is taken as 1.3 times to 1.7 times the diameter of the circular tube section.

[0035] Furthermore, for the cooling of the transverse single-row bamboo joint-shaped microtube array of the turbine guide vane flange, reducing the diameter of the circular tubes of the microtube array and delivering the cooling air to any position of the turbine guide vane flange to achieve precise customized delivery of the cooling requirements of the turbine guide vane flange and targeted cooling of the high-temperature area of the turbine guide vane flange.

[0036] Further, the three-dimensional modeling software for the computational domain uses UG NX software, the full three-dimensional fluid-thermal coupling calculation and analysis software uses CFX and Fluent software, and the mesh generation uses ICEM CFD software.

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

[0038] As can be seen from the above solution, the embodiment of the present invention provides a design method for the cooling structure of the turbine guide vane edge plate with a bamboo-joint-shaped microtube array. By determining the cooling structure of the turbine guide vane body, performing a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane, and determining that the temperature parameters of the turbine guide vane body meet the predetermined temperature standard; determining the position of the high-temperature area in the turbine guide vane edge plate where the cooling structure is to be arranged, and giving the cooling structure parameters of the transverse single-row bamboo-joint-shaped microtube array; constructing a three-dimensional model of the turbine guide vane with a cooling structure of a transverse single-row bamboo-joint-shaped microtube array on the edge plate and a cooling structure on the vane body; 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 the temperature field distribution information of the turbine guide vane edge plate; performing a full three-dimensional fluid-thermal coupling calculation and analysis on the overall turbine guide vane body and edge plate 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 standard, the design of the cooling structure of the turbine guide vane edge plate with a bamboo-joint-shaped microtube array is completed. The technical solution of the present invention can solve the problems that the turbine guide vane edge plate of the gas turbine is affected by the transverse secondary flow in the end region and the limitation of the structural size space, and it is difficult for the cooling air to cover, resulting in the ablation of the blade edge plate, and avoid the problem that the blade operates at an over-temperature and causes the blade to fail and cannot work. Description of the Drawings

[0039] Figure 1 It shows a flow chart of a design method for the cooling structure of the turbine guide vane edge plate with a bamboo-joint-shaped microtube array according to an embodiment of the present invention. Detailed Embodiments

[0040] To make the objectives, technical solutions, and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Apparently, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0041] As Figure 1 shown, Figure 1 It shows a flow chart of a design method for the cooling structure of the turbine guide vane edge plate with a bamboo-joint-shaped microtube array according to an embodiment of the present invention.

[0042] In the figure, a design method for the cooling structure of the turbine guide vane edge plate with a bamboo-joint-shaped microtube array includes:

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

[0044] In an embodiment of the present invention, based on the external shape obtained from the turbine aerodynamic design, the cooling structure design of the turbine guide vane blade is carried out. Among them, the cooling structure design such as film cooling is not carried out on the guide vane edge plate for the time being, and the cooling structure of the guide vane blade is obtained.

[0045] According to the inlet and outlet boundary conditions of the turbine guide vane, a three-dimensional model of the turbine guide vane is constructed, the grids of the fluid domain and the solid domain required for the full three-dimensional calculation are divided, and a full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane is carried out to obtain the temperature field distribution and data of the turbine guide vane edge plate, which are used as the basis for subsequent analysis and comparison after the design of the bamboo-shaped microtube array cooling is adopted;

[0046] Obtain the convective heat transfer coefficient h s,yb and the convective heat transfer amount as the boundary conditions for subsequent analysis.

[0047] If the temperature parameters of the turbine guide vane blade meet the predetermined temperature standard, that is, the highest temperature T Sblade,max of the turbine guide vane blade is lower than the temperature resistance level T S-M of the metal material used, T Sblade,max <T S-M , then execute S102; otherwise, re-determine the cooling structure of the turbine guide vane blade until the temperature parameters of the turbine guide vane blade reach the predetermined standard.

[0048] S102. According to the temperature field distribution and data of the turbine guide vane edge plate, determine the position of the high-temperature area in the turbine guide vane edge plate where the bamboo-shaped microtube array cooling structure is to be arranged.

[0049] In an embodiment of the present invention, the specific positions where the turbine guide vane edge plate needs to be strengthened in cooling will be arranged with a bamboo-shaped microtube array cooling structure at these high-temperature positions subsequently.

[0050] S103. According to the surface structure of the guide vane edge plate, combined with the structural dimension parameters of the guide vane edge plate including at least thickness, width, and length, give the parameters of the transverse single-row bamboo-shaped microtube array cooling structure.

[0051] In an embodiment of the present invention, on the basis of determining the specific positions of the turbine guide vane edge plates that need to be cooled, according to the structural characteristics of the surface of the turbine guide vane edge plates being approximately parallelogram-shaped, and in combination with structural dimension parameters such as the thickness, width, and length of the guide vane edge plates, cooling structure parameters of a transverse single-row bamboo-joint-shaped microtube array are given: the positions of the centerlines of the micro bamboo-joint-shaped tubes arranged along the thickness direction of the guide vane edge plates, the positions of the centerlines of the micro bamboo-joint-shaped tubes arranged along the width direction of the guide vane edge plates, the number of rows of micro bamboo-joint-shaped tubes arranged along the width direction of the guide vane edge plates, the tube diameters and lengths of each row of microtubes, and the paths of each microtube arranged along the length direction of the guide vane edge plates;

[0052] Among them, the position of the centerline of the micro bamboo-joint-shaped tube arranged along the thickness direction of the guide vane edge plate is the distance from the centerline of the micro bamboo-joint-shaped tube to the flow-through surface of the edge plate; the position of the centerline of the micro bamboo-joint-shaped tube arranged along the width direction of the guide vane edge plate is the distance from the centerline of the micro bamboo-joint-shaped tube to the side surface of the edge plate; the tube diameters of the microtube rows include the through-tube diameters and the bamboo-joint diameters.

[0053] S104. Set micro circular tube rows and bamboo-joint-shaped bulges on the guide vane edge plates to construct a three-dimensional model of a turbine guide vane with a cooling structure of a transverse single-row bamboo-joint-shaped microtube array on the edge plate and a cooling structure on the blade body.

[0054] In an embodiment of the present invention, based on the three-dimensional model of the turbine guide vane, using the given cooling structure parameters of the transverse single-row bamboo-joint-shaped microtube array, set bamboo-joint-shaped microtube rows on the guide vane edge plates to construct a three-dimensional model of a turbine guide vane with a cooling structure of a transverse single-row bamboo-joint-shaped microtube array on the edge plate and a cooling structure on the blade body.

[0055] S105. Extract the three-dimensional model of the turbine guide vane edge plate with a cooling structure of a transverse single-row bamboo-joint-shaped microtube array, 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 the 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 bamboo-joint-shaped 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 the embodiment of the present invention, a three-dimensional model of the turbine guide vane flange with a transverse single-row bamboo-shaped microtube array with flanges is meshed to divide the fluid domain and solid domain meshes required for full three-dimensional calculation, and based on the temperature field distribution and data of the turbine guide vane flange, the Nusselt number of convective heat transfer of the turbine guide vane flange, the convective heat transfer coefficient of the turbine guide vane flange, as well as the cooling air flow rate, the temperature and pressure boundary conditions at the inlet and outlet of the cooling air, a full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane flange is carried out to obtain the temperature field distribution and data of the guide vane flange;

[0058] Among them, the Nusselt number is:

[0059]

[0060] The convective heat transfer coefficient is:

[0061]

[0062] The cooling air flow rate is:

[0063]

[0064] Among them, the Reynolds number Re = uD / ν, the Prandtl number Pr = ν / α, u is the fluid velocity at the inlet of the microtube, ν is the kinematic viscosity of the fluid, D is the straight pipe diameter, α is the thermal diffusivity, L is the straight pipe length, m is the flow and heat transfer power exponent, n ZJ is the number of bamboo joints of each microtube, l is the length of each bamboo joint, d is the diameter of the bamboo joint, G is the total mass flow rate of the microtube array, Q s,yb is the heat transferred from the gas to the flange, Cp is the specific heat capacity at constant pressure of the cold air, T g is the gas temperature on the flange side, h g is the convective heat transfer coefficient of the gas on the flange side, A is the heat transfer area on the gas side of the flange, T c is the cold air inlet temperature of the microtube array, h c is the convective heat transfer coefficient of the cold air, n is the number of microtubes, and λ is the thermal conductivity of the cooling air.

[0065] If the highest temperature of the turbine guide vane flange is higher than the temperature resistance level of the metal material used, the predetermined temperature standard is: the highest temperature of the turbine guide vane flange is lower than the temperature resistance level of the metal material used; if the highest temperature of the turbine guide vane flange is lower than the temperature resistance level of the metal material used, the predetermined temperature standard is: the highest temperature of the turbine guide vane flange is reduced by no less than 10 °C.

[0066] In an embodiment of the present invention, adjusting the cooling structure parameters of the horizontal single-row bamboo-shaped micro-tube array includes: reducing the distance from the center line of the micro-bamboo-shaped tube to the flow surface of the guide vane edge plate, increasing the number of the micro-tube rows, increasing the diameter of the microtubes in the micro-tube rows, and increasing the number of bamboo-shaped tubes in each micro-tube 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 bamboo-shaped 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 the bamboo-shaped 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 bamboo-shaped micro-tube array cooling structure is 0.4mm to 0.8mm, and the diameter of the bamboo tube is 1.3 to 2 times the diameter of the circular tube section. The smaller diameter micro-tube array, combined with the bamboo-shaped enhanced cooling structure, is conducive to doubling the heat exchange area of the cooling channel and doubling the convective heat transfer coefficient, thereby achieving super cooling of the edge plate. Obviously, through the bamboo-shaped micro-tube array, 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 end zone lateral secondary flow and spatial structure limitations, which makes it difficult for the air film to cover the cooling "dead zone", will no longer exist, and the cooling and temperature reduction requirements of the gas turbine high-pressure turbine guide vane edge plate can be more easily met.

[0069] In another embodiment of the present invention, the turbine guide vane edge plate is cooled by a horizontal single row of bamboo-shaped micro-tube arrays. By reducing the diameter of the circular tubes of the micro-tube array (to a minimum of 0.1 mm), the cooling air is delivered to any position of the guide vane edge plate, thereby achieving precise customized delivery to meet the cooling needs of the edge plate, and by enhancing cooling through smaller-scale bamboo-shaped pipes (to a minimum of 0.15 mm), the high-temperature area of the edge plate can be cooled in a targeted manner.

[0070] In this embodiment of the present invention, the film hole cooling structure on the guide vane edge plate is eliminated, which helps to reduce the impact of the edge plate film cooling on the main flow, reduce mixing losses, and improve turbine efficiency. In addition, the hollow structure inside the guide vane edge plate can reduce the weight of the guide vane by 2%.

[0071] 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.

[0072] In the embodiments of the present invention, on the basis of making full use of the conventional three-dimensional flow and heat coupling calculation method for turbine guide vanes, according to the structural characteristics of the shroud of the high-pressure turbine guide vane of a gas turbine, and focusing on the high-temperature area of the shroud of the high-pressure turbine guide vane, the cooling structure design of the shroud and the temperature field calculation process are reorganized. A transverse single-row bamboo-shaped microtube array cooling design method suitable for the shroud of the high-pressure turbine guide vane of a gas turbine is proposed, and an efficient cooling structure design method for the shroud of the high-pressure turbine guide vane is obtained, solving the problem that it is difficult to cool the shroud of the high-pressure turbine guide vane of a gas turbine. Through microtube rows with a smaller diameter (0.1 mm - 1 mm), combined with a bamboo-shaped enhanced cooling structure, the heat transfer area and convective heat transfer coefficient of the cooling channels are increased several times, thereby realizing the super cooling of the shroud. It can not only achieve full coverage of the cooling of the shroud of the high-pressure turbine guide vane, but also fully meet the cooling requirements of the shroud. Therefore, the film cooling of the shroud can be cancelled, effectively solving the problem of the "dead zone" of film cooling that is difficult to cover due to the influence of the end region transverse secondary flow near the shroud and the limitation of the space structure in the traditional film cooling structure, and further effectively solving the problem of the ablation of the blade shroud.

[0073] In the embodiments of the present invention, the cooling air is transported to any position of the shroud of the guide vane through a bamboo-shaped microtube array, realizing the precise customized transportation of the cooling requirements of the shroud, and specifically cooling the high-temperature area of the shroud, meeting the local cooling and temperature reduction requirements of the shroud of the guide vane. The technical solution of the present invention can give full play to the better cooling effect of the bamboo-shaped microtube array, cancel the film hole cooling structure of the shroud of the guide vane, thereby weakening the influence of the film cooling of the shroud on the mainstream, being beneficial to reducing the mixing loss of heat and cold of the shroud of the turbine guide vane, and improving the turbine efficiency.

[0074] The cooling structure of the shroud of the guide vane designed by the technical solution of the present invention directly discharges the cooling air from the rear side of the shroud of the guide vane, which is not only beneficial to the cooling of the downstream moving blades, but also beneficial to the sealing between the guide vane and the shroud of the moving blade, avoiding the "invasion" of gas into the disk cavity of the high-pressure turbine disk. Among them, the inside of the shroud of the turbine blade adopts a hollow structure, which is beneficial to reducing the weight of the guide vane and improving the power-to-weight ratio of the engine.

[0075] In one embodiment of the present invention, a design method for a cooling structure of a turbine guide vane shroud with a bamboo-shaped microtube array includes:

[0076] Step 1: Determine the cooling structure of the blade body of the turbine guide vane. On the basis of the outer shape of the guide vane obtained by turbine aerodynamic design, carry out the cooling structure design of the blade body of the turbine guide vane, and do not carry out cooling structure designs such as film cooling on the shroud of the guide vane for the time being, to obtain a three-dimensional model of the guide vane with a cooling structure;

[0077] Step 2: Conduct a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane. According to the inlet and outlet boundary conditions of the turbine guide vane, import the constructed three-dimensional model of the guide vane into the mesh generation program, divide the grids of the fluid domain and solid domain required for the full three-dimensional calculation, and then 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 guide vane, obtaining the temperature field distribution and data of the turbine guide vane shroud plate as the basis for subsequent analysis and comparison after the design of the bamboo-shaped microtube array cooling, obtaining the convective heat transfer coefficient of the turbine guide vane shroud plate as the boundary condition for subsequent analysis, and obtaining the temperature field distribution and data of the vane body of the turbine guide vane.

[0078] If the temperature parameters of the vane body of the turbine guide vane meet the predetermined temperature standard, that is, the highest temperature of the vane body of the turbine guide vane is lower than the temperature resistance grade of the used metal material, then proceed to the next step; if it does not meet the predetermined standard, repeat the above steps until the temperature parameters of the vane body of the guide vane reach the predetermined standard;

[0079] Step 3: Determine the positions on the turbine guide vane shroud plate that need enhanced cooling. Based on the temperature field distribution and data of the guide vane shroud plate, judge the positions where the guide vane shroud plate exceeds the temperature resistance grade of the metal material or the high-temperature areas of the shroud plate, and determine the specific positions on the guide vane shroud plate that need enhanced cooling. Subsequently, a bamboo-shaped microtube array cooling structure will be arranged at these high-temperature positions;

[0080] Step 4: Specify the cooling parameters of the bamboo-shaped microtube array for the turbine guide vane shroud plate. On the basis of determining the specific positions on the guide vane shroud plate that need cooling in Step 3, according to the structural characteristics of the approximate parallelogram on the surface of the guide vane shroud plate, combined with the structural dimension parameters such as the thickness, width, and length of the guide vane shroud plate, specify the cooling structure parameters of the transverse single-row bamboo-shaped microtube array: the position of the center line of the micro-bamboo-shaped tube row set along the thickness direction of the shroud plate (the distance H from the flow-through surface of the shroud plate), the position of the center line of the micro-bamboo-shaped tube row set along the width direction of the shroud plate (the distance W from the side surface of the shroud plate), the number N or the distance Lk of the micro-bamboo-shaped tube rows set along the width direction of the shroud plate, the pipe diameters of the microtube rows (the through-pipe diameter φ and the bamboo-joint diameter ψ), and the path of each microtube set along the length direction of the shroud plate;

[0081] Step 5: Construct the overall three-dimensional model of the turbine guide vane with a bamboo-shaped microtube array cooling structure on the shroud plate. Based on the three-dimensional model of the guide vane with a cooling structure, use the specified cooling structure parameters of the transverse single-row bamboo-shaped microtube array to set the bamboo-shaped microtube rows on the guide vane shroud plate, construct a three-dimensional model of the turbine guide vane with a transverse single-row bamboo-shaped microtube array cooling structure on the shroud plate and a cooling structure on the vane body, and connect the cooling channels through and through by setting hollow micro-connection pipes at the positions of the blade cavities;

[0082] Step 6: Establish a 3D fluid-thermal coupling calculation model for the cooling of the flange bamboo-joint-shaped microtube array. Using the 3D model of the turbine guide vane, ignoring the cooling structure of the vane body, only using the outer shape of the vane body, extract only the turbine guide vane flange model with a transverse single-row bamboo-joint-shaped microtube array cooling structure on the flange;

[0083] Step 7: Perform a full 3D fluid-thermal coupling calculation and analysis of the turbine guide vane flange. Import the established 3D fluid-thermal coupling calculation model for the cooling of the flange bamboo-joint-shaped microtube array of the turbine guide vane into the mesh generation program, generate the full 3D calculation mesh, and based on the temperature and convective heat transfer coefficient of the turbine guide vane flange and vane body, as well as the temperature and pressure boundary conditions at the inlet and outlet of the cooling air, 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 flange to obtain the temperature field distribution and data of the guide vane flange;

[0084] If the temperature parameters of the turbine guide vane flange meet the predetermined temperature standard (if the highest temperature of the turbine guide vane flange is higher than the temperature resistance level of the metal material used, the predetermined temperature standard is: the highest temperature of the turbine guide vane flange is lower than the temperature resistance level of the metal material used; if the highest temperature of the turbine guide vane flange is lower than the temperature resistance level of the metal material used, the predetermined temperature standard is: the highest temperature of the turbine guide vane flange is reduced by no less than 10 °C), then proceed to the next step; if not meeting the predetermined standard, adjust the parameters of the transverse single-row bamboo-joint-shaped microtube array cooling structure (reduce the distance from the center line to the flow-through surface of the flange, increase the number of microtube rows, increase the diameter of the microtubes, increase the number of bamboo joints in each microtube row), and repeat Steps 4 to 7 until the temperature parameters of the turbine guide vane flange reach the predetermined standard;

[0085] Step 8: Perform a full 3D fluid-thermal coupling calculation and analysis of the entire vane body and flange of the guide vane. Using the same inlet and outlet boundary conditions of the turbine guide vane as in Step 2, import the overall 3D model of the turbine guide vane with the bamboo-joint-shaped microtube array cooling structure on the flange constructed in Step 5 into the mesh generation program, generate the grids for the fluid domain and solid domain required for the full 3D calculation, and then 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 to obtain the temperature field distribution and data of the turbine guide vane (including the vane body and flange) after adding the bamboo-joint-shaped microtube array cooling structure.

[0086] If the temperature parameters of the turbine guide vane (including the vane body and flange) obtained in Step 8 meet the predetermined temperature standard, then proceed to the next step; if not meeting the predetermined standard, repeat Steps 1 to 8 until the temperature parameters of the turbine guide vane reach the predetermined standard.

[0087] In another embodiment of the present invention, different from the above embodiments, a design method for the cooling structure of a turbine guide vane edge plate with a bamboo-joint-shaped microtube array is provided. The diameter of the cooling round tubes in the bamboo-joint-shaped microtube array cooling structure usually ranges from 0.1 mm to 1 mm. The microtube rows with a smaller diameter, combined with the bamboo-joint-shaped enhanced cooling structure, are beneficial to doubling the heat transfer area of the cooling channels and doubling the convective heat transfer coefficient at the same time, thereby achieving super cooling of the edge plate. Obviously, through the bamboo-joint-shaped microtube array, not only can the full coverage of the cooling of the high-pressure turbine guide vane edge plate be realized, but also the cooling requirements of the edge plate can be fully met. Therefore, the film cooling of the edge plate can be cancelled, and the problem that the film cooling is difficult to cover the cooling "dead zone" due to the influence of the end-region lateral secondary flow and the spatial structure limitation in the traditional edge plate film cooling will no longer exist, and it is easier to meet the cooling and temperature reduction requirements of the high-pressure turbine guide vane edge plate of the gas turbine.

[0088] In another embodiment of the present invention, a design method for the cooling structure of a turbine guide vane edge plate with a bamboo-joint-shaped microtube array is provided. Different from the above two embodiments, in the lateral single-row bamboo-joint-shaped microtube array cooling of the turbine guide vane edge plate, the diameter of the round tubes in the microtube array can be reduced (the minimum can reach 0.1 mm), and the cooling air can be conveyed to any position of the guide vane edge plate, so as to realize the precise customized delivery of the cooling requirements of the edge plate. And through the enhanced cooling of the bamboo-joint-shaped pipes with a smaller scale (the minimum can reach 0.15 mm), the high-temperature area of the edge plate can be cooled targeted.

[0089] In another embodiment of the present invention, a lateral single-row bamboo-joint-shaped microtube array cooling of a turbine guide vane edge plate cancels the film hole cooling structure of the guide vane edge plate, which is beneficial to weakening the influence of the edge plate film cooling on the main flow, reducing the mixing loss, and improving the turbine efficiency.

[0090] In another embodiment of the present invention, a design method for the cooling structure of a turbine guide vane edge plate with a bamboo-joint-shaped microtube array is provided. Different from the above four embodiments, in the lateral single-row bamboo-joint-shaped microtube array cooling of the turbine guide vane edge plate, the inside of the guide vane edge plate is a hollow structure, which can reduce the weight of the guide vane by 2%.

[0091] A design method for the cooling structure of a turbine guide vane edge plate with a bamboo-joint-shaped microtube array proposed by the present invention has universality and is not limited to the design of the high-pressure turbine guide vane of a gas turbine, but also applicable to the design of the high-pressure turbine guide vane of an aeroengine.

[0092] The above are the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art in this technical field, without departing from the principle of the present invention, several improvements and refinements can still be made, and these improvements and refinements should also be regarded as the protection scope of the present invention.

Claims

1. A design method for a turbine guide vane edge plate cooling structure with a bamboo-shaped microtube array, characterized in that, The described design method includes: S101. Determine the cooling structure of the turbine guide vane blade body, conduct a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane, and ensure that the temperature parameters of the turbine guide vane blade body meet the predetermined temperature standard. S102. Based on the temperature field distribution and data of the turbine guide vane flange, determine the position of the high-temperature area in the turbine guide vane flange where the bamboo joint-shaped microtube array cooling structure is to be arranged. S103. Given the cooling structure parameters of the transverse single-row bamboo joint-shaped microtube array according to the surface structure of the guide vane flange, in combination with the structural dimension parameters of the guide vane flange including at least thickness, width, and length. S104. Set up a bamboo joint-shaped microtube row on the guide vane flange to construct a three-dimensional model of the turbine guide vane with a transverse single-row bamboo joint-shaped microtube array cooling structure on the flange. S105. Extract the three-dimensional model of the turbine guide vane flange with a transverse single-row bamboo joint-shaped microtube array cooling structure on the flange, and conduct a full three-dimensional fluid-thermal coupling calculation and analysis on the three-dimensional model of the turbine guide vane flange to obtain the temperature field distribution information of the turbine guide vane flange. S106. If the temperature parameters of the turbine guide vane flange meet the predetermined temperature standard, proceed to the next step; otherwise, adjust the cooling structure parameters of the transverse single-row bamboo joint-shaped microtube array, and repeat S103 to S105 until the temperature parameters of the turbine guide vane flange reach the predetermined temperature standard. S107. Conduct a full three-dimensional fluid-thermal coupling calculation and analysis on the entire turbine guide vane blade body and flange to obtain the temperature field distribution information of the turbine guide vane with a bamboo joint-shaped microtube array cooling structure on the flange. If the temperature parameters of the turbine guide vane meet the predetermined temperature standard, the cooling structure design of the turbine guide vane flange with a bamboo joint-shaped microtube array is completed; otherwise, repeat steps S101 to S107 until the temperature parameters of the turbine guide vane reach the predetermined temperature standard.

2. A design method for a turbine guide vane edge plate cooling structure with a bamboo-joint-shaped microtube array according to claim 1, characterized in that, Conduct a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane, and ensure that the temperature parameters of the turbine guide vane blade body meet the predetermined temperature standard, including: Construct a three-dimensional model of the turbine guide vane, divide the grids of the fluid domain and solid domain required for the full three-dimensional calculation, conduct a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane to obtain the temperature field distribution and data of the turbine guide vane flange. Obtain the convective heat transfer coefficient h of the flow-through surface of the turbine guide vane edge plate s,yb and the convective heat transfer amount as the boundary condition for subsequent analysis; If the temperature parameter of the turbine guide vane blade body meets the predetermined temperature standard, that is, the highest temperature T of the turbine guide vane blade body Sblade,max is 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 the predetermined standard.

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

4. A design method for a turbine guide vane edge plate cooling structure with a bamboo-shaped microtube array according to claim 1, characterized in that, Extract the three-dimensional model of the turbine guide vane edge plate with a single-row transverse bamboo-shaped microtube array with flanges, 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 the temperature field distribution information of the turbine guide vane edge plate, including: Perform mesh generation on the three-dimensional model of the turbine guide vane edge plate with a single-row transverse bamboo-shaped microtube array with flanges, divide the grids of the fluid domain and solid domain required for the full three-dimensional calculation, and perform a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane edge plate according to the temperature field distribution and data of the turbine guide vane edge plate, the Nusselt number of convective heat transfer of the turbine guide vane edge plate, the convective heat transfer coefficient of the turbine guide vane edge plate, as well as the cooling air flow rate and the temperature and pressure boundary conditions at the inlet and outlet of the cooling air, to obtain the temperature field distribution and data of the guide vane edge plate; Among them, the Nusselt number is: The convective heat transfer coefficient is: The cooling air flow rate is: Among them, the Reynolds number Re = uD / ν, the Prandtl number Pr = ν / α, u is the fluid velocity at the inlet of the microtube, ν is the kinematic viscosity coefficient of the fluid, D is the diameter of the straight tube, α is the thermal diffusivity, L is the length of the straight tube, m is the flow and heat transfer power exponent, n ZJ is the number of bamboo joints of each microtube, l is the length of each bamboo joint, d is the diameter of the bamboo joint, G is the total mass flow rate of the microtube array, Q s,yb is the heat transferred from the gas to the flange, Cp is the specific heat capacity at constant pressure of the cold air, T g is the gas temperature on the flange side, h g is the convective heat transfer coefficient of the gas on the flange side, A is the heat transfer area on the gas side of the flange, T c is the cold air inlet temperature of the microtube array, h c is the convective heat transfer coefficient of the cold air, n is the number of microtubes, and λ is the thermal conductivity of the cooling air.

5. A design method for a turbine guide vane leading edge cooling structure with a bamboo-shaped microtube array according to claim 1, characterized in that The temperature parameters of the turbine guide vane edge plate meet the predetermined temperature standard, including: If the highest 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 highest temperature of the turbine guide vane edge plate is lower than the temperature resistance grade of the metal material used; if the highest 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 highest temperature of the turbine guide vane edge plate is reduced by no less than 10 °C.

6. A design method for a turbine vane leading edge cooling structure with a bamboo-shaped microtube array according to claim 1, characterized in that Adjust the cooling structure parameters of the single-row transverse bamboo-shaped microtube array, including: Reduce the distance from the center line of the bamboo-shaped microtube to the flow-through surface of the guide vane edge plate, increase the number of the microtube rows, increase the diameter of the microtubes in the microtube rows, and increase the number of bamboo shapes in each microtube row.

7. A design method for a turbine vane leading edge cooling structure with a bamboo-shaped microtube array according to claim 1, characterized in that, The diameter of the cooling circular tube section of the bamboo-shaped microtube array cooling structure ranges from 0.4 mm to 0.8 mm, and the diameter of the bamboo tube is 1.3 to 1.7 times the diameter of the circular tube section.

8. A design method for a turbine guide vane edge plate cooling structure with a bamboo-shaped microtube array according to claim 1, characterized in that, Cool the turbine guide vane edge plate with a single-row transverse bamboo-shaped microtube array, reduce the diameter of the circular tube of the microtube array, and deliver the cooling air to any position of the turbine guide vane edge plate to achieve precise customized delivery of the cooling requirements of the turbine guide vane edge plate, and cool the high-temperature area of the turbine guide vane edge plate specifically.

9. A design method for a turbine guide vane edge plate cooling structure with a bamboo-shaped microtube array according to claim 1, characterized in that, The three-dimensional modeling software for the calculation domain uses UG NX software, the full three-dimensional fluid-thermal coupling calculation and analysis software uses CFX and Fluent software, and the mesh generation uses ICEM CFD software.

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