An improved design method and system for the film cooling structure of a turbine blade

Abstract

The present invention discloses an improved design method and system for the gas film cooling structure of a turbine blade. Using the prototype turbine blade as the improved design template, the prototype turbine blade is respectively subjected to fluid-thermal-solid coupling analysis, cooling air flow characteristic test, and comprehensive cooling effect test. The temperature analysis result of the prototype turbine blade is obtained. Based on the temperature analysis result, the internal cooling structure of the prototype turbine blade is improved. Through multi-level iterative optimization and verification by numerical and experimental methods, an improved turbine blade with a comprehensive cooling effect superior to that of the prototype turbine blade is obtained. The improved method for the gas film cooling structure of the turbine blade provided by the embodiment of the present invention is a comprehensive and general improved design method for the gas film cooling structure, and the final improved turbine blade has a good comprehensive cooling effect.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine improvement, and particularly relates to an improved design method and system for the gas film cooling structure of a turbine blade. Background Art

[0002] The goal of turbine cooling technology is to achieve better turbine cooling effect with less loss of the gas turbine cycle efficiency. A better cooling effect will enable the gas turbine turbine to have a longer life and higher reliability, which can extend the replacement cycle of the gas turbine turbine components, and is of great significance for reducing the operating cost of the gas turbine and ensuring the safe operation of the gas turbine.

[0003] The main purpose of the research on turbine gas film cooling is to use limited cooling air volume to achieve better gas film cooling coverage to block the gas, thereby reducing the heat flux density of the hot wall surface and reducing the turbine heat load. Studying the gas film cooling effect under different film hole patterns, different jet conditions (blowing ratio, density ratio, momentum ratio, etc.) and mainstream conditions (mainstream velocity, pressure gradient, turbulence intensity, unsteadiness, etc.) is also an important working direction. Gas film cooling is a convective heat transfer problem with a highly complex flow field structure. The existing gas film cooling structure of turbine blades determines the improved parts by analyzing the actual application situation of the prototype blades, and cannot improve it comprehensively and effectively, and requires multiple improvements. Summary of the Invention

[0004] In view of this, the embodiments of the present invention provide an improved design method and system for the gas film cooling structure of a turbine blade to solve the deficiency that the comprehensive cooling effect after improving the gas film cooling structure by the existing improvement method is not good.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] The embodiments of the present invention provide an improved design method for the gas film cooling structure of a turbine blade, including: Step S1: Obtain the temperature analysis results of the prototype turbine blade by respectively performing fluid-thermal-solid coupling analysis, cooling air flow characteristic test, and comprehensive cooling effect test on the prototype turbine blade;

[0007] Step S2: Improve the internal cooling structure of the prototype turbine blade based on the temperature field analysis results of the prototype turbine blade;

[0008] Step S3: Analyze the deviation of the cooling air flow rate of the blade before and after improvement, generate the design parameters of the gas film cooling structure, and pre-arrange gas film cooling holes in the high-temperature area on the surface of the improved turbine blade according to the design parameters;

[0009] Step S4: Check the cooling air flow characteristics of the improved turbine blade with the film cooling structure arranged, analyze the deviation of the flow characteristics from those of the prototype turbine blade. If the deviation meets the preset requirements, proceed to the next step for the initial improved turbine blade; otherwise, adjust the film cooling structure.

[0010] Step S5: Conduct a fluid-thermal-solid coupling analysis on the initial improved turbine blade, and optimize the film cooling structure parameters under different operating conditions of the blade.

[0011] Step S6: Conduct a flow analysis on the multi-stage turbine blades, evaluate the influence of adding the film cooling structure to the prototype turbine blade on the aerodynamic characteristics of the downstream stage. If it meets the design requirements, proceed to the next step; otherwise, return to Step S5 to continue optimizing the film cooling structure.

[0012] Step S7: Conduct a fluid-thermal-solid coupling analysis on the improved turbine blade model, check the strength and vibration characteristics of the blade. If it meets the design requirements, obtain the numerically predicted improved turbine blade and proceed to the next step; otherwise, return to Step S5 to continue optimizing the film cooling structure.

[0013] Step S8: Conduct a comprehensive cooling effect test on the numerically predicted improved turbine blade, and compare it with the comprehensive cooling effect of the prototype turbine blade to verify the effectiveness and accuracy of the improved design method. If it meets the design requirements, obtain the finally improved turbine blade that meets the requirements; otherwise, return to Step S5 to continue optimizing the film cooling structure.

[0014] Optionally, Step S1 includes:

[0015] Conduct a fluid-thermal-solid coupling analysis on the prototype turbine blade to obtain the temperature field, stress field, and thermal deformation data of the prototype turbine blade.

[0016] Conduct tests on the cooling air flow characteristics of the prototype turbine blade in divided chambers and all chambers to obtain the total flow rate of each chamber and the flow characteristic curve data of the divided chambers.

[0017] Conduct a comprehensive cooling effect test on the prototype turbine blade to obtain the test data of the comprehensive cooling effect on the blade surface.

[0018] Based on the above data, obtain the temperature distribution contour map of the outer surface of the prototype turbine blade, the temperature distribution contour map of the cross-section of the blade, and the comprehensive cooling effect distribution contour map of the outer surface of the blade.

[0019] Optionally, Step S2 includes: Based on the temperature distribution contour map of the outer surface of the blade, the temperature distribution contour map of the cross-section of the blade, and the comprehensive cooling effect distribution contour map of the outer surface of the blade, optimize the spoiler rib structure near the trailing edge of the internal cooling channels of the turbine blade and the structures at the turning points of each channel near the blade tip and near the shroud.

[0020] Optionally, when analyzing the flow cooling air flow deviation of the blade before and after improvement in step S3 and generating the design parameters of the film cooling structure, first determine the number of film holes according to the flow characteristic deviation; secondly, respectively determine the areas of the local high-temperature zones on the pressure surface and the suction surface through the blade surface temperature field information obtained by coupled analysis, and allocate the number of film holes on the pressure surface and the suction surface according to the sizes of the high-temperature zone areas. The angle α between the center line of the film hole and the pressure surface or the suction surface is between 25° and 35°.

[0021] Optionally, the angle β between the outflow direction of the film hole and the plane perpendicular to the blade height direction is 0°; arrange the positions of the film holes according to the ratio of the film hole pitch P to the film hole diameter D where 5 < P / D < 10.

[0022] Optionally, the film holes are arranged along the center line of the core high-temperature zone on the blade surface.

[0023] Optionally, the design requirement for the influence on the aerodynamic efficiency of the downstream stage after adding the film cooling structure to the prototype turbine blade is less than 0.3.

[0024] The embodiment of the present invention also provides an improved design system for the film cooling structure of a turbine blade, including:

[0025] A prototype turbine blade analysis module, configured to obtain the temperature analysis results of the prototype turbine blade by respectively performing fluid-thermal-solid coupling analysis, cooling air flow characteristic testing, and comprehensive cooling effect tests on the prototype turbine blade;

[0026] A prototype turbine blade improvement module, configured to improve the internal cooling structure of the prototype turbine blade based on the temperature field analysis results of the prototype turbine blade;

[0027] A cooling structure parameter design module, configured to analyze the flow cooling air flow deviation of the blade before and after improvement, generate the design parameters of the film cooling structure, and pre-arrange film cooling holes in the high-temperature area on the surface of the improved turbine blade according to the design parameters;

[0028] A first verification module, configured to perform a cooling air flow characteristic verification on the improved turbine blade with the film cooling structure arranged, analyze the flow characteristic deviation from the prototype turbine blade, and if the deviation meets the preset requirements, continue to the next step for the initial improved turbine blade, and if not, adjust the film cooling structure;

[0029] An improved turbine blade three-dimensional analysis module, configured to perform fluid-thermal-solid coupling analysis on the initial improved turbine blade and optimize the film cooling structure parameters under different working conditions of the blade;

[0030] The multi-stage turbine blade analysis module is used to perform flow analysis on multi-stage turbine blades, evaluate the impact on the aerodynamic characteristics of the downstream stage after adding a film cooling structure to the prototype turbine blade. If the design requirements are met, proceed to the next step; if not, return to the three-dimensional analysis module of the improved turbine blade to continue optimizing the film cooling structure;

[0031] The second verification module is used to perform fluid-thermal-solid coupling analysis on the improved turbine blade model, verify the strength and vibration characteristics of the blade. If the design requirements are met, obtain the numerically predicted improved turbine blade and proceed to the next step; if not, return to the three-dimensional analysis module of the improved turbine blade to continue optimizing the film cooling structure;

[0032] The comprehensive cooling effect analysis module is used to conduct a comprehensive cooling effect test on the numerically predicted improved turbine blade and compare it with the comprehensive cooling effect of the prototype turbine blade to verify the effectiveness and accuracy of the improved design method. If the design requirements are met, obtain the final improved turbine blade that meets the requirements; if not, return to the three-dimensional analysis module of the improved turbine blade to continue optimizing the film cooling structure.

[0033] An embodiment of the present invention also provides an electronic device, including: a memory and a processor, which are communicatively connected to each other. The memory stores computer instructions, and the processor executes the computer instructions to execute the improved design method for the film cooling structure of the turbine blade provided by the embodiment of the present invention.

[0034] An embodiment of the present invention also provides a computer-readable storage medium, which stores computer instructions for causing a computer to execute the improved design method for the film cooling structure of the turbine blade provided by the embodiment of the present invention.

[0035] The technical solution of the present invention has the following advantages:

[0036] The present invention provides an improved design method and system for the film cooling structure of turbine blades. Using the prototype turbine blade as the improved design template, fluid-thermal-solid coupling analysis, cooling air flow characteristic testing, and comprehensive cooling effect testing are respectively performed on the prototype turbine blade. Based on the temperature analysis results of the prototype turbine blade, the internal cooling structure of the prototype turbine blade is improved. Through multi-level iterative optimization and verification by numerical and experimental methods, an improved turbine blade with a better comprehensive cooling effect than the prototype turbine blade is obtained. The improved design method for the film cooling structure of the turbine blade provided by the embodiment of the present invention is a comprehensive and general film cooling structure improvement design method, and the final improved turbine blade has a good comprehensive cooling effect. Description of the Drawings

[0037] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0038] Figure 1 It is a flowchart of the improved design method for the gas film cooling structure of the turbine blade in the embodiment of the present invention;

[0039] Figure 2 It is a schematic diagram of the included angle between the gas film hole and the blade cross-section in the embodiment of the present invention;

[0040] Figure 3 It is a schematic diagram of the included angle between the gas film hole and the blade surface in the leaf height direction in the embodiment of the present invention;

[0041] Figure 4 It is a schematic diagram of the arrangement direction of the gas film holes in the embodiment of the present invention;

[0042] Figure 5 It is a flowchart of the multi-level iterative optimization of the improved design method for the gas film cooling structure of the turbine blade in the embodiment of the present invention;

[0043] Figure 6 It is a schematic diagram of the structure of the improved design system for the gas film cooling structure of the turbine blade in the embodiment of the present invention;

[0044] Figure 7 It is a schematic diagram of the structure of the electronic device in the embodiment of the present invention. Specific Embodiments

[0045] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0046] According to the embodiments of the present invention, an embodiment of an improved design method for the gas film cooling structure of a turbine blade is provided. It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, as Figure 1 shown, and include the following steps:

[0047] Step S1: Obtain the temperature analysis results of the prototype turbine blade by performing fluid-thermal-solid coupling analysis, cooling air flow characteristic test, and comprehensive cooling effect test on the prototype turbine blade respectively.

[0048] In the embodiment of the present invention, the temperature field, stress field, and thermal deformation data of the prototype turbine blade are obtained through fluid-thermal-solid coupling analysis of the prototype turbine blade; the total flow rate of each chamber and the flow characteristic curve data of the divided chambers are obtained by performing cooling air flow characteristic tests on the divided chambers and all chambers of the prototype turbine blade; the test data of the comprehensive cooling effect on the blade surface are obtained by performing a comprehensive cooling effect test on the prototype turbine blade; finally, based on the above data, the temperature distribution nephogram of the outer surface of the blade, the temperature distribution nephogram of the cross-section of the blade, and the comprehensive cooling effect distribution nephogram of the outer surface of the blade of the prototype turbine blade are obtained.

[0049] Step S2: Improve the internal cooling structure of the prototype turbine blade based on the temperature field analysis results of the prototype turbine blade.

[0050] Specifically, in the embodiment of the present invention, based on the temperature distribution nephogram of the outer surface of the blade, the temperature distribution nephogram of the cross-section of the blade, and the comprehensive cooling effect distribution nephogram of the outer surface of the blade, the turbulator rib structure near the trailing edge of the internal cooling channel of the turbine blade and the structures at the turning points of each channel near the blade tip and near the shroud are optimized.

[0051] Step S3: Analyze the flow cooling air flow deviation of the blade before and after improvement, generate the design parameters of the film cooling structure, and pre-arrange film cooling holes in the high-temperature area on the surface of the improved turbine blade according to the design parameters.

[0052] When analyzing the flow cooling air flow deviation of the blade before and after improvement and generating the design parameters of the film cooling structure in the embodiment of the present invention, first, the number of film holes is determined according to the flow characteristic deviation; secondly, based on the blade surface temperature field information obtained through fluid-thermal-solid coupling analysis (including the high and low of the blade surface temperature, the magnitude of the temperature gradient, the position of the local high-temperature area, the distribution trend of the local high-temperature area, etc.), the areas of the local high-temperature areas on the pressure surface and the suction surface are respectively determined, and the number of film holes on the pressure surface and the suction surface is allocated according to the size of the high-temperature area. As Figure 2 shown, the angle α between the center line of the film hole and the pressure surface or the suction surface is between 25° and 35°; as Figure 3 shown, the angle β between the outflow direction of the film hole and the plane perpendicular to the blade height direction is 0°; the film holes are arranged according to the ratio of the film hole pitch P to the film hole diameter D being 5 < P / D < 10, and the film holes are arranged along the center line of the core high-temperature area on the blade surface. As Figure 4 shown in the direction of line L, the high-temperature area can be directly cooled down.

[0053] Step S4: Check the cooling air flow characteristics of the improved turbine blade with the film cooling structure arranged, analyze the deviation of the flow characteristics from those of the prototype turbine blade. If the deviation meets the preset requirements, proceed to the next step for the initial improved turbine blade; if not, adjust the film cooling structure.

[0054] Step S5: Conduct a fluid-thermal-solid coupling analysis on the initial improved turbine blade and optimize the film cooling structure parameters under different operating conditions of the blade. Figure 5 As shown, in the subsequent improvement process, if the corresponding requirements are not met, return to the initial improved turbine blade and re-optimize the film cooling structure parameters under different operating conditions of the blade in Step S5.

[0055] Step S6: Conduct a flow analysis on the multi-stage turbine blade, evaluate the influence of adding the film cooling structure to the prototype turbine blade on the aerodynamic characteristics of the downstream stage. If the requirements are met, proceed to the next step; if not, return to Step S5 and continue to optimize the film cooling structure;

[0056] In the embodiment of the present invention, if the influence of adding the film cooling structure to the prototype turbine blade on the aerodynamic efficiency of the downstream stage is less than 0.3, it meets the design requirements. This is only an example and not limited thereto.

[0057] Step S7: Conduct a fluid-thermal-solid coupling analysis on the improved turbine blade model, check the strength and vibration characteristics of the blade. If the requirements are met, obtain the numerically predicted improved turbine blade and proceed to the next step; if not, return to Step S5 and continue to optimize the film cooling structure;

[0058] Step S8: Conduct a comprehensive cooling effect test on the numerically predicted improved turbine blade and compare it with the comprehensive cooling effect of the prototype turbine blade to verify the effectiveness and accuracy of the improved design method. If the requirements are met, obtain the finally improved turbine blade that meets the requirements; if not, return to Step S5 and continue to optimize the film cooling structure.

[0059] The method for improving the film cooling structure of the turbine blade provided in the embodiment of the present invention is a comprehensive and general method for improving the design of the film cooling structure. Using the prototype turbine blade as the improvement design template, through multi-level iterative optimization and verification by numerical and experimental methods, the comprehensive cooling effect of the finally improved turbine blade is better than that of the prototype turbine blade.

[0060] This embodiment also provides an improved design system for the film cooling structure of a turbine blade, as Figure 6 shown, including:

[0061] The prototype turbine blade analysis module 1 is used to obtain the temperature analysis results of the prototype turbine blade obtained by respectively performing fluid-thermal-solid coupling analysis, cooling air flow characteristic test, and comprehensive cooling effect test on the prototype turbine blade. For detailed content, refer to the relevant description of step S1 in the above method embodiment, and details will not be elaborated here.

[0062] The prototype turbine blade improvement module 2 is used to improve the internal cooling structure of the prototype turbine blade based on the temperature field analysis results of the prototype turbine blade; for detailed content, refer to the relevant description of step S2 in the above method embodiment, and details will not be elaborated here.

[0063] The cooling structure parameter design module 3 is used to analyze the deviation of the cooling air flow rate of the blade before and after improvement, generate the design parameters of the film cooling structure, and pre-arrange film cooling holes in the high-temperature area on the surface of the improved turbine blade according to the design parameters; for detailed content, refer to the relevant description of step S3 in the above method embodiment, and details will not be elaborated here.

[0064] The first verification module 4 is used to verify the cooling air flow characteristics of the improved turbine blade with the arranged film cooling structure, analyze the deviation of the flow characteristics from the prototype turbine blade. If the deviation meets the preset requirements, the initial improved turbine blade proceeds to the next step. If not, the film cooling structure is adjusted. For detailed content, refer to the relevant description of step S4 in the above method embodiment, and details will not be elaborated here.

[0065] The improved turbine blade three-dimensional analysis module 5 is used to perform fluid-thermal-solid coupling analysis on the initial improved turbine blade and optimize the film cooling structure parameters under different working conditions of the blade; for detailed content, refer to the relevant description of step S5 in the above method embodiment, and details will not be elaborated here.

[0066] The multi-stage turbine blade analysis module 6 is used to perform flow analysis on the multi-stage turbine blade, evaluate the influence on the aerodynamic characteristics of the downstream stage after adding the film cooling structure to the prototype turbine blade. If the design requirements are met, proceed to the next step. If not, return to the improved turbine blade three-dimensional analysis module to continue optimizing the film cooling structure; for detailed content, refer to the relevant description of step S6 in the above method embodiment, and details will not be elaborated here.

[0067] The second verification module 7 is used to perform fluid-thermal-solid coupling analysis on the improved turbine blade model, verify the strength and vibration characteristics of the blade. If the design requirements are met, the numerically predicted improved turbine blade is obtained and proceed to the next step. If not, return to the improved turbine blade three-dimensional analysis module to continue optimizing the film cooling structure; for detailed content, refer to the relevant description of step S7 in the above method embodiment, and details will not be elaborated here.

[0068] The comprehensive cooling effect analysis module 8 is used to conduct a comprehensive cooling effect test on the numerically predicted improved turbine blade, and compare it with the comprehensive cooling effect of the prototype turbine blade to verify the effectiveness and accuracy of the improved design method. If the design requirements are met, the final improved turbine blade is obtained. If not, it returns to the three-dimensional analysis module of the improved turbine blade to continue optimizing the film cooling structure. For detailed content, refer to the relevant description of step S8 in the above method embodiment, and details will not be elaborated here.

[0069] According to an embodiment of the present invention, there is also provided an electronic device, as Figure 7 shown. The electronic device may include a processor 901 and a memory 902, where the processor 901 and the memory 902 may be connected through a bus or other means. Figure 7 Taking the connection through the bus as an example.

[0070] The processor 901 may be a central processing unit (CPU). The processor 901 may also be other general-purpose processors, digital signal processors (DSPs), application specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. chips, or a combination of the above types of chips.

[0071] The memory 902, as a non-transitory computer-readable storage medium, can be used to store non-transitory software programs, non-transitory computer-executable programs, and modules, such as the program instructions / modules corresponding to the method in the method embodiment of the present invention. The processor 901 executes various functional applications and data processing of the processor by running the non-transitory software programs, instructions, and modules stored in the memory 902, that is, implements the method in the above method embodiment.

[0072] The memory 902 may include a program storage area and a data storage area. Among them, the program storage area can store an operating system and application programs required for at least one function; the data storage area can store data created by the processor 901 and the like. In addition, the memory 902 may include high-speed random access memory, and may also include non-transitory memory, such as at least one magnetic disk storage device, a flash memory device, or other non-transitory solid-state storage devices. In some embodiments, the memory 902 may optionally include a memory remotely disposed relative to the processor 901, and these remote memories can be connected to the processor 901 through a network. Examples of the above-mentioned network include but are not limited to the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0073] One or more modules are stored in the memory 902 and, when executed by the processor 901, execute the methods in the above method embodiments.

[0074] For the specific details of the above electronic device, reference can be made to the corresponding relevant descriptions and effects in the above method embodiments for understanding, and details will not be repeated here.

[0075] Those skilled in the art can understand that to implement all or part of the processes in the above method embodiments, it can be completed by instructing relevant hardware through a computer program. The program can be stored in a computer-readable storage medium. When the program is executed, it can include the processes of the above method embodiments. Among them, the storage medium can be a magnetic disk, an optical disc, a read-only memory (ROM), a random access memory (RAM), a flash memory, a hard disk drive (abbreviation: HDD), or a solid-state drive (SSD), etc.; the storage medium can also include a combination of the above types of memories.

[0076] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. An improved design method for the film cooling structure of a turbine blade, characterized in that, it includes: Step S1: Obtain the temperature analysis results of the prototype turbine blade by performing fluid-thermal-solid coupling analysis, cooling air flow characteristic test, and comprehensive cooling effect test on the prototype turbine blade respectively; Step S2: Improve the internal cooling structure of the prototype turbine blade based on the temperature field analysis results of the prototype turbine blade; Step S3: Analyze the deviation of the cooling air flow rate of the blade before and after improvement, generate the design parameters of the film cooling structure, and pre-arrange film cooling holes in the high-temperature area on the surface of the improved turbine blade according to the design parameters; Step S4: Check the cooling air flow characteristic of the improved turbine blade with the film cooling structure arranged, analyze the deviation of the flow characteristic from the prototype turbine blade. If the deviation meets the preset requirements, continue to the next step for the initial improved turbine blade. If not, adjust the film cooling structure; Step S5: Perform fluid-thermal-solid coupling analysis on the initial improved turbine blade, and optimize the film cooling structure parameters under different working conditions of the blade; Step S6: Perform flow analysis on multi-stage turbine blades, evaluate the influence on the aerodynamic characteristics of the downstream stage after adding the film cooling structure to the prototype turbine blade. If it meets the design requirements, continue to the next step. If not, return to Step S5 and continue to optimize the film cooling structure; Step S7: Perform fluid-thermal-solid coupling analysis on the improved turbine blade model, check the strength and vibration characteristics of the blade. If it meets the design requirements, obtain the numerically predicted improved turbine blade and continue to the next step. If not, return to Step S5 and continue to optimize the film cooling structure; Step S8: Conduct a comprehensive cooling effect test on the numerically predicted improved turbine blade, and compare it with the comprehensive cooling effect of the prototype turbine blade to verify the effectiveness and accuracy of the improved design method. If it meets the design requirements, obtain the final improved turbine blade that meets the requirements. If not, return to Step S5 and continue to optimize the film cooling structure.

2. The improved design method for the film cooling structure of a turbine blade according to claim 1, characterized in that, the Step S1 includes: Performing fluid-thermal-solid coupling analysis on the prototype turbine blade to obtain the temperature field, stress field, and thermal deformation data of the prototype turbine blade; Performing cooling air flow characteristic tests on the prototype turbine blade in divided chambers and all chambers to obtain the total flow rate of each chamber and the flow characteristic curve data of the divided chambers; Performing a comprehensive cooling effect test on the prototype turbine blade to obtain the test data of the comprehensive cooling effect on the blade surface; Based on the above data, obtaining the temperature distribution nephogram of the outer surface of the blade, the temperature distribution nephogram of the cross-section of the blade, and the comprehensive cooling effect distribution nephogram of the outer surface of the blade of the prototype turbine blade.

3. The improved design method for the film cooling structure of a turbine blade according to claim 2, characterized in that, the Step S2 includes: Based on the temperature distribution nephogram of the outer surface of the blade, the temperature distribution nephogram of the cross-section of the blade, and the comprehensive cooling effect distribution nephogram of the outer surface of the blade, optimize the turbulator rib structure near the trailing edge of the internal cooling channel of the turbine blade, and the structures at the turning points of each channel near the blade tip and near the shroud.

4. The improved design method for the film cooling structure of a turbine blade according to claim 3, characterized in that, when analyzing the flow rate deviation of the cooling air of the blade before and after improvement in step S3 and generating the design parameters of the film cooling structure, first determine the number of film holes according to the flow rate characteristic deviation; secondly, respectively determine the areas of the local high-temperature zones on the pressure surface and the suction surface through the blade surface temperature field information obtained by coupling analysis, and distribute the number of film holes on the pressure surface and the suction surface according to the sizes of the high-temperature zone areas. The angle α between the center line of the film hole and the pressure surface or the suction surface is between 25° and 35°.

5. The improved design method for the film cooling structure of a turbine blade according to claim 4, characterized in that, the angle β between the outflow direction of the film hole and the plane perpendicular to the blade height direction is 0°; the positions of the film holes are arranged according to the ratio of the film hole pitch P to the film hole diameter D where 5 < P / D < 10.

6. The improved design method for the film cooling structure of a turbine blade according to claim 5, characterized in that, the film holes are arranged along the center line of the core high-temperature zone on the blade surface.

7. The improved design method for the film cooling structure of a turbine blade according to claim 5, characterized in that, the design requirement for the influence on the aerodynamic efficiency of the downstream stage after adding the film cooling structure to the prototype turbine blade is less than 0.

3.

8. An improved design system for the film cooling structure of a turbine blade, characterized in that, comprising: a prototype turbine blade analysis module for obtaining the temperature analysis results of the prototype turbine blade by respectively performing fluid-thermal-solid coupling analysis, cooling air flow rate characteristic testing, and comprehensive cooling effect tests on the prototype turbine blade; a prototype turbine blade improvement module for improving the internal cooling structure of the prototype turbine blade based on the prototype turbine blade temperature field analysis results; a cooling structure parameter design module for analyzing the flow rate deviation of the cooling air of the blade before and after improvement, generating the design parameters of the film cooling structure, and pre-arranging film cooling holes in the high-temperature areas on the surface of the improved turbine blade according to the design parameters; a first verification module for performing a cooling air flow rate characteristic verification on the improved turbine blade with the film cooling structure arranged, analyzing the flow rate characteristic deviation from the prototype turbine blade, and if the deviation meets the preset requirements, proceeding to the next step for the initial improved turbine blade, and if not, adjusting the film cooling structure; an improved turbine blade three-dimensional analysis module for performing fluid-thermal-solid coupling analysis on the initial improved turbine blade and optimizing the film cooling structure parameters under different operating conditions of the blade; a multi-stage turbine blade analysis module for performing a flow analysis on the multi-stage turbine blade, evaluating the influence on the aerodynamic characteristics of the downstream stage after adding the film cooling structure to the prototype turbine blade, and if it meets the design requirements, proceeding to the next step, and if not, returning to the improved turbine blade three-dimensional analysis module to continue optimizing the film cooling structure; a second verification module for performing fluid-thermal-solid coupling analysis on the improved turbine blade model, verifying the strength and vibration characteristics of the blade, and if it meets the design requirements, obtaining a numerically predicted improved turbine blade, and if not, returning to the improved turbine blade three-dimensional analysis module to continue optimizing the film cooling structure; The comprehensive cooling effect analysis module is used to conduct comprehensive cooling effect tests on the numerically predicted improved turbine blade, and compare it with the comprehensive cooling effect of the prototype turbine blade to verify the effectiveness and accuracy of the improved design method. If the design requirements are met, the final improved turbine blade is obtained; if not, it returns to the 3D analysis module of the improved turbine blade to continue optimizing the film cooling structure.

9. An electronic device, characterized in that, it includes: a memory and a processor, the memory and the processor are communicatively connected to each other, the memory stores computer instructions, and the processor executes the computer instructions to execute the improved design method for the film cooling structure of the turbine blade according to any one of claims 1-7.

10. A computer-readable storage medium, characterized in that, the computer-readable storage medium stores computer instructions, and the computer instructions are used to cause the computer to execute the improved design method for the film cooling structure of the turbine blade according to any one of claims 1-7.

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