Design method of micro-tube array cooling structure with spherical bulge on guide vane blade

Abstract

The present invention provides a method for designing a micro-tube array cooling structure of a guide vane with a spherical bulge. By constructing the appearance and internal cooling structure of the turbine guide vane, the position of the turbine guide vane that needs to be enhanced in cooling is determined. An overall three-dimensional model of a turbine guide vane with a micro-tube array cooling structure of a spherical bulge is constructed, and the cooling air reduction amount of the turbine guide vane is preset; the cooling parameters of the turbine guide vane, the cooling structure and the micro-tube array of the spherical bulge are adjusted, and the full three-dimensional fluid-heat coupling calculation and analysis of the turbine guide vane is performed. If the temperature parameters of the turbine guide vane meet the predetermined temperature standard, the design of the micro-tube array cooling structure of the turbine guide vane with a spherical bulge is completed. The technical solution of the present invention can solve the problem that the high-pressure turbine guide vane of a gas turbine is limited by the structural size space and the amount of cooling air, resulting in uneven temperature distribution of the blade body, causing blade ablation, cracks and other faults.

Description

Technical Field

[0001] The invention belongs to the technical field of gas turbine design, and particularly relates to a design method for a micro-tube array cooling structure of a guide vane blade with a spherical 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 engines, there are areas in turbine blades that are difficult to cool, especially the end walls and blade tops with relatively small dimensions and relatively complex flows, which are prone to forming cooling "blind spots" or even "dead spots". The metal temperatures at these locations are close to the heat resistance limit of the blade alloy. Similar phenomena have also been reported by foreign researchers when conducting gas turbine design and testing. The surface temperature distribution of turbine blades obtained by transient liquid crystal measurement and numerical calculation by Siemens and other companies shows that obvious local high-temperature areas appear at the blade body, end wall and blade top. These local high-temperature areas that are difficult to cool can easily cause local ablation of turbine blades, which brings great difficulties to the cooling design of turbine blades. In addition, with the expansion of the engine use environment and the improvement of performance requirements, the turbine inlet temperature continues to increase, further increasing the design difficulty of the turbine blade cooling structure.

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

[0005] The embodiment of the present invention provides a method for designing a micro-tube array cooling structure of a guide vane with a spherical 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, resulting in uneven temperature distribution of 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 be unable to work.

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

[0007] S101. Determine the cooling structure of the turbine guide vane without a micro-tube array cooling channel according to the appearance of the turbine guide vane, perform 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 comparison basis for subsequent analysis and the use of a design with a spherical bulge micro-tube array cooling structure;

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

[0009] S103, according to the surface structure of the guide vane blade, combined with the size 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 spherical bulge micro-tube array are given;

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

[0011] S105. Based on the overall three-dimensional model of the turbine guide vane with a spherical bulge micro-tube array cooling structure, the fluid domain and solid domain grids required for full three-dimensional calculation 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;

[0012] S106, determining the thinning amount of the turbine guide vane blade body based on the ratio of the cooling air reduction amount to the original given cooling air usage amount;

[0013] S107, based on the reduction ratio of the cooling channel area inside the turbine guide vane blade body and the outer thickness of the blade body, reconstruct the cooling structure of the turbine guide vane blade body, and use a three-dimensional modeling tool to establish a three-dimensional model of the turbine guide vane blade body and the cooling channel after the blade shape is adjusted;

[0014] S108, adjusting the positions of the micro-spherical tubes 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 spherical bulges in each micro-channel along the blade height direction, the spherical bulge spacing, the diameter of each spherical bulge, and the spherical bulge micro-tube array cooling structure parameters including the number of micro-tube channels according to the three-dimensional model of the turbine guide vane after the blade profile is adjusted and the reduction ratio of the cooling channel area inside the guide vane;

[0015] S109. Construct an overall three-dimensional model of the turbine guide vane with a spherical micro-tube array cooling structure after the blade body is thinned, perform full three-dimensional heat-flow coupling calculation and analysis on 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 standard, the design process ends; otherwise, adjust the thinning amount of the turbine guide vane blade body shape and the parameters of the spherical bulge micro-tube array cooling structure and repeat S106 to S108 until the temperature parameters of the turbine guide vane blade body reach the predetermined standard.

[0016] Further, according to the surface structure of the guide vane blade, combined with the size 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 spherical bulge micro-tube array are given, including:

[0017] Based on the specific position of the turbine guide vane that needs enhanced cooling, according to the thin and slender structural characteristics of the turbine guide vane, combined with the size parameters of at least the turbine guide vane wall thickness, the leading edge air film structure, and the trailing edge exhaust structure, the turbine guide vane blade is given with a spherical bulge micro-tube array cooling structure parameter, the number of micro-tube channels N; wherein, in the root section, the distance H from the position of the center of each micro-tube along the center line of the blade wall thickness to the leading edge point of the center line of the blade wall thickness 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 spherical bulges along the blade height direction in each microchannel M j , Spherical bulge spacing G j,k以及 The diameter of each spherical bulge ψ j,k , the number of microtubule channels N.

[0018] Further, based on the ratio of the cooling air reduction amount to the original given cooling air usage amount, the thinning amount of the turbine guide vane blade is determined, including:

[0019] The ratio of the cooling air reduction amount to the original given cooling air usage is the reduction ratio of the cooling channel area inside the turbine guide vane blade body. On the basis of the original turbine guide vane blade body internal cooling channel, a new turbine guide vane blade body internal cooling channel is obtained by reducing the channel, keeping the guide vane blade body wall thickness unchanged, and the guide vane blade body wall thickness is offset outward in the new turbine guide vane blade body internal cooling channel to obtain the blade body external thickness after adjusting the internal cooling channel. The difference between the blade body external thickness after adjusting the internal cooling channel and the thickness before adjustment is the blade body external thinning amount.

[0020] Furthermore, based on the overall three-dimensional model of the turbine guide vane with a spherical bulge micro-tube array cooling structure, the fluid domain and solid domain meshes required for full three-dimensional calculation are divided to obtain the temperature field distribution and temperature data of the guide vane body, including:

[0021] 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 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 cooling structure parameters of the spherical blisters micro-tube array are adjusted by at least increasing the number of micro-tube rows or increasing the diameters of the micro-tubes and the spherical blisters, and S104 to S105 are repeatedly executed until the temperature parameters of the turbine guide vane blade body reach the predetermined temperature standard.

[0022] Furthermore, the predetermined temperature standard includes:

[0023] 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;

[0024] 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.

[0025] Furthermore, the spherical 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 spherical 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 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.

[0026] Furthermore, the method comprises:

[0027] The spherical micro-tube array cooling structure is used for cooling. The micro-tube array is spread over the remaining positions of the blade except the leading edge, thereby achieving full coverage of the cooling of the high-pressure turbine guide vane and blade, so that the temperature distribution of the blade is more uniform.

[0028] Further, determining the position of the high temperature area in the turbine guide vane blade where the enhanced cooling structure is to be arranged comprises:

[0029] Based on the temperature field distribution and temperature data of the guide vane blade body, the location of the high-temperature area of ​​the turbine guide vane blade body is determined, that is, the specific location of the turbine guide vane blade body that needs to be focused on and enhanced cooling. Subsequently, spherical micro-tube array cooling structures will be arranged in these high-temperature areas.

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

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

[0032] It can be seen from the above scheme that an embodiment of the present invention provides a method for designing a micro-tube array cooling structure of a guide vane blade with a spherical bulge. By constructing the appearance 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 spherical bulge of the turbine guide vane blade, the overall three-dimensional model of the turbine guide vane with the micro-tube array cooling structure of the spherical bulge is constructed, and the cooling air reduction amount of the turbine guide vane blade is preset; the full three-dimensional fluid-heat coupling calculation and analysis of the turbine guide vane blade is performed to determine the thinning amount of the turbine guide vane blade shape, and the cooling parameters of the turbine guide vane blade, cooling structure and spherical bulge micro-tube array are adjusted; the overall three-dimensional model of the turbine guide vane with the spherical micro-tube array cooling structure after the blade is thinned is constructed, and the full three-dimensional fluid-heat coupling calculation and analysis of the turbine guide vane blade is performed to obtain the temperature field distribution information of the turbine guide vane blade. If the temperature parameters of the turbine guide vane blade meet the predetermined temperature standard, the design of the micro-tube array cooling structure of the turbine guide vane blade with the spherical bulge is completed. The technical scheme of the present invention can solve the problem that the blade temperature distribution of the high-pressure turbine guide vane blade of the gas turbine is uneven due to the limitation of the structural size space and the amount of cooling air, which causes the failure of the blade ablation, cracks and the like, and avoids the blade from over-temperature operation, causing the blade to fail to work. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 A flow chart showing a method for designing a micro-tube array cooling structure with a spherical bulge on a guide vane blade body according to an embodiment of the present invention. DETAILED DESCRIPTION

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

[0035] like Figure 1 As shown, Figure 1 A flow chart showing a method for designing a micro-tube array cooling structure with a spherical bulge on a guide vane blade body according to an embodiment of the present invention.

[0036] In the figure, a design method for a micro-tube array cooling structure with a spherical bulge on a guide vane blade body includes:

[0037] S101. Determine the cooling structure of the turbine guide vane without a micro-tube array cooling channel according to the appearance of the turbine guide vane, perform a full three-dimensional heat-flow 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 spherical bulge micro-tube array cooling structure.

[0038] In an embodiment of the present invention, a turbine guide vane blade shape is constructed. Based on the blade profile obtained by the turbine aerodynamic design, a three-dimensional modeling tool is used to carry out a turbine guide vane blade shape structure design to construct a three-dimensional shape of the turbine guide vane blade. A turbine guide vane blade cooling structure without a micro-tube array cooling channel is designed. Based on the three-dimensional shape of the turbine guide vane blade, a turbine guide vane blade cooling structure design is carried out (the guide vane blade does not temporarily carry out the spherical bulge micro-tube array cooling structure design), and a three-dimensional model of a turbine guide vane with a blade cooling structure is obtained (without a spherical bulge micro-tube array cooling structure).

[0039] 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 and blade body are obtained as a basis for subsequent analysis and comparison after adopting the design of a cooling structure with a spherical bulge micro-tube array.

[0040] S102, determining the position of the high temperature area in the turbine guide vane blade where the enhanced cooling structure is to be arranged.

[0041] In an embodiment of the present invention, based on the temperature field distribution and temperature data of the guide vane blade body, the position of the high temperature area of ​​the turbine guide vane blade body is determined, that is, the specific position of the turbine guide vane blade body that needs to be focused on enhanced cooling, and subsequently, spherical micro-tube array cooling structures will be arranged in these high temperature areas.

[0042] 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 a spherical bulge micro-tube array are given.

[0043] In the embodiment of the present invention, based on the specific position of the turbine guide vane blade that needs enhanced cooling, according to the thin and slender structural characteristics of the turbine guide vane blade, combined with the turbine guide vane blade wall thickness, leading edge air film, trailing edge exhaust and other structural size parameters, the turbine guide vane blade with spherical bulge micro-tube array cooling structure parameters are given: wherein, in the root section, the distance H from the position of each micro-tube center along the blade body wall thickness midline direction to the leading edge point of the blade body wall thickness midline 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 spherical bulges along the blade height direction in each microchannel M j , Spherical bulge spacing G j,k以及 The diameter of each spherical bulge ψ j,k , the number of microtubule channels N.

[0044] S104, constructing an overall three-dimensional model of a turbine guide vane with a spherical bulge micro-tube array cooling structure, and inferring the reduction in cooling air for the turbine guide vane blade body and the amount of cooling air used for the turbine guide vane blade body with the spherical bulge micro-tube array cooling structure.

[0045] In an embodiment of the present invention, based on a three-dimensional model of a turbine guide vane with a cooling structure on a blade body (without a spherical bulge micro-tube array cooling structure), using given parameters of the spherical micro-tube array cooling structure of the turbine guide vane blade body, a three-dimensional modeling tool is adopted, and the mixing function is used to mix the root section and top section micro-tube array channels, and a circular micro-tube row is constructed on the turbine guide vane blade body. On this basis, a spherical bulge structure is added using the rotation function to obtain a three-dimensional model of a turbine guide vane with a spherical micro-tube array cooling structure.

[0046] According to the given parameters of the spherical bulge micro-tube array cooling structure of the turbine guide vane blade, its heat exchange cooling effect is evaluated. Based on this, the reduction in cooling air for the turbine guide vane blade and the amount of cooling air used for the turbine guide vane blade with the spherical bulge micro-tube array cooling structure are preliminarily inferred.

[0047] S105. Based on the overall three-dimensional model of the turbine guide vane with a spherical bulge micro-tube array cooling structure, the fluid domain and solid domain grids required for full three-dimensional calculation 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.

[0048] In an embodiment of the present invention, based on the reduction in cooling air 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 spherical 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, 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 to obtain the temperature field distribution and temperature data of the guide vane blade body.

[0049] 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 spherical bulge microtube array are adjusted by at least increasing the number of microtube rows or increasing the diameters of the microtubes and the spherical bulge, and S104 to S105 are repeatedly executed until the temperature parameters of the turbine guide vane blade body reach the predetermined temperature standard.

[0050] Wherein, the predetermined temperature standard includes:

[0051] 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;

[0052] 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.

[0053] S106. Determine the amount of thinning of the turbine guide vane blade body based on the ratio of the cooling air reduction amount to the original given cooling air usage amount.

[0054] In an embodiment of the present invention, the ratio of the cooling air reduction amount to the original given cooling air usage is, that is, the reduction ratio of the cooling channel area inside the turbine guide vane blade body; on the basis of the original turbine guide vane blade body internal cooling channel, a new turbine guide vane blade body internal cooling channel is obtained by reducing the channel, keeping the guide vane blade body wall thickness unchanged, and the guide vane blade body wall thickness is offset outward in the new turbine guide vane blade body internal cooling channel to obtain the blade body external thickness after adjusting the internal cooling channel, and the difference between the blade body external thickness after adjusting the internal cooling channel and the thickness before adjustment is the blade body external thinning amount.

[0055] S107. Based on the reduction ratio of the cooling channel area inside the turbine guide vane blade body and the outer thickness of the blade body, the cooling structure of the turbine guide vane blade body is reconstructed, and a three-dimensional model of the turbine guide vane blade body and the cooling channel after the blade shape is adjusted is established using a three-dimensional modeling tool.

[0056] S108. According to the three-dimensional model of the turbine guide vane body after the blade shape is adjusted and the reduction ratio of the cooling channel area inside the guide vane body, adjust the position of the micro-spherical tubes 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 spherical bulges in each micro-channel along the blade height direction, the spherical bulge spacing, the diameter of each spherical bulge, and the spherical bulge micro-tube array cooling structure parameters including the number of micro-tube channels.

[0057] In the embodiment of the present invention, based on the given parameters of the cooling structure of the spherical micro-tube array of the turbine guide vane blade, the positions of the micro-spherical tubes at the root section and the top section are adjusted according to the parameters such as the chord length of the adjusted blade profile (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 spherical bulges in each microchannel along the blade height direction is M j , Spherical bulge spacing G j,k 、The diameter of each spherical bulge is ψ j,k , the number of microtube channels N and other cooling structure parameters of the spherical bulge microtube array.

[0058] S109. Construct an overall three-dimensional model of the turbine guide vane with a spherical micro-tube array cooling structure after the blade body is thinned, perform full three-dimensional heat-flow coupling calculation and analysis on 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 standard, the design process ends; otherwise, adjust the thinning amount of the turbine guide vane blade body shape and the parameters of the spherical bulge micro-tube array cooling structure and repeat S106 to S108 until the temperature parameters of the turbine guide vane blade body reach the predetermined standard.

[0059] In an embodiment of the present invention, based on the three-dimensional model of the turbine guide vane blade body, using the given spherical micro-tube 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 micro-tube array channels, and a circular micro-tube row is constructed on the turbine guide vane blade body. On this basis, a spherical bulge structure is added using the rotation function, and an overall three-dimensional model of the turbine guide vane with a spherical micro-tube array cooling structure after the blade body is thinned is constructed. 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 spherical bulge micro-tube array cooling structure after the blade body is thinned is imported into the meshing program to divide the fluid domain and solid domain meshes required for the full three-dimensional calculation. Then, the full three-dimensional fluid-heat coupling calculation and analysis program is used to carry out the full three-dimensional fluid-heat coupling calculation and analysis of the turbine guide vane blade body to obtain the guide vane blade body temperature field distribution and temperature data; if the obtained turbine guide vane blade body temperature parameters meet the predetermined temperature standard, the design process ends; if it does not meet the predetermined standard, the thinning amount of the turbine guide vane blade body shape and the spherical bulge micro-tube array cooling structure parameters are adjusted (increase the number of micro-tube rows, increase the diameters of micro-tubes and spherical bulges).

[0060] In an embodiment of the present invention, the spherical micro-tube array cooling structure is used for cooling, and the diameter of the circular tube is between 0.2 mm and 0.4 mm. The micro-tube array cooperates with the spherical 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, 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, thereby meeting the cooling requirements of the blade body.

[0061] In the embodiment of the present invention, the spherical micro-tube array cooling structure is arranged inside the metal wall of the blade body, thereby realizing 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.

[0062] In another embodiment of the present invention, the spherical micro-tube array cooling structure cooling fully utilizes the advantages of excellent cooling effect and large heat exchange area of ​​the spherical bulge micro-tube array, and cooperates with the internal cavity convection heat exchange to meet the blade cooling requirements. Therefore, the air film cooling of the rear part of the blade grid can be eliminated.

[0063] The spherical micro-tube array cooling of the turbine guide vane blade body can deliver cooling air to any position of the guide vane blade body by reducing the diameter of the circular tube of the micro-tube array, thereby achieving precise customized delivery of the blade body cooling needs. Combined with the spherical bulge-enhanced cooling structure, the high-temperature area of ​​the blade body can be cooled in a targeted manner.

[0064] In another embodiment of the present invention, the spherical micro-tube array cooling of the turbine guide vane blade body can achieve parametric design of the spherical micro-tube array cooling of the guide vane blade body 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 spherical micro-tube array cooling.

[0065] In another embodiment of the present invention, the turbine guide vane blade body is cooled by a spherical micro-tube array, eliminating the film hole cooling structure of the guide vane blade body part, which is beneficial to weaken the influence of the blade body film cooling on the mainstream, reduce mixing losses, and improve turbine efficiency.

[0066] In another embodiment of the present invention, the turbine guide vane blade body is cooled by the spherical micro-tube array, which fully utilizes the excellent cooling effect of the spherical micro-tube array structure, reduces the amount of cooling air used for the blade body, and is beneficial to improving the performance of the turbine and the entire gas turbine unit and improving the efficiency of the unit.

[0067] In another embodiment of the present invention, the turbine guide vane blade body is cooled by a spherical micro-tube array, the guide vane blade body thickness is thinned, and a cooling tube array channel is arranged inside the blade wall thickness, which can reduce the weight of the guide vane by about 8%.

[0068] In yet 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.

[0069] The present invention proposes a method for designing a micro-tube array cooling structure with a spherical 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.

[0070] The present invention proposes a method for designing a micro-tube array cooling structure of a turbine guide vane with a spherical bulge. On the basis of making full use of the full three-dimensional fluid-heat coupling calculation method of a conventional turbine guide vane, according to the structural characteristics of the high-pressure turbine guide vane of a gas turbine, the invention focuses on the high-temperature zone of the high-pressure turbine guide vane blade, reorganizes the guide vane blade cooling structure design and temperature field calculation process, and proposes a spherical micro-tube array cooling design method suitable for the high-pressure turbine guide vane blade of a gas turbine. A design method for an efficient cooling structure of 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.

[0071] The method for designing a micro-tube array cooling structure with a spherical bulge on a turbine guide vane blade body proposed in the present invention can multiply the heat exchange area and convection heat transfer coefficient of the cooling channel through a micro-tube array with a smaller diameter (0.2mm to 0.4mm), thereby realizing super cooling of the blade body. Not only can full coverage of high-pressure turbine guide vane blade cooling be achieved, but also the cooling requirements of the blade body can be fully met. Therefore, the problem of "blind spots" and "dead spots" that are difficult to cool due to the limitation of spatial structure in traditional air film and large-scale cooling can be effectively solved, thereby effectively solving the problem of overheating and even ablation of blades and blade bodies. The cooling air is delivered to any position of the guide vane blade body through a small-scale spherical micro-tube array cooling structure, thereby realizing precise customized delivery of the cooling requirements of the blade body, so that the high-temperature area of ​​the blade body can be focused on in a targeted manner, meeting the local cooling requirements of the guide vane blade body.

[0072] The technical solution of the present invention can give full play to the better cooling effect of the micro-tube array, cancel the film hole cooling structure in the middle and rear sections of the guide vane blade, thereby reducing the influence of the blade film cooling on the mainstream, which is beneficial to reducing the cold and hot mixing loss of the turbine guide vane blade and improving the turbine efficiency. The technical solution of the present invention fully utilizes the excellent cooling effect of the spherical micro-tube array structure, can reduce the amount of cooling air used for the blade body, is beneficial to improve the performance of the turbine and the entire gas turbine unit, and improve the unit efficiency. The designed guide vane blade line is thin, and a micro-pipeline is arranged inside the wall thickness, which is beneficial to reduce the weight of the guide vane and improve the power-to-weight ratio of the engine.

[0073] The above are preferred embodiments of the present invention. It should be pointed out that, for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as within the scope of protection of the present invention.

Claims

1. A design method for a micro-tube array cooling structure with a spherical bulge on a guide vane blade, characterized in that: The design method comprises: S101. Determine the cooling structure of the turbine guide vane without a micro-tube array cooling channel according to the appearance of the turbine guide vane, perform 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 comparison basis for subsequent analysis and the use of a design with a spherical bulge micro-tube array cooling structure; S102, determining the position of the high temperature area in the turbine guide vane blade where the enhanced cooling structure is to be arranged; S103, according to the surface structure of the guide vane blade, combined with the size 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 spherical bulge micro-tube array are given; S104, constructing an overall three-dimensional model of a turbine guide vane with a spherical bulge micro-tube array cooling structure, and inferring a reduction in cooling air for the turbine guide vane blade body and an amount of cooling air for the turbine guide vane blade body with the spherical bulge micro-tube array cooling structure; S105. Based on the overall three-dimensional model of the turbine guide vane with a spherical bulge micro-tube array cooling structure, the fluid domain and solid domain grids required for full three-dimensional calculation 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; S106, determining the amount of thinning of the turbine guide vane blade body based on the ratio of the cooling air reduction amount to the original given cooling air usage amount; S107, based on the reduction ratio of the cooling channel area inside the turbine guide vane blade body and the outer thickness of the blade body, reconstruct the cooling structure of the turbine guide vane blade body, and use a three-dimensional modeling tool to establish a three-dimensional model of the turbine guide vane blade body and the cooling channel after the blade shape is adjusted; S108, adjusting the positions of the micro-spherical tubes 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 spherical bulges in each micro-channel along the blade height direction, the spherical bulge spacing, the diameter of each spherical bulge, and the spherical bulge micro-tube array cooling structure parameters including the number of micro-tube channels according to the three-dimensional model of the turbine guide vane after the blade profile is adjusted and the reduction ratio of the cooling channel area inside the guide vane; S109. Construct an overall three-dimensional model of the turbine guide vane with a spherical micro-tube array cooling structure after the blade body is thinned, perform full three-dimensional heat-flow coupling calculation and analysis on 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 standard, the design process ends; otherwise, adjust the thinning amount of the turbine guide vane blade body shape and the parameters of the spherical bulge micro-tube array cooling structure and repeat S106 to S108 until the temperature parameters of the turbine guide vane blade body reach the predetermined standard.

2. The method for designing a micro-tube array cooling structure with a spherical bulge on a guide vane blade according to claim 1, characterized in that: According to the surface structure of the guide vane blade, combined with the size 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 spherical bulge micro-tube array are given, including: Based on the specific position of the turbine guide vane that needs enhanced cooling, according to the thin and slender structural characteristics of the turbine guide vane, combined with the size parameters of at least the turbine guide vane wall thickness, the leading edge air film structure, and the trailing edge exhaust structure, the cooling structure parameters of the turbine guide vane with a spherical bulge micro-tube array are given; among which, in the root section, the distance H from the position of the center of each micro-tube along the center line of the blade wall thickness to the leading edge point of the center line of the blade wall thickness 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 spherical bulges along the blade height direction in each microchannel M j , Spherical bulge spacing G j,k以及 The diameter of each spherical bulge ψ j,k , the number of microtubule channels N.

3. The method for designing a micro-tube array cooling structure with a spherical bulge on a guide vane blade according to claim 1, characterized in that: Based on the ratio of the cooling air reduction to the original given cooling air usage, determine the thinning amount of the turbine guide vane blade, including: The ratio of the cooling air reduction amount to the original given cooling air usage is the reduction ratio of the cooling channel area inside the turbine guide vane blade body. On the basis of the original turbine guide vane blade body internal cooling channel, a new turbine guide vane blade body internal cooling channel is obtained by reducing the channel, keeping the guide vane blade body wall thickness unchanged, and the guide vane blade body wall thickness is offset outward in the new turbine guide vane blade body internal cooling channel to obtain the blade body external thickness after adjusting the internal cooling channel. The difference between the blade body external thickness after adjusting the internal cooling channel and the thickness before adjustment is the blade body external thinning amount.

4. The method for designing a micro-tube array cooling structure with a spherical bulge on a guide vane blade according to claim 1, characterized in that: Based on the overall three-dimensional model of the turbine guide vane with a spherical bulge micro-tube array cooling structure, the fluid domain and solid domain meshes required for full three-dimensional calculation 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, 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 cooling structure parameters of the spherical blisters micro-tube array are adjusted by at least increasing the number of micro-tube rows or increasing the diameters of the micro-tubes and the spherical blisters, and S104 to S105 are repeatedly executed 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 spherical 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 spherical bulge on a guide vane blade according to claim 1, characterized in that: The spherical 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 spherical 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.

7. The method for designing a micro-tube array cooling structure with a spherical bulge on a guide vane blade according to claim 1, characterized in that: The method comprises: The spherical micro-tube array cooling structure is used for cooling. The micro-tube array is spread over the remaining positions of the blade except the leading edge, thereby achieving full coverage of the cooling of the high-pressure turbine guide vane and blade, so that the temperature distribution of the blade is more uniform.

8. The method for designing a micro-tube array cooling structure with a spherical bulge 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 blade where the enhanced cooling structure is to be arranged comprises: Based on the temperature field distribution and temperature data of the guide vane blade body, the location of the high-temperature area of ​​the turbine guide vane blade body is determined, that is, the specific location of the turbine guide vane blade body that needs to be focused on and enhanced cooling. Subsequently, spherical 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 a spherical bulge on a guide vane blade according to claim 1, characterized in that: The 3D modeling software of the computational domain adopts UG NX software, the full 3D fluid-heat coupling calculation and analysis software adopts CFX and Fluent software, and the meshing adopts ICEM CFD software.

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