Design method of micro-tube array cooling structure with bamboo-shaped bulge on guide vane

Abstract

The present invention provides a method for designing a micro-tube array cooling structure for a guide vane with a bamboo-shaped bulge. By constructing the turbine guide vane blade shape and internal cooling structure, the location of the turbine guide vane blade to be enhanced is determined. An overall three-dimensional model of the turbine guide vane with the bamboo-shaped bulge micro-tube array cooling structure is constructed, and the amount of cooling air reduction for the turbine guide vane blade is preset; the amount of blade thinning is determined, and the cooling parameters of the turbine guide vane blade, cooling structure, and bamboo-shaped bulge micro-tube array are adjusted; an overall three-dimensional model of the turbine guide vane with the bamboo-shaped micro-tube array cooling structure after blade thinning is constructed, and full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane blade is performed. If the turbine guide vane blade temperature parameters meet the predetermined temperature standards, the design is complete. The technical solution of the present invention can solve the problem that the high-pressure turbine guide vane blade of a gas turbine is limited by the structural size space and cooling air consumption, resulting in uneven blade temperature distribution, which in turn causes blade ablation, cracking, and other faults.

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 micro-tube array cooling structure of a guide vane with a bamboo-shaped bulge. 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 micro-tube array cooling structure for a guide vane with a bamboo-shaped bulge, which can solve the problem that the guide vane of a high-pressure turbine of a gas turbine is limited by the structural size space and the amount of cooling air used, resulting in uneven temperature distribution on the blade body, causing blade ablation, cracks and other faults, and avoid over-temperature operation of the blade, which causes the blade to fail and become unable to work.

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

[0007] S101. Determine a turbine guide vane cooling structure without micro-tube array cooling channels based on the turbine guide vane blade shape, perform a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane, and determine the temperature field distribution and data information of the guide vane blade to serve as a basis for subsequent analysis and comparison with a design using a micro-tube array cooling structure with bamboo-shaped bulges.

[0008] S102, determining a location of a high-temperature area in the turbine guide vane where an enhanced cooling structure is to be arranged;

[0009] S103. According to the surface structure of the guide vane, combined with the dimensional parameters of the guide vane including at least the wall thickness, the leading edge air film structure, and the trailing edge exhaust structure, the cooling structure parameters of the turbine guide vane with the bamboo-shaped bulge micro-tube array are determined.

[0010] S104, constructing an overall three-dimensional model of a turbine guide vane with a bamboo-shaped bulge micro-tube array cooling structure, and inferring the reduction in cooling air for the turbine guide vane blade body and the cooling air consumption of the turbine guide vane blade body after the bamboo-shaped bulge micro-tube array cooling structure is installed;

[0011] S105. Based on the overall 3D model of the turbine guide vane with a bamboo-shaped bulge micro-tube array cooling structure, the fluid and solid domains required for full 3D calculations were meshed. Full 3D fluid-thermal coupling calculations and analysis were performed to obtain the temperature field distribution and temperature data of the guide vane blade body.

[0012] S106. Determine an external thinning amount of the turbine guide vane based on a ratio of the cooling air reduction amount to an originally given cooling air usage amount;

[0013] S107. Reconstructing the cooling structure of the turbine guide vane based on the reduction ratio of the cooling channel area inside the turbine guide vane and the outer thickness of the blade, and using a three-dimensional modeling tool to create a three-dimensional model of the turbine guide vane and cooling channel after the blade profile is adjusted.

[0014] S108. Based on the three-dimensional model of the turbine guide vane after the blade profile adjustment and the reduction ratio of the cooling channel area inside the guide vane, adjust the positions of the bamboo-shaped microtubes in the root and top sections, the diameter of each circular channel tube, the center-to-center spacing of the channel tubes, the number of bamboo-shaped bulges in each microchannel along the blade height direction, the spacing between the bamboo-shaped bulges, the diameter of each bamboo-shaped bulge, and the cooling structure parameters of the bamboo-shaped bulge microtube array, including the number of microtube channels;

[0015] S109. Construct an overall three-dimensional model of the turbine guide vane with a bamboo-shaped micro-tube array cooling structure after the blade body is thinned, perform full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane blade body, and obtain the temperature field distribution and temperature data of the guide vane blade body; if the temperature parameters of the turbine guide vane blade body meet the predetermined temperature standards, the design process is completed; otherwise, adjust the thinning amount of the turbine guide vane blade body and the parameters of the bamboo-shaped bulge micro-tube array cooling structure, and repeat S106 to S108 until the temperature parameters of the turbine guide vane blade body meet the predetermined standards.

[0016] Furthermore, according to the surface structure of the guide vane blade, combined with the dimensional parameters of the guide vane blade including at least the blade wall thickness, the leading edge air film structure, and the trailing edge exhaust structure, the cooling structure parameters of the turbine guide vane blade with a bamboo-shaped bulge micro-tube array are given, including:

[0017] Based on the specific location of the turbine guide vane that requires enhanced cooling, the cooling structure parameters of the bamboo-shaped micro-tube array on the turbine guide vane are determined according to the thin and slender structure of the turbine guide vane, and the dimensional parameters including at least the turbine guide vane wall thickness, leading edge air film structure, and trailing edge exhaust structure.

[0018] Among them, in the root section, the distance H between the position of each microtube center along the blade wall thickness midline and the leading edge point of the blade wall thickness midline is h,i 、The diameter of each circular channel tube φ h,i , channel tube center distance L h,i ; In the top section, the distance H between the center of each microtube along the midline of the blade thickness and the leading edge of the midline of the blade thickness t,i 、The diameter of each circular channel tube φ t,i , through pipe center distance L t,i ; The number of bamboo-shaped bulges along the height direction of each microchannel is M j , bamboo-shaped bulge spacing G j,k The diameter of each bamboo-shaped bulge ψ j,k and length L j,k , the number of microtubule channels N.

[0019] Furthermore, based on the cooling air reduction amount ΔG cool Compared with the original given cooling air consumption G cool,ori The ratio of △G k =△G cool / G cool,ori , determine the outer thinning amount △Th of the turbine guide vane body, including:

[0020] The cooling air reduction amount ΔG cool Compared with the original given cooling air consumption G cool,ori The ratio of △G k =△G cool / G cool,ori, that is, the reduction ratio of the cooling channel area inside the turbine guide vane blade △A k =△G k On the basis of the original turbine guide vane blade internal cooling channel, a new turbine guide vane blade internal cooling channel is obtained by reducing the guide vane blade wall thickness, keeping the guide vane blade wall thickness unchanged, and offsetting the guide vane blade wall thickness outward in the new turbine guide vane blade internal cooling channel to obtain the blade body external thickness after adjusting the internal cooling channel, and the blade body external thickness after adjusting the internal cooling channel is Th. ori Compared with the blade thickness before adjustment Th new The difference is the blade body thinning amount △Th.

[0021] Furthermore, based on the overall 3D model of the turbine guide vane with a bamboo-shaped bulge micro-tube array cooling structure, the fluid domain and solid domain mesh required for full 3D calculations were divided to obtain the temperature field distribution and temperature data of the guide vane body, including:

[0022] The temperature field distribution and temperature data of the turbine guide vane blade body are compared and analyzed with the temperature field distribution and data information of the guide vane blade body. If the obtained temperature parameters of the turbine guide vane blade body meet the predetermined temperature standard, S106 is executed; otherwise, the cooling structure parameters of the bamboo-shaped blisters microtube array are adjusted by at least increasing the number of microtube rows or increasing the diameters of the microtubes and the bamboo-shaped blisters, and S104 to S105 are repeatedly executed until the temperature parameters of the turbine guide vane blade body reach the predetermined temperature standard.

[0023] Furthermore, the predetermined temperature standard includes:

[0024] If the maximum temperature of the turbine guide vane blade body 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 blade body is lower than the temperature resistance grade of the metal material used;

[0025] If the maximum temperature of the turbine guide vane blade body 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 blade body is reduced by not less than 20°C.

[0026] Furthermore, the bamboo-shaped micro-tube array cooling structure has a circular tube diameter between 0.2 mm and 0.4 mm. The micro-tube array cooperates with the bamboo-shaped enhanced cooling structure to increase the heat exchange area of ​​the cooling channel, increase the convection heat transfer coefficient, and achieve super cooling of the blade body; at the same time, it cooperates with the leading edge air film cooling of the turbine guide vane blade body to achieve full coverage of the cooling of the high-pressure turbine guide vane blade body.

[0027] Furthermore, the method comprises:

[0028] The bamboo-shaped micro-tube array cooling structure is arranged inside the metal wall of the blade body, which reduces the original internal cooling cavity, thins the guide vane blade line thickness, and reduces the heated area of ​​the turbine guide vane blade body.

[0029] Furthermore, determining the location of the high-temperature area in the turbine guide vane blade where the enhanced cooling structure is to be arranged includes:

[0030] Based on the temperature field distribution and temperature data of the guide vane blade, the location of the high-temperature area of ​​the turbine guide vane blade is determined, that is, the specific location of the turbine guide vane blade that needs to be focused on and enhanced cooling. Subsequently, bamboo-shaped micro-tube array cooling structures will be arranged in these high-temperature areas.

[0031] 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.

[0032] The beneficial effects brought about by the present invention are as follows:

[0033] It can be seen from the above scheme that an embodiment of the present invention provides a method for designing a micro-tube array cooling structure of a guide vane blade with a bamboo-shaped bulge. By constructing the external shape and internal cooling structure of the turbine guide vane blade, a turbine guide vane blade cooling structure without a micro-tube array cooling channel is designed, and the position of the turbine guide vane blade that requires enhanced cooling is determined. Given the parameters of the micro-tube array cooling structure of the bamboo-shaped bulge on the turbine guide vane blade, a three-dimensional model of the turbine guide vane with the micro-tube array cooling structure of the bamboo-shaped bulge is constructed, and the cooling air reduction amount of the turbine guide vane blade is preset. A full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane blade is performed to determine the thinning amount of the turbine guide vane blade body, and the parameters of the turbine guide vane blade, cooling structure, and micro-tube array cooling of the bamboo-shaped bulge are adjusted. A full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane blade after blade thinning is constructed, and the temperature field distribution information of the turbine guide vane blade is obtained. If the temperature parameters of the turbine guide vane blade meet the predetermined temperature standards, the design of the micro-tube array cooling structure of the turbine guide vane blade with the bamboo-shaped bulge is completed. The technical solution of the present invention can solve the problem that the blade body temperature distribution of the high-pressure turbine guide vane of a gas turbine is uneven due to the limitations of the structural size space and the amount of cooling air used, which causes blade ablation, cracking and other faults, and avoids the blade from overheating and causing blade failure. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 A flow chart showing a method for designing a micro-tube array cooling structure with bamboo-shaped bulges on a guide vane blade according to an embodiment of the present invention. DETAILED DESCRIPTION

[0035] 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.

[0036] like Figure 1 As shown, Figure 1 A flow chart showing a method for designing a micro-tube array cooling structure with bamboo-shaped bulges on a guide vane blade according to an embodiment of the present invention.

[0037] The figure shows a design method for a micro-tube array cooling structure with a guide vane having a bamboo-shaped bulge, including:

[0038] S101. Based on the outer shape of the turbine guide vane, determine the cooling structure of the turbine guide vane without a micro-tube array cooling channel, perform a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane, and determine the temperature field distribution and data information of the guide vane, which will serve as a basis for subsequent analysis and comparison after adopting a design with a bamboo-shaped bulge micro-tube array cooling structure.

[0039] In an embodiment of the present invention, a turbine guide vane airfoil shape is constructed. Based on the airfoil profile obtained from the turbine aerodynamic design, a 3D modeling tool is used to carry out the turbine guide vane airfoil shape structural design, thereby constructing a 3D shape of the turbine guide vane airfoil. A turbine guide vane airfoil cooling structure without micro-tube array cooling channels is designed. Based on the 3D shape of the turbine guide vane airfoil, the turbine guide vane airfoil cooling structure design is carried out (the bamboo-shaped bulge micro-tube array cooling structure design for the guide vane airfoil is not currently being carried out), thereby obtaining a 3D model of the turbine guide vane airfoil with a cooling structure (without the bamboo-shaped bulge micro-tube array cooling structure).

[0040] A full three-dimensional fluid-thermal coupling calculation and analysis is performed on the turbine guide vanes. According to the inlet and outlet boundary conditions of the turbine guide vanes, the constructed three-dimensional model of the turbine guide vanes with a blade cooling structure is imported into the meshing program to divide the fluid domain and solid domain meshes required for the full three-dimensional calculation. Then, the full three-dimensional fluid-thermal coupling calculation and analysis program is used to carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vanes, and the temperature field distribution and data of the guide vanes are obtained as a basis for subsequent analysis and comparison after adopting the design of a cooling structure with a bamboo-shaped bulge micro-tube array.

[0041] S102: Determine the location of the high-temperature area in the turbine guide vane where the enhanced cooling structure is to be arranged.

[0042] In an embodiment of the present invention, based on the temperature field distribution and temperature data of the guide vane blade, the position of the high-temperature area of ​​the turbine guide vane blade is determined, that is, the specific position of the turbine guide vane blade that requires focused enhanced cooling. After obtaining the specific position of the guide vane blade that requires focused enhanced cooling, the bamboo-shaped micro-tube array cooling structure will be arranged in these high-temperature areas.

[0043] S103. According to the surface structure of the guide vane blade, combined with the dimensional parameters of the guide vane blade including at least the blade wall thickness, the leading edge air film structure, and the trailing edge exhaust structure, the cooling structure parameters of the turbine guide vane blade with the bamboo-shaped bulge micro-tube array are determined.

[0044] In an embodiment of the present invention, based on the specific location of the turbine guide vane requiring enhanced cooling, according to the thin and slender structural characteristics of the turbine guide vane, and in combination with dimensional parameters including at least the turbine guide vane wall thickness, leading edge air film structure, and trailing edge exhaust structure, the cooling structure parameters of the turbine guide vane with bamboo-shaped bulge micro-tube array are determined.

[0045] Among them, in the root section, the distance H between the position of each microtube center along the blade wall thickness midline and the leading edge point of the blade wall thickness midline is h,i 、The diameter of each circular channel tube φ h,i , channel tube center distance L h,i ; In the top section, the distance H between the center of each microtube along the midline of the blade thickness and the leading edge of the midline of the blade thickness t,i 、The diameter of each circular channel tube φ t,i , through pipe center distance L t,i ; The number of bamboo-shaped bulges along the height direction of each microchannel is M j , bamboo-shaped bulge spacing G j,k The diameter of each bamboo-shaped bulge ψ j,k and length L j,k , the number of microtubule channels N.

[0046] S104. Construct an overall three-dimensional model of a turbine guide vane with a bamboo-shaped bulge micro-tube array cooling structure, and infer the reduction in cooling air for the turbine guide vane blade body and the cooling air consumption of the turbine guide vane blade body after the bamboo-shaped bulge micro-tube array cooling structure is installed.

[0047] In an embodiment of the present invention, a three-dimensional model of a turbine guide vane with a cooling structure is provided (without a bamboo-shaped bulge microtube array cooling structure). Using the given parameters of the bamboo-shaped microtube array cooling structure of the turbine guide vane blade, a three-dimensional modeling tool is used to mix the root section and top section microtube array channels using the mixing function to construct a circular microtube row on the turbine guide vane blade. On this basis, a bamboo-shaped bulge structure is added using the rotation or stretching function to obtain a three-dimensional model of a turbine guide vane with a bamboo-shaped bulge microtube array cooling structure.

[0048] Based on the given parameters of the bamboo-shaped bulge micro-tube array cooling structure of the turbine guide vane, its heat exchange cooling effect is evaluated. Based on this, the reduction in cooling air for the turbine guide vane and the cooling air consumption of the turbine guide vane with the bamboo-shaped bulge micro-tube array cooling structure are preliminarily inferred.

[0049] S105. Based on the overall three-dimensional model of the turbine guide vane with a bamboo-shaped bulge micro-tube array cooling structure, the fluid domain and solid domain meshes required for full three-dimensional calculations are divided, and full three-dimensional fluid-thermal coupling calculation and analysis are carried out to obtain the temperature field distribution and temperature data of the guide vane blade body.

[0050] In an embodiment of the present invention, based on the reduction in cooling air and combined with the remaining inlet and outlet boundary conditions of the turbine guide vane, the constructed overall three-dimensional model of the turbine guide vane with a bamboo-shaped bulge micro-tube array cooling structure is imported into a meshing program to divide the fluid domain and solid domain meshes required for the full three-dimensional calculation. Then, a full three-dimensional fluid-thermal coupling calculation and analysis program is used to carry out full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane blade body to obtain the temperature field distribution and temperature data of the guide vane blade body.

[0051] The temperature field distribution and temperature data of the turbine guide vane blade body are compared and analyzed with the temperature field distribution and data information of the guide vane blade body. If the obtained temperature parameters of the turbine guide vane blade body meet the predetermined temperature standard, S106 is executed; otherwise, the cooling structure parameters of the bamboo-shaped blisters microtube array are adjusted by at least increasing the number of microtube rows or increasing the diameters of the microtubes and the bamboo-shaped blisters, and S104 to S105 are repeatedly executed until the temperature parameters of the turbine guide vane blade body reach the predetermined temperature standard.

[0052] Wherein, the predetermined temperature standard includes:

[0053] If the maximum temperature of the turbine guide vane blade body 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 blade body is lower than the temperature resistance grade of the metal material used;

[0054] If the maximum temperature of the turbine guide vane blade body 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 blade body is reduced by not less than 20°C.

[0055] S106, based on the cooling air reduction amount ΔG cool Compared with the original given cooling air consumption G cool,ori The ratio of △G k =△G cool / G cool,ori , determine the external thinning amount △Th of the turbine guide vane blade.

[0056] The cooling air reduction amount ΔG cool Compared with the original given cooling air consumption G cool,ori The ratio of △Gk =△G cool / G cool,ori , that is, the reduction ratio of the cooling channel area inside the turbine guide vane blade △A k =△G k On the basis of the original turbine guide vane blade internal cooling channel, a new turbine guide vane blade internal cooling channel is obtained by reducing the guide vane blade wall thickness, keeping the guide vane blade wall thickness unchanged, and offsetting the guide vane blade wall thickness outward in the new turbine guide vane blade internal cooling channel to obtain the blade body external thickness after adjusting the internal cooling channel, and the blade body external thickness after adjusting the internal cooling channel is Th. ori Compared with the blade thickness before adjustment Th new The difference is the blade body thinning amount △Th.

[0057] S107. Based on the reduction ratio of the cooling channel area inside the turbine guide vane blade and the outer thickness of the blade, the cooling structure of the turbine guide vane blade is reconstructed, and a three-dimensional model of the turbine guide vane blade and cooling channel after the blade shape is adjusted is established using a three-dimensional modeling tool.

[0058] S108. Based on the three-dimensional model of the turbine guide vane blade body after the blade profile is adjusted and the reduction ratio of the cooling channel area inside the guide vane blade body, adjust the positions of the bamboo-shaped microtubes in the root section and the top section, the diameter of each circular channel tube, the center spacing of the channel tubes, the number of bamboo-shaped bulges in each microchannel along the blade height direction, the spacing between the bamboo-shaped bulges, the diameter of each bamboo-shaped bulge, and the cooling structure parameters of the bamboo-shaped bulge microtube array including the number of microtube channels.

[0059] In the embodiment of the present invention, based on the given parameters of the cooling structure of the bamboo-shaped micro-tube array of the turbine guide vane blade, the positions of the root section and the top section of the micro-bamboo-shaped tubes (H h,i 、H t,i ), diameter of each circular channel tube (φ h,i 、φ t,i ), channel tube center distance (L h,i , L t,i ), the number of bamboo bulges along the height direction of each microchannel is M j , bamboo bulge spacing G j,k 、The diameter of each bamboo drum is ψ j,k and length L j,k , the number of microtube channels N and other bamboo-shaped bulge microtube array cooling structure parameters.

[0060] S109. Construct an overall three-dimensional model of the turbine guide vane with a bamboo-shaped micro-tube array cooling structure after the blade body is thinned, perform full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane blade body, and obtain the temperature field distribution and temperature data of the guide vane blade body; if the temperature parameters of the turbine guide vane blade body meet the predetermined temperature standards, the design process is completed; otherwise, adjust the thinning amount of the turbine guide vane blade body and the parameters of the bamboo-shaped bulge micro-tube array cooling structure, and repeat S106 to S108 until the temperature parameters of the turbine guide vane blade body meet the predetermined standards.

[0061] In an embodiment of the present invention, based on the three-dimensional model of the turbine guide vane blade body, using the given bamboo-shaped microtube array cooling structure parameters of the turbine guide vane blade body, a three-dimensional modeling tool is adopted, and the mixing function is utilized to mix the root section and top section microtube array channels to construct a circular microtube row on the turbine guide vane blade body. On this basis, the rotation function is utilized to add a bamboo-shaped bulge structure to construct an overall three-dimensional model of the turbine guide vane with a bamboo-shaped microtube array cooling structure after the blade body is thinned.

[0062] According to the given cooling air consumption and combined with the other inlet and outlet boundary conditions of the turbine guide vane, the constructed overall three-dimensional model of the turbine guide vane with a bamboo-shaped bulge micro-tube array cooling structure after blade thinning is imported into the meshing program, and the fluid domain and solid domain meshes required for the full three-dimensional calculation are divided. Then, the full three-dimensional fluid-thermal coupling calculation and analysis program is used to carry out the full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane blade body, and the temperature field distribution and temperature data of the guide vane blade body are obtained.

[0063] If the obtained turbine guide vane blade temperature parameters meet the predetermined temperature standards, the design process ends; if they do not meet the predetermined standards, the turbine guide vane blade body thinning amount and the bamboo-shaped bulge microtube array cooling structure parameters are adjusted (increasing the number of microtube rows and increasing the diameters of the microtubes and bamboo-shaped bulges).

[0064] In an embodiment of the present invention, the bamboo-shaped micro-tube array cooling structure is cooled, and the diameter of the circular tube is between 0.2 mm and 0.4 mm. The micro-tube array cooperates with the bamboo-shaped enhanced cooling structure to increase the heat exchange area of ​​the cooling channel, increase the convective heat transfer coefficient, and achieve super cooling of the blade body; at the same time, cooperate with the leading edge air film cooling of the turbine guide vane blade body to achieve full coverage of the high-pressure turbine guide vane blade body cooling, meeting the blade body cooling requirements.

[0065] In an embodiment of the present invention, the bamboo-shaped micro-tube array cooling structure is arranged inside the metal wall of the blade body to achieve one-time efficient cooling of the blade body. The cooling demand inside the blade body will be reduced, and the original internal cooling cavity can be reduced, that is, the thickness of the blade body profile can be thinned, which is not only beneficial to reducing the blade profile loss of the guide vane and improving the aerodynamic performance of the guide vane, but also can reduce the heated area of ​​the blade body, which is beneficial to further reduce the cooling demand and comprehensively reduce the cooling air consumption.

[0066] In another embodiment of the present invention, the bamboo-shaped bulge micro-tube array cooling structure is cooled. It uses smaller-scale micro-tube arrays to cover the rest of the blade except the leading edge. It can not only achieve full coverage of the cooling of the high-pressure turbine guide vanes and blades, but also make the temperature distribution of the blades more uniform. The problem of uneven temperature of the traditional blade film plus convection cooling leading to excessive thermal stress will no longer exist.

[0067] The cooling structure of the bamboo-shaped bulge micro-tube array fully utilizes the advantages of the bamboo-shaped bulge micro-tube array with excellent cooling effect and large heat exchange area, and cooperates with the internal cavity convection heat exchange to meet the cooling requirements of the blade body. Therefore, the air film cooling of the middle and rear part of the blade grid can be eliminated.

[0068] In another embodiment of the present invention, the turbine guide vane blade body is cooled by the bamboo-shaped bulge micro-tube array. The cooling air can be delivered to any position of the guide vane blade body by reducing the diameter of the circular tube of the micro-tube array, thereby realizing precise customized delivery of the blade body cooling needs. Combined with the bamboo-shaped bulge to strengthen the cooling structure, the high-temperature area of ​​the blade body can be cooled in a targeted manner.

[0069] In another embodiment of the present invention, the turbine guide vane blade body bamboo-shaped bulge micro-tube array cooling can achieve parametric design of the guide vane blade body bamboo-shaped bulge micro-tube array cooling with only a small number of parameters, which is conducive to rapid optimization and adjustment to obtain the best cooling solution, thereby realizing the design process of bamboo-shaped bulge micro-tube array cooling.

[0070] In another embodiment of the present invention, the turbine guide vane blade body uses a bamboo-shaped bulge micro-tube array for cooling, eliminating the film hole cooling structure in the guide vane blade body. This helps reduce the impact of blade film cooling on the main flow, reduces mixing losses, and improves turbine efficiency. This bamboo-shaped bulge micro-tube array cooling of the turbine guide vane blade body fully utilizes the excellent cooling effect of the bamboo-shaped bulge micro-tube array structure, reduces blade cooling air consumption, and improves the performance of the turbine and the entire gas turbine unit, thereby increasing unit efficiency.

[0071] In another embodiment of the present invention, the turbine guide vane blade body is cooled by a bamboo-shaped micro-tube array, the guide vane blade body thickness is thinned, and cooling tube array channels are arranged inside the blade wall thickness, which can reduce the guide vane weight by about 8%.

[0072] In another embodiment of the present invention, the three-dimensional modeling software is UG NX software, the full three-dimensional fluid-thermal coupling calculation and analysis software is CFX and Fluent software, and the meshing program is ICEM CFD software.

[0073] The present invention proposes a design method for a micro-tube array cooling structure with a bamboo-shaped bulge on a guide vane blade body. 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.

[0074] The present invention proposes a method for designing a micro-tube array cooling structure of a turbine guide vane with a bamboo-shaped bulge. On the basis of fully utilizing the full three-dimensional fluid-thermal coupling calculation method of conventional turbine guide vanes, according to the structural characteristics of the high-pressure turbine guide vane of a gas turbine, focusing on the high-temperature zone of the high-pressure turbine guide vane blade, the guide vane blade cooling structure design and temperature field calculation process are reorganized, and a bamboo-shaped micro-tube array cooling design method suitable for the high-pressure turbine guide vane blade of a gas turbine is proposed. A high-efficiency cooling structure design method for the high-pressure turbine guide vane blade is obtained, which solves the problem that the high-pressure turbine guide vane blade of a gas turbine is difficult to cool.

[0075] The present invention proposes a method for designing a micro-tube array cooling structure with bamboo-shaped bulges on the guide vanes of turbines. Through the use of micro-tube arrays with smaller diameters (0.2mm to 0.4mm), the heat exchange area and convection heat transfer coefficient of the cooling channel are multiplied, thereby achieving super cooling of the blades. Not only can full coverage of the cooling of the high-pressure turbine guide vanes and blades be achieved, but also the cooling requirements of the blades can be fully met. Therefore, the problem of "blind spots" and "dead spots" that are difficult to cool due to the limitations of the spatial structure of traditional air film and large-scale cooling is effectively solved, thereby effectively solving the problem of overheating and even ablation of the blades and blades. The cooling air is delivered to any position of the guide vanes and blades through the small-scale bamboo-shaped micro-tube array cooling structure, thereby achieving precise and customized delivery of the cooling requirements of the blades, focusing on the high-temperature areas of the blades in a targeted manner, and meeting the local cooling requirements of the guide vanes and blades.

[0076] The technical solution of the present invention can give full play to the better cooling effect of the micro-tube array, eliminate the film hole cooling structure in the middle and rear sections of the guide vane blade, thereby weakening the influence of the blade film cooling on the mainstream, which is beneficial to reducing the hot and cold mixing loss of the turbine guide vane blade and improving the turbine efficiency.

[0077] The technical solution of the present invention fully utilizes the excellent cooling effect of the bamboo-shaped micro-tube array structure, which can reduce the amount of cooling air used for the blade body, which is beneficial to improving the performance of the turbine and the entire gas turbine unit and improving the efficiency of the unit. The designed guide vane blade body has a thinner profile and micro-tubes are arranged inside the wall thickness, which is beneficial to reducing the weight of the guide vane and improving the power-to-weight ratio of the engine.

[0078] 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 design method for a micro-tube array cooling structure with a bamboo-shaped bulge on a guide vane blade, characterized in that: The design method comprises: S101. Determine a turbine guide vane cooling structure without micro-tube array cooling channels based on the turbine guide vane blade shape, perform a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine guide vane, and determine the temperature field distribution and data information of the guide vane blade to serve as a basis for subsequent analysis and comparison with a design using a micro-tube array cooling structure with bamboo-shaped bulges. S102, determining a location of a high-temperature area in the turbine guide vane blade where an enhanced cooling structure is to be arranged; S103. According to the surface structure of the guide vane, combined with the dimensional parameters of the guide vane including at least the wall thickness, the leading edge air film structure, and the trailing edge exhaust structure, the cooling structure parameters of the turbine guide vane with the bamboo-shaped bulge micro-tube array are determined. S104, constructing an overall three-dimensional model of a turbine guide vane with a bamboo-shaped bulge micro-tube array cooling structure, and inferring the reduction in cooling air for the turbine guide vane blade body and the cooling air consumption of the turbine guide vane blade body after the bamboo-shaped bulge micro-tube array cooling structure is installed; S105. Based on the overall 3D model of the turbine guide vane with a bamboo-shaped bulge micro-tube array cooling structure, the fluid and solid domains required for full 3D calculations were meshed. Full 3D fluid-thermal coupling calculations and analysis were performed to obtain the temperature field distribution and temperature data of the guide vane blade body. S106. Determine an external thinning amount of the turbine guide vane based on a ratio of the cooling air reduction amount to an originally given cooling air usage amount; S107. Reconstructing the cooling structure of the turbine guide vane based on the reduction ratio of the cooling channel area inside the turbine guide vane and the outer thickness of the blade, and using a three-dimensional modeling tool to create a three-dimensional model of the turbine guide vane and cooling channel after the blade profile is adjusted. S108. Based on the three-dimensional model of the turbine guide vane after the blade profile adjustment and the reduction ratio of the cooling channel area inside the guide vane, adjust the positions of the bamboo-shaped microtubes in the root and top sections, the diameter of each circular channel tube, the center-to-center spacing of the channel tubes, the number of bamboo-shaped bulges in each microchannel along the blade height direction, the spacing between the bamboo-shaped bulges, the diameter of each bamboo-shaped bulge, and the cooling structure parameters of the bamboo-shaped bulge microtube array, including the number of microtube channels; S109. Construct an overall three-dimensional model of the turbine guide vane with a bamboo-shaped micro-tube array cooling structure after the blade body is thinned, perform full three-dimensional fluid-thermal coupling calculation and analysis of the turbine guide vane blade body, and obtain the temperature field distribution and temperature data of the guide vane blade body; if the temperature parameters of the turbine guide vane blade body meet the predetermined temperature standards, the design process is completed; otherwise, adjust the thinning amount of the turbine guide vane blade body and the parameters of the bamboo-shaped bulge micro-tube array cooling structure, and repeat S106 to S108 until the temperature parameters of the turbine guide vane blade body meet the predetermined standards.

2. The method for designing a micro-tube array cooling structure with a bamboo-shaped bulge on a guide vane according to claim 1, characterized in that: According to the surface structure of the guide vane blade, combined with the dimensional parameters of the guide vane blade including at least the blade wall thickness, the leading edge air film structure, and the trailing edge exhaust structure, the cooling structure parameters of the turbine guide vane blade with bamboo-shaped bulge micro-tube array are given, including: Based on the specific location of the turbine guide vane that requires enhanced cooling, the cooling structure parameters of the bamboo-shaped micro-tube array on the turbine guide vane are determined according to the thin and slender structure of the turbine guide vane, and the dimensional parameters including at least the turbine guide vane wall thickness, leading edge air film structure, and trailing edge exhaust structure. Among them, in the root section, the distance H between the position of each microtube center along the blade wall thickness midline and the leading edge point of the blade wall thickness midline is h,i 、The diameter of each circular channel tube φ h,i , channel tube center distance L h,i ; In the top section, the distance H between the center of each microtube along the midline of the blade thickness and the leading edge of the midline of the blade thickness t,i 、The diameter of each circular channel tube φ t,i , through pipe center distance L t,i ; The number of bamboo-shaped bulges along the height direction of each microchannel is M j , bamboo-shaped bulge spacing G j,k The diameter of each bamboo-shaped bulge ψ j,k and length L j,k , the number of microtubule channels N.

3. The method for designing a micro-tube array cooling structure with a bamboo-shaped bulge on a guide vane according to claim 1, characterized in that: Based on cooling air reduction △G cool Compared with the original given cooling air consumption G cool,ori The ratio of △G k =△G cool / G cool,ori , determine the outer thinning amount △Th of the turbine guide vane body, including: The cooling air reduction amount ΔG cool Compared with the original given cooling air consumption G cool,ori The ratio of △G k =△G cool / G cool,ori , that is, the reduction ratio of the cooling channel area inside the turbine guide vane blade △A k =△G k On the basis of the original turbine guide vane blade internal cooling channel, a new turbine guide vane blade internal cooling channel is obtained by reducing the guide vane blade wall thickness, keeping the guide vane blade wall thickness unchanged, and offsetting the guide vane blade wall thickness outward in the new turbine guide vane blade internal cooling channel to obtain the blade body external thickness after adjusting the internal cooling channel, and the blade body external thickness after adjusting the internal cooling channel is Th. ori Compared with the blade thickness before adjustment Th new The difference is the blade body thinning amount △Th.

4. The method for designing a micro-tube array cooling structure with a bamboo-shaped bulge on a guide vane according to claim 1, characterized in that: Based on the overall 3D model of the turbine guide vane with a bamboo-shaped bulge micro-tube array cooling structure, the fluid and solid domains required for full 3D calculations were meshed. Full 3D fluid-thermal coupling calculations and analysis were performed to obtain the temperature field distribution and temperature data of the guide vane blade body, including: The temperature field distribution and temperature data of the turbine guide vane blade body are compared and analyzed with the temperature field distribution and data information of the turbine guide vane blade body without the micro-tube array cooling channel. If the obtained temperature parameters of the turbine guide vane blade body meet the predetermined temperature standard, S106 is executed; otherwise, the bamboo-shaped blisters micro-tube array cooling structure parameters are adjusted by at least increasing the number of micro-tube rows or increasing the diameters of the micro-tubes and the bamboo-shaped blisters, and S104 to S105 are repeated until the temperature parameters of the turbine guide vane blade body reach the predetermined temperature standard.

5. The method for designing a micro-tube array cooling structure with a bamboo-shaped bulge on a guide vane blade according to claim 4, characterized in that: The predetermined temperature standard includes: If the maximum temperature of the turbine guide vane blade body 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 blade body is lower than the temperature resistance grade of the metal material used; If the maximum temperature of the turbine guide vane blade body 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 blade body is reduced by not less than 20°C.

6. The method for designing a micro-tube array cooling structure with a bamboo-shaped bulge on a guide vane according to claim 1, characterized in that: The bamboo-shaped micro-tube array cooling structure has a circular tube diameter between 0.2 mm and 0.4 mm. The micro-tube array is arranged in conjunction with the bamboo-shaped enhanced cooling structure to increase the heat exchange area of ​​the cooling channel, increase the convective heat transfer coefficient, and achieve super cooling of the blade body; at the same time, in conjunction with the leading edge air film cooling of the turbine guide vane blade body, full coverage of the cooling of the high-pressure turbine guide vane blade body is achieved.

7. The method for designing a micro-tube array cooling structure with bamboo-shaped bulges on a guide vane according to claim 1, characterized in that: The method comprises: The bamboo-shaped micro-tube array cooling structure is arranged inside the metal wall of the blade body, which reduces the original internal cooling cavity, thins the guide vane blade line thickness, and reduces the heating area of ​​the turbine guide vane blade body.

8. The method for designing a micro-tube array cooling structure with bamboo-shaped bulges on a guide vane blade according to claim 1, characterized in that: Determining the location of the high-temperature area in the turbine guide vane where the enhanced cooling structure is to be arranged includes: Based on the temperature field distribution and temperature data of the guide vane blade, the location of the high-temperature area of ​​the turbine guide vane blade is determined, that is, the specific location of the turbine guide vane blade that needs to be focused on and enhanced cooling. Subsequently, bamboo-shaped micro-tube array cooling structures will be arranged in these high-temperature areas.

9. The method for designing a micro-tube array cooling structure with bamboo-shaped bulges on a guide vane 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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