Design method of cooling structure with bamboo-shaped micro-tube array on rotor blade

Abstract

The present invention provides a method for designing a cooling structure for a rotor blade with a bamboo-shaped micro-tube array. By constructing the outer shape and internal cooling structure of the turbine rotor blade, the position of the turbine rotor blade to be enhanced in cooling is determined. An overall three-dimensional model of the turbine rotor blade with the bamboo-shaped micro-tube array cooling structure is constructed, and the amount of cooling air reduction for the turbine rotor blade is preset; the amount of thinning of the turbine rotor blade outer shape is determined, and the cooling parameters of the turbine rotor blade, cooling structure, and bamboo-shaped bulge micro-tube array are adjusted; an overall three-dimensional model of the turbine rotor blade with the bamboo-shaped micro-tube array cooling structure after blade thinning is constructed, and full three-dimensional fluid-thermal coupling calculation of the turbine rotor blade is performed. If the temperature parameters of the turbine rotor blade meet the predetermined temperature standards, the design is completed. The technical solution of the present invention can solve the problem that the high-pressure turbine rotor blade of a gas turbine is limited by the structural size space and the amount of cooling air used, resulting in uneven temperature distribution of the blade body, causing blade ablation, cracks, 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 cooling structure of a moving blade with a bamboo-shaped micro-tube array. Background Art

[0002] With the continuous improvement of gas turbine performance indicators and the continuous expansion of their operating boundaries, the turbine inlet temperature continues to increase, which puts higher requirements on the temperature resistance grade of turbine blade materials and cooling structure design for long-term continuous operation under high load conditions.

[0003] During the operation of existing engines and the development of new ones, turbine blades exhibit challenging cooling areas. This is particularly true at the endwalls and blade tips, where relatively small dimensions and complex flow conditions create cooling "blind spots" or even "dead zones." Metal temperatures in these locations approach the heat resistance limits of the blade alloy. Similar phenomena have been reported by researchers abroad during gas turbine design and testing. Transient liquid crystal measurements and numerical calculations of turbine blade surface temperature distributions obtained by Siemens and other companies reveal distinct localized high-temperature zones at the blade body, endwalls, and blade tips. These difficult-to-cool localized high-temperature zones can easily lead to localized ablation of the turbine blades, posing significant challenges to turbine blade cooling design. Furthermore, with the widening of engine operating environments and increasing performance requirements, turbine inlet temperatures continue to rise, further complicating the design of turbine blade cooling structures.

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

[0005] An embodiment of the present invention provides a method for designing a cooling structure for a moving blade with a bamboo-shaped micro-tube array, which can solve the problem that the moving blade 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 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 cooling structure of a rotor blade with a bamboo-shaped micro-tube array is provided, comprising:

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

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

[0009] S103, determining the cooling structure parameters of the turbine rotor blade with a bamboo-shaped micro-tube array based on the surface structure of the rotor blade and the dimensional parameters of the rotor blade including at least the blade wall thickness, the leading edge air film structure, and the trailing edge exhaust structure;

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

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

[0012] S106. Determine the amount of thinning of the turbine blade body based on the ratio of the cooling air usage to the original given cooling air usage;

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

[0014] S108. Based on the three-dimensional model of the turbine rotor blade after the blade profile adjustment and the reduction ratio of the cooling channel area inside the rotor blade, 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 core diameter length 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 rotor blade with a bamboo-shaped micro-tube array cooling structure after blade thinning, perform full three-dimensional fluid-thermal coupling calculation and analysis of the turbine rotor blade body, and obtain the temperature field distribution and temperature data of the rotor blade body; if the temperature parameters of the turbine rotor blade body meet the predetermined temperature standards, the design process ends; otherwise, adjust the thinning amount of the turbine rotor 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 rotor blade body reach the predetermined standards.

[0016] Furthermore, according to the surface structure of the rotor blade, combined with the dimensional parameters of the rotor 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 rotor blade with the bamboo-shaped micro-tube array are given, including:

[0017] Based on the specific location of the turbine rotor blade to be enhanced cooled, according to the thin and slender structure of the turbine rotor blade, and in combination with the dimensional parameters including at least the turbine rotor blade wall thickness, leading edge air film structure, and trailing edge exhaust structure, the parameters of the turbine rotor blade with a bamboo-shaped micro-tube array cooling structure are determined;

[0018] Among them, the number of microtube channels N; in the root section, the distance from the position of each microtube center along the blade wall thickness midline to the leading edge point of the blade wall thickness midline H 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 .

[0019] Furthermore, based on the ratio of the cooling air usage to the originally given cooling air usage, determining the amount of thinning of the turbine blade body includes:

[0020] The ratio of the cooling air usage to the original given cooling air usage is the reduction ratio of the cooling channel area inside the turbine blade body; on the basis of the original turbine blade body internal cooling channel, a new turbine blade body internal cooling channel is obtained by reducing the channel, keeping the blade body wall thickness unchanged, and the blade body wall thickness is offset outward in the new turbine 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.

[0021] Furthermore, based on the overall 3D model of the turbine rotor blade 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 rotor blade body temperature field distribution and temperature data, including:

[0022] The temperature field distribution and temperature data of the turbine rotor blade body are compared and analyzed with the temperature field distribution and data information of the rotor blade body. If the obtained temperature parameters of the turbine rotor 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 repeated until the temperature parameters of the turbine rotor blade body reach the predetermined temperature standard.

[0023] Furthermore, the predetermined temperature standard includes:

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

[0025] If the maximum temperature of the turbine rotor 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 rotor 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 0.1mm and 1mm. 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 blade body, full coverage of the cooling of the high-pressure turbine blade body is achieved.

[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 blade body profile thickness, and reduces the heated area of ​​the turbine blade body.

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

[0030] Based on the temperature field distribution and temperature data of the moving blade body, the location of the high-temperature area of ​​the turbine moving blade body is determined, that is, the specific location of the turbine moving blade body 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] As can be seen from the above scheme, an embodiment of the present invention provides a method for designing a rotor blade with a bamboo-shaped micro-tube array cooling structure. By constructing the turbine rotor blade body's external shape and internal cooling structure, the position of the turbine rotor blade body that requires enhanced cooling is determined. Given the parameters of the turbine rotor blade body's bamboo-shaped bulge micro-tube array cooling structure, an overall three-dimensional model of the turbine rotor blade with the bamboo-shaped micro-tube array cooling structure is constructed, and the amount of cooling air reduction of the turbine rotor blade body is preset; a full three-dimensional fluid-thermal coupling calculation and analysis of the turbine rotor blade body is performed to determine the amount of thinning of the turbine rotor blade body's external shape, and adjust the turbine rotor blade body, cooling structure, and bamboo-shaped bulge micro-tube array cooling parameters; a full three-dimensional fluid-thermal coupling calculation and analysis of the turbine rotor blade body with the bamboo-shaped micro-tube array cooling structure after blade thinning is constructed, and a full three-dimensional fluid-thermal coupling calculation and analysis of the turbine rotor blade body is performed to obtain the temperature field distribution information of the turbine rotor blade body. If the temperature parameters of the turbine rotor blade body meet the predetermined temperature standards, the design of the turbine rotor blade body's micro-tube array cooling structure with the bamboo-shaped bulge is completed. The technical solution of the present invention can solve the problem that the blade body of the high-pressure turbine of the gas turbine is limited by the structural size space and the amount of cooling air used, resulting in uneven temperature distribution of the blade body, causing blade ablation, cracks and other faults, and avoid the blade from overheating and causing the blade to fail and become unable to work. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 A flow chart showing a method for designing a cooling structure of a moving blade with a bamboo-shaped micro-tube array 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] In order to solve the problem that the blade body of the high-pressure turbine rotor blade of a gas turbine is limited by the structural size space and the amount of cooling air, resulting in uneven temperature distribution of the blade body, causing blade ablation, cracks and other faults, a bamboo-shaped micro-tube array turbine rotor blade cooling structure design method suitable for the high-pressure turbine rotor blade of a gas turbine is provided, which has the advantages of excellent cooling effect and low cooling air consumption, so as to avoid the problem that the blade overheats and causes blade failure and inability to work.

[0037] like Figure 1 As shown, Figure 1 A flow chart showing a method for designing a cooling structure of a moving blade with a bamboo-shaped micro-tube array according to an embodiment of the present invention.

[0038] In the figure, a design method for a cooling structure of a moving blade with a bamboo-shaped micro-tube array includes:

[0039] S101. Based on the outer shape of the turbine rotor blade, determine the cooling structure of the turbine rotor blade without micro-tube array cooling channels, perform full three-dimensional fluid-thermal coupling calculation and analysis on the turbine rotor blade, and determine the temperature field distribution and data information of the rotor blade, which will serve as a basis for subsequent analysis and comparison after adopting a design with a bamboo-shaped micro-tube array cooling structure.

[0040] In an embodiment of the present invention, a turbine rotor blade shape is constructed. Based on the blade profile obtained from the turbine aerodynamic design, a 3D modeling tool is used to carry out a turbine rotor blade shape structural design, thereby constructing a 3D rotor blade shape. A turbine rotor blade cooling structure is designed without a bamboo-shaped micro-tube array cooling channel. Based on the 3D turbine rotor blade shape, a turbine rotor blade cooling structure design is carried out (the bamboo-shaped bulge micro-tube array cooling structure design is not currently carried out for the rotor blade), thereby obtaining a 3D model of a turbine rotor blade with a blade cooling structure (without the bamboo-shaped bulge micro-tube array cooling structure).

[0041] A full three-dimensional fluid-thermal coupling calculation and analysis is performed on the turbine blades. According to the inlet and outlet boundary conditions of the turbine blades, the constructed three-dimensional model of the turbine blade with a 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 blades, and the temperature field distribution and data of the blade body 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.

[0042] S102: Determine the location of the high-temperature area in the turbine rotor blade where the enhanced cooling structure is to be arranged.

[0043] In an embodiment of the present invention, based on the temperature field distribution and temperature data of the rotor blade body, the location of the high-temperature area of ​​the turbine rotor blade body is determined, and the specific locations of the rotor blade body that require enhanced cooling are obtained. Subsequently, bamboo-shaped micro-tube array cooling structures will be arranged in these high-temperature areas.

[0044] S103. According to the surface structure of the rotor blade, combined with the dimensional parameters of the rotor blade including at least the blade wall thickness, the leading edge air film structure, and the trailing edge exhaust structure, the turbine rotor blade is given cooling structure parameters with a bamboo-shaped micro-tube array.

[0045] In an embodiment of the present invention, based on the specific position of the turbine rotor blade to be enhanced cooled, according to the structural characteristics of the turbine rotor blade with slender thickness, combined with the dimensional parameters including at least the turbine rotor blade wall thickness, the leading edge air film structure, and the trailing edge exhaust structure, the turbine rotor blade is given with bamboo-shaped micro-tube array cooling structure parameters.

[0046] Among them, the number of microtube channels N; in the root section, the distance from the position of each microtube center along the blade wall thickness midline to the leading edge point of the blade wall thickness midline H 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 .

[0047] S104. Construct an overall three-dimensional model of a turbine rotor blade with a bamboo-shaped micro-tube array cooling structure, and infer the cooling air consumption of the turbine rotor blade body and the cooling air consumption of the turbine rotor blade body with the bamboo-shaped micro-tube array cooling structure.

[0048] In an embodiment of the present invention, based on a three-dimensional model of a turbine blade with a cooling structure (without a bamboo-shaped bulge microtube array cooling structure), using given parameters of the bamboo-shaped microtube array cooling structure of the turbine blade body, a three-dimensional modeling tool is adopted, and the mixing function is used to mix the root section and top section microtube array channels to construct a circular microtube row on the blade body. On this basis, the rotation function is used to add a bamboo-shaped bulge structure to construct a three-dimensional model of a turbine blade with a bamboo-shaped microtube array cooling structure.

[0049] Based on the given parameters of the bamboo-shaped micro-tube array cooling structure of the turbine rotor blade, its heat exchange cooling effect is evaluated. Based on this, the reduction in cooling air for the turbine rotor blade and the cooling air consumption of the turbine rotor blade with the bamboo-shaped micro-tube array cooling structure are preliminarily inferred.

[0050] S105. Based on the overall three-dimensional model of the turbine rotor blade with a bamboo-shaped bulge micro-tube array cooling structure, the fluid domain and solid domain mesh 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 rotor blade body.

[0051] 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 blade, the constructed overall three-dimensional model of the turbine blade with the bamboo-shaped bulge micro-tube array cooling structure 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 blade body to obtain the temperature field distribution and temperature data of the blade body.

[0052] The temperature field distribution and temperature data of the turbine rotor blade body are compared and analyzed with the temperature field distribution and data information of the rotor blade body. If the obtained temperature parameters of the turbine rotor 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 repeated until the temperature parameters of the turbine rotor blade body reach the predetermined temperature standard.

[0053] Wherein, the predetermined temperature standard includes:

[0054] If the maximum temperature of the turbine rotor 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 rotor blade body is lower than the temperature resistance grade of the metal material used;

[0055] If the maximum temperature of the turbine rotor 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 rotor blade body is reduced by not less than 20°C.

[0056] S106 : Determine the outer thinning amount of the turbine rotor blade based on the ratio of the cooling air usage to the originally given cooling air usage.

[0057] In an embodiment of the present invention, the ratio of the cooling air usage to the original given cooling air usage is the ratio of the reduction in the area of ​​the cooling channel inside the turbine blade body; on the basis of the original turbine blade body internal cooling channel, a new turbine blade body internal cooling channel is obtained by reducing the channel, keeping the blade body wall thickness unchanged, and the blade body wall thickness is offset outward in the new turbine 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.

[0058] S107. Based on the reduction ratio of the cooling channel area inside the turbine rotor blade and the outer thickness of the blade, the cooling structure of the turbine rotor blade is reconstructed, and a three-dimensional model of the turbine rotor blade and the cooling channel after the blade shape is adjusted is established using a three-dimensional modeling tool.

[0059] S108. Based on the three-dimensional model of the turbine rotor blade body after the blade profile is adjusted and the reduction ratio of the cooling channel area inside the rotor 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 core length of 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.

[0060] In the embodiment of the present invention, based on the given cooling parameters of the bamboo-shaped micro-tube array of the turbine rotor 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.

[0061] S109. Construct an overall three-dimensional model of the turbine rotor blade with a bamboo-shaped micro-tube array cooling structure after blade thinning, perform full three-dimensional fluid-thermal coupling calculation and analysis of the turbine rotor blade body, and obtain the temperature field distribution and temperature data of the rotor blade body; if the temperature parameters of the turbine rotor blade body meet the predetermined temperature standards, the design process ends; otherwise, adjust the thinning amount of the turbine rotor 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 rotor blade body reach the predetermined standards.

[0062] In an embodiment of the present invention, based on the three-dimensional model of the turbine rotor blade body, using the given parameters of the bamboo-shaped microtube array cooling structure of the turbine rotor 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 rotor 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 rotor blade with a bamboo-shaped microtube array cooling structure after the blade body is thinned.

[0063] According to the given cooling air consumption and combined with the other inlet and outlet boundary conditions of the turbine rotor blade, the constructed three-dimensional model of the rotor blade body is imported into the meshing program to divide the full three-dimensional calculation grid. 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 rotor blade body to obtain the rotor blade body temperature distribution and related temperature data.

[0064] If the obtained turbine blade body temperature parameters meet the predetermined temperature standards, the design process ends; if they do not meet the predetermined standards, the thinning amount of the turbine blade body 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).

[0065] 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 0.1mm and 1mm. The micro-tube array with a smaller diameter, combined with the bamboo-shaped enhanced cooling structure, is conducive to doubling the heat exchange area of ​​the cooling channel and doubling the convective heat transfer coefficient, thereby achieving super cooling of the blade body. Combined with the air film cooling at the leading edge of the blade body, full coverage of the cooling of the high-pressure turbine moving blade can be achieved to meet the cooling requirements of the blade body.

[0066] 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 moving blade and improving the aerodynamic performance of the moving blade, 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.

[0067] In another embodiment of the present invention, the bamboo-shaped micro-tube array cooling structure is cooled by covering the rest of the blade except the leading edge with a micro-tube array of smaller scale. This not only achieves full coverage of the cooling of the high-pressure turbine moving blade, but also makes the temperature distribution of the blade more uniform. The problem of uneven temperature of the traditional blade film plus convection cooling leading to excessive thermal stress will no longer exist.

[0068] The cooling structure of the bamboo-shaped micro-tube array fully utilizes the advantages of the excellent cooling effect and large heat exchange area of ​​the bamboo-shaped bulge micro-tube array, 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.

[0069] In another embodiment of the present invention, the turbine blade body is cooled by the bamboo-shaped bulge microtube array. The cooling air can be delivered to any position of the blade body by reducing the diameter of the circular tube of the microtube 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.

[0070] In another embodiment of the present invention, the bamboo-shaped bulge micro-tube array cooling of the turbine moving blade blade body can realize parametric design of the bamboo-shaped bulge micro-tube array cooling of the moving blade blade body through 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.

[0071] In another embodiment of the present invention, the turbine rotor blade airfoil bamboo-shaped bulge micro-tube array cooling eliminates the film hole cooling structure of the rotor blade airfoil, which helps to reduce the impact of blade airfoil film cooling on the main flow, reduce mixing losses, and improve turbine efficiency. The turbine rotor blade airfoil bamboo-shaped bulge micro-tube array cooling fully utilizes the excellent cooling effect of the bamboo-shaped bulge micro-tube array structure, reduces the amount of blade airfoil cooling air required, and helps improve the performance of the turbine and the entire gas turbine unit, increasing the unit efficiency.

[0072] In another embodiment of the present invention, the turbine rotor blade is cooled by a bamboo-shaped micro-tube array, the rotor blade thickness is thinned, and cooling tube array channels are arranged inside the blade wall thickness, which can reduce the rotor blade weight by about 8%.

[0073] 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.

[0074] The present invention proposes a method for designing a cooling structure of a moving blade with a bamboo-shaped micro-tube array. The method is universal and is not limited to the design of high-pressure turbine moving blades of gas turbines, but is also applicable to the design of high-pressure turbine moving blades of aircraft engines.

[0075] The present invention proposes a method for designing a cooling structure of a turbine rotor blade with a bamboo-node-shaped micro-tube array. On the basis of fully utilizing the full three-dimensional fluid-thermal coupling calculation method of conventional turbine rotor blades, according to the structural characteristics of the high-pressure turbine rotor blade body of a gas turbine, focusing on the high-temperature zone of the high-pressure turbine rotor blade body, the blade blade cooling structure design and temperature field calculation process are reorganized, and a method for designing a cooling structure of a bamboo-node-shaped micro-tube array suitable for the high-pressure turbine rotor blade body of a gas turbine is proposed. A method for designing an efficient cooling structure of a high-pressure turbine rotor blade body is obtained, which solves the problem that the high-pressure turbine rotor blade body of a gas turbine is difficult to cool.

[0076] The present invention proposes a design method for a turbine moving blade with a bamboo-shaped micro-tube array cooling structure. Through the array of micro-tubes with a smaller diameter (0.1mm to 1mm), the heat exchange area and convection heat transfer coefficient of the cooling channel are multiplied, thereby achieving super cooling of the blade. Not only can full coverage of the cooling of the high-pressure turbine moving blade and blade be achieved, but also the cooling requirements of the blade can be fully met. Therefore, it effectively solves 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, and can effectively solve the problem of overheating and even ablation of the blade and blade. The cooling air is delivered to any position of the moving blade and blade through the small-scale bamboo-shaped micro-tube array cooling structure, thereby achieving precise and customized delivery of the cooling requirements of the blade and blade, and focusing on the high-temperature area of ​​the blade to meet the local cooling requirements of the moving blade and blade.

[0077] 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 moving 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 moving blade and blade, and improving the turbine efficiency.

[0078] 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 moving blade body has a thinner profile and micro-tubes are arranged inside the wall thickness, which is beneficial to reducing the weight of the moving blade and improving the power-to-weight ratio of the engine.

[0079] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A method for designing a cooling structure for a moving blade with a bamboo-shaped micro-tube array, characterized in that: The design method comprises: S101. Determine a rotor blade cooling structure without micro-tube array cooling channels based on the rotor blade shape, perform a full three-dimensional fluid-thermal coupling calculation and analysis on the turbine rotor blade, and determine the rotor blade temperature field distribution and data information, which will serve as a basis for subsequent analysis and comparison with a design using a bamboo-shaped micro-tube array cooling structure. S102, determining a location of a high-temperature area in the blade body where an enhanced cooling structure is to be arranged; S103, determining the cooling structure parameters of the moving blade with a bamboo-shaped micro-tube array based on the surface structure of the moving blade and the dimensional parameters of the moving blade including at least the blade wall thickness, the leading edge air film structure, and the trailing edge exhaust structure; S104, constructing an overall three-dimensional model of a turbine rotor blade with a bamboo-shaped micro-tube array cooling structure, and inferring the cooling air consumption of the rotor blade body and the cooling air consumption of the rotor blade body after the bamboo-shaped micro-tube array cooling structure is installed; S105. Based on the overall 3D model of the rotor blade with the bamboo-shaped micro-tube array cooling structure, the fluid and solid domains required for full 3D calculations are divided into meshes. Full 3D fluid-thermal coupling calculations and analysis are performed to obtain the temperature field distribution and temperature data of the rotor blade body. S106. Determine the amount of thinning of the blade body based on the ratio of the cooling air usage to the original given cooling air usage; S107. Reconstructing the cooling structure of the rotor blade based on the reduction ratio of the cooling channel area inside the rotor blade and the blade thickness, and using a three-dimensional modeling tool to create a three-dimensional model of the turbine rotor blade and cooling channel after the blade profile is adjusted. S108. Based on the three-dimensional model of the rotor blade after the blade profile adjustment and the reduction ratio of the cooling channel area inside the rotor blade, 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 core length of each bamboo-shaped tube, and the bamboo-shaped microtube array cooling structure parameters including the number of microtube channels. S109. Construct an overall three-dimensional model of the moving blade with a bamboo-shaped micro-tube array cooling structure after the blade body is thinned, perform full three-dimensional heat-flow coupling calculation and analysis of the moving blade body, and obtain the temperature field distribution and temperature data of the moving blade body; if the temperature parameters of the moving blade body meet the predetermined temperature standards, the design process ends; otherwise, adjust the thinning amount of the moving blade body shape and the parameters of the bamboo-shaped bulge micro-tube array cooling structure and repeat S106 to S108 until the temperature parameters of the moving blade body meet the predetermined standards.

2. The method for designing a cooling structure of a moving blade with a bamboo-shaped micro-tube array according to claim 1, characterized in that: Based on the surface structure of the rotor blade, combined with the dimensional parameters of the rotor blade including at least the blade wall thickness, the leading edge air film structure, and the trailing edge exhaust structure, the parameters of the rotor blade with the bamboo-shaped micro-tube array cooling structure are given, including: Based on the specific location of the rotor blade to be enhanced cooled, the structural characteristics of the rotor blade, which are thick and slender, and the dimensional parameters including at least the rotor blade wall thickness, leading edge air film structure, and trailing edge exhaust structure, the parameters of the rotor blade with a bamboo-shaped micro-tube array cooling structure are determined; Among them, the number of microtube channels N; in the root section, the distance from the position of each microtube center along the blade wall thickness midline to the leading edge point of the blade wall thickness midline H 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 spacing G i,j The diameter of each bamboo-shaped bulge ψ i,j and length L i,j .

3. The method for designing a cooling structure of a moving blade with a bamboo-shaped micro-tube array according to claim 1, characterized in that: Based on the ratio of cooling air consumption to the original given cooling air consumption, the amount of thinning of the blade body is determined, including: The ratio of the cooling air usage to the original given cooling air usage is the reduction ratio of the internal cooling channel of the moving blade body; on the basis of the original internal cooling channel of the moving blade body, a new internal cooling channel of the moving blade body is obtained by reducing the channel, keeping the wall thickness of the moving blade body unchanged, and the wall thickness of the moving blade body is offset outward in the new internal cooling channel of the moving blade body to obtain the outer thickness of the blade body after adjusting the internal cooling channel, and the difference between the outer thickness of the blade body after adjusting the internal cooling channel and the thickness before adjustment is the amount of thinning of the blade body outer shape.

4. The method for designing a cooling structure of a moving blade with a bamboo-shaped micro-tube array according to claim 1, characterized in that: Based on the overall 3D model of a turbine rotor blade with a bamboo-shaped 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 rotor blade body temperature field distribution and temperature data, including: The temperature field distribution and temperature data of the turbine rotor blade body are compared and analyzed with the temperature field distribution and data information of the rotor blade body without the micro-tube array cooling channel. If the obtained rotor blade body temperature parameters meet the predetermined temperature standard, S106 is executed; otherwise, the bamboo-shaped 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 bulges, and S104 to S105 are repeated until the rotor blade body temperature parameters reach the predetermined temperature standard.

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

6. The method for designing a cooling structure of a moving blade with a bamboo-shaped micro-tube array according to claim 1, characterized in that: The bamboo-shaped micro-tube array cooling structure has a circular tube diameter between 0.1mm and 1mm. 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 moving blade body, full coverage of the high-pressure moving blade blade body cooling is achieved.

7. The method for designing a cooling structure of a moving blade with a bamboo-shaped micro-tube array 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 blade body profile thickness, and reduces the heated area of ​​the blade body.

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

9. The method for designing a bamboo-shaped micro-tube array cooling structure for a moving blade 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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