Multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor

Abstract

The objective is to provide a multidimensional coupled design method for the flow aerodynamic arrangement of a gas turbine transition section-high-pressure compressor. This method integrates the transition section and high-pressure compressor as a single system, ensuring full integration with the upstream transition section in each dimension and stage of the high-pressure compressor aerodynamic design. This achieves integrated and coordinated design of the flow arrangement between the transition section and the high-pressure compressor, systematizing, parameterizing, and miniaturizing the aerodynamic design of the transition section-high-pressure compressor in different dimensions. This effectively improves the aerodynamic performance of the high-pressure compressor, enhances aerodynamic design accuracy, saves a large amount of design iteration time, shortens the design cycle, and is highly suitable for construction design applications. The present invention is not limited to gas turbine high-pressure compressors, but is also applicable to the aerodynamic design process of aircraft engine high-pressure compressors and various industrial axial flow compressors with transition flow structures.

Description

【Technical Field】 【0001】 The present invention relates to a gas turbine design method, and specifically to a compressor design method. 【Background Art】 【0002】 A compressor is one of the three core components of a gas turbine, and the quality of its performance directly determines the technical index level of the gas turbine. For the development of a type 1 high-performance gas turbine, the aerodynamic design of the compressor is the most important technology and a narrow bottleneck. In a three-shaft simple cycle gas turbine, the high-pressure compressor has extremely high aerodynamic design difficulty due to reasons such as a complex and variable incoming flow environment and significant influence of the true structure such as the upstream transition part. The high-efficiency and high-stability high-pressure compressor aerodynamic design technology has become a core technical element restricting the gas turbine development system. 【0003】 Due to the inherent characteristics of the overall layout of a three-shaft simple cycle gas turbine, the transition section structure connected between the low-pressure and high-pressure compressors significantly affects the intake resistance and uniformity of the high-pressure compressor, directly causing an increase in incoming flow resistance and a decrease in intake uniformity, rapidly deteriorating the matching of the high-pressure compressor's flow capacity with its internal flow. Therefore, developing effective technical means to improve the aerodynamic performance indicators of the high-pressure compressor first requires resolving the issue of the impact of the pressure loss and outlet non-uniformity of the transition section, caused by the overall layout, on the flow of the downstream high-pressure compressor. Current high-pressure compressor aerodynamic design methods basically perform low-level flow design based on uniform incoming flow conditions and do not consider the influence of the transition section. The disclosed solutions to the transition section problem can be summarized into two main types, but both have clear shortcomings. (1) Optimizing the flow in the transition section to reduce its influence as much as possible. (1) The method can improve the incoming flow conditions of the high-pressure compressor to some extent, but because the flow elements of the transition section are not substituted into the aerodynamic design of the high-pressure compressor, the performance of the high-pressure compressor is still affected by the upstream incoming flow due to the unavoidable losses and non-uniform flow conditions of the transition section. (2) The high-pressure compressor is aerodynamically designed according to a uniform incoming flow, and then iteratively optimized for the flow inside the high-pressure compressor using three-dimensional CFD or test means. This method helps to some extent to improve the performance of the high-pressure compressor, but it requires repeated iterative adjustments between the geometric design of the high-pressure compressor and the calculated three-dimensional CFD calculations or test processes, which consumes a great deal of time and resources. At the same time, the difference between the final high-pressure compressor obtained by extensively adjusting the geometric design and the original design is relatively large, and it often causes the internal load distribution and flow matching of the high-pressure compressor to deviate significantly from the design expectations. As can be seen from the above, conventional methods design and optimize the transition section and the high-pressure compressor as independent entities, lacking systemic consideration of the overall flow arrangement between the transition section and the high-pressure compressor. This limits the effectiveness of performance improvements, and the performance level of the high-pressure compressor remains a weakness and bottleneck in the current development of tri-shaft gas turbine technology. 【0004】 As gas turbine technology metrics continue to rise, the demands on compressor aerodynamic design levels are increasing. Designing a low-loss, highly adaptable transition-to-high-pressure compressor flow aerodynamic configuration directly impacts the overall performance level of the transition-to-high-pressure compressor system. Given the complex and highly interconnected relationship between the transition and high-pressure compressor, designing them as a single integrated unit is a rational approach to address these issues and achieve high-performance metrics. [Overview of the Initiative] [Problems that the invention aims to solve] 【0005】 The object of the present invention is to provide a multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor that can solve the difficult problem of improving the aerodynamic performance level of the gas turbine transition section-high pressure compressor system. [Means for solving the problem] 【0006】 The objective of this invention is achieved as follows. The present invention provides a multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor. (1) Decomposition of design indicators: A step of decomposing the performance indicators for the entire gas turbine transition section-high pressure compressor into performance indicators for the transition section and performance indicators for the high pressure compressor, (2) Flow design and optimization of the transition section: In accordance with the performance indicator requirements of the transition section, flow aerodynamic design and optimization of the transition section are performed, including end wall flow path shape line design, support plate shape line design and three-dimensional CFD calculation analysis, and it is determined whether the design requirements are met based on the results of the three-dimensional CFD calculation analysis. If the design requirements are not met, the end wall flow path shape line and support plate shape line of the transition section are optimized based on the calculation results, and a flow aerodynamic design means for the transition section that satisfies the performance indicator requirements of the transition section is obtained through repeated iterations. (3) Extraction of coupling parameters in different dimensions: Based on the flow aerodynamic design results of the transition section in step (2), key coupling design parameters in different dimensions of the transition section-high pressure compressor are extracted and converted into parameterized inputs for the design of each dimension of the integrated flow aerodynamic arrangement of the transition section-high pressure compressor, (4) Integrated flow aerodynamic arrangement design of the transition section and high-pressure compressor: In accordance with the performance indicator requirements of the high-pressure compressor, an integrated flow aerodynamic arrangement design of the transition section and high-pressure compressor is performed, including one-dimensional inverse problem flow design, one-dimensional characteristic analysis, S2 inverse problem flow design, blade shaping design and three-dimensional CFD calculation analysis, and it is determined whether the design requirements are met based on the results of the three-dimensional CFD calculation analysis, if the design requirements are met, the current aerodynamic design means is the final design means, if the design requirements are not met, an optimized design of the high-pressure compressor is performed based on the calculation results, and by iteratively obtaining an aerodynamic design means for the high-pressure compressor that finally satisfies the performance indicator requirements. 【0007】 The present invention may further include the following: 1. In step (1), the performance indicators for the entire gas turbine transition section-high-pressure compressor are decomposed into performance indicators for the transition section and performance indicators for the high-pressure compressor. Based on the requirements for flow capacity, supercharging capacity, efficiency, and stable operating range for the entire gas turbine transition section-high-pressure compressor, the converted flow rate and total pressure loss requirements for different incoming Mach numbers of the flow section are extracted and used as performance indicators for the transition section. The design point converted flow rate, pressure ratio, efficiency, and surge margin requirements for different rotational speeds of the high-pressure compressor, taking into account the influence of the transition section, are extracted and used as performance indicators for the high-pressure compressor. 2. The end wall flow path shape design described in step (2) employs an nth-order Bezier curve to perform parameterized design for the end wall flow path of the transition section, and the structural dimensional constraints for the low-pressure compressor, high-pressure compressor, and transition section of the gas turbine are used as boundary conditions for the Bezier curve. 3. The support plate shape line design described in step (2) employs a polynomial or polyarc airfoil to create a thickness distribution curve, performs cross-sectional shape line thickness distribution discrete analysis on the support plate, and uses the airfoil axial length, leading edge radius, trailing edge radius, and thickness distribution coefficient as variable parameters to realize parameterized design of the support plate shape line. 4. The optimization design of the end wall channel shape of the transition section described in step (2) employs a global optimization method that combines a test design method and a gradient optimization algorithm to optimize the end wall channel of the transition section. 5. The optimization design of the support plate shape line described in step (2) is performed by adopting an optimization policy that combines the test design method and the multi-island genetic algorithm to optimize the support plate shape line. 6. Extraction of key coupling design parameters in different dimensions of the transition-high pressure compressor as described in step (3) includes one-dimensional coupling parameters, S2 flow surface coupling parameters, and three-dimensional coupling parameters of the transition-high pressure compressor. 7. The one-dimensional coupling parameter is the total pressure recovery coefficient of the transition region. 8. The S2 flow surface coupling parameters are the two-dimensional coordinate values ​​of the transition section flow path and the support plate shape line. 9. The three-dimensional coupling parameters are a three-dimensional computational model of the transition fluid region, and include three-dimensional coordinate values ​​of the inner and outer wall flow channels and support plate shape lines. 10. The conversion of the dimensional design of the transition-high pressure compressor integrated flow aerodynamic arrangement described in step (3) to parameterized inputs includes parameterized inputs for one-dimensional inverse problem flow design and one-dimensional characteristic analysis, parameterized inputs for S2 inverse problem flow design, and parameterized inputs for three-dimensional CFD calculation analysis. 11. The parameterized inputs for the one-dimensional inverse problem flow design and one-dimensional characteristic analysis are realized by providing the total pressure recovery coefficient value for the transition section. 12. The parameterized inputs for the S2 inverse problem flow design are discretely converted into two-dimensional coordinate values ​​of the integrated meridian flow between the transition section and the high-pressure compressor, which are necessary for the S2 inverse problem flow design, by connecting, fitting, and smoothing the meridian flow shape lines to the transition section flow path and the high-pressure compressor main flow path obtained by the one-dimensional inverse problem flow design. 13. The parameterized inputs for the three-dimensional CFD calculation analysis form an integrated three-dimensional CFD calculation model of the transition region and the high-pressure compressor by connecting the three-dimensional calculation model of the transition region fluid zone to the three-dimensional calculation model of the high-pressure compressor fluid zone according to the actual geometric position. 14. The S2 inverse problem flow design described in step (4) involves dividing the calculation stations along the flow direction and radial direction for the meridional flow of the transition section-high-pressure compressor integrated system. In both the flow section of the transition section and the flow section of each blade row of the high-pressure compressor, five flow calculation stations and twelve radial calculation stations are divided, and the streamline curvature method is employed to solve the S2 inverse problem for the integrated flow of the transition section-high-pressure compressor system. 15. The optimization design of the high-pressure compressor described in step (4) involves performing stepwise distribution optimization adjustments for key parameters such as axial velocity, pressure ratio, and reaction rate of each stage of the high-pressure compressor in the one-dimensional inverse problem flow design, performing radial distribution optimization adjustments for key parameters such as absolute tangential velocity, pressure ratio, and loss coefficient at the inlet of each stage of the high-pressure compressor in the S2 inverse problem flow design, and performing inlet / outlet geometric matching optimization and three-dimensional design optimization of the end region for each stage blade of the high-pressure compressor in the blade design. [Effects of the Invention] 【0008】 The advantages of the present invention are as follows: 1. The present invention integrates the transition section and the high-pressure compressor into a single design based on a systemic approach, incorporates the influence factors of the transition section into the design process of each dimension of the high-pressure compressor, and fully considers the strong influence that the pressure loss and outlet non-uniformity of the transition section have on the high-pressure compressor from the initial design stage. This fundamentally solves the aerodynamic design challenges of the high-pressure compressor caused by the transition section and improves the performance level of the high-pressure compressor. 2. The present invention creatively and completely links the flow design of the transition section and the aerodynamic design of the high-pressure compressor, giving important consideration to the main factors affecting the performance of the transition section-high-pressure compressor system, thereby not only forming a low-loss flow means for the transition section but also obtaining an aerodynamic means for the high-pressure compressor based on the flow arrangement characteristics of the transition section, thereby maximizing the performance of both the transition section member and the high-pressure compressor member of the gas turbine, and thereby achieving a significant improvement in performance level. 3. The present invention fully explains the coupling design process and key parameters at each stage, permeates the aerodynamic design flow of the entire transition section-high pressure compressor system, and enables fine-tuning control of the flow loss of the transition section and the flow matching of the high pressure compressor by the method of the present invention, thereby achieving parameterization of the transition section-high pressure compressor system in different dimensions, refinement of the coupling aerodynamic design, and effectively improving design accuracy. 4. The present invention fully integrates with the upstream transition section at each dimension and stage of the aerodynamic design of the high-pressure compressor, fully considers and parameterizes the influencing factors of the transition section from the low-dimensional layer surface, effectively reduces the number of iterations in the design and development process, maintains maximum consistency between the high-pressure compressor means and the original design, obtains a high-performance aerodynamic means, saves optimization time, and shortens the development cycle. 5. The present invention is not limited to gas turbine high-pressure compressors, but is also applicable to the aerodynamic design process of aircraft engine high-pressure compressors and various industrial axial flow compressors with transition flow structures. [Brief explanation of the drawing] 【0009】 [Figure 1] This is a flowchart of the present invention. [Modes for carrying out the invention] 【0010】 The present invention will be described in more detail below with reference to the drawings and examples. Referring to FIG. 1, the specific implementation method of the multi-dimensional coupling design method for the flow aerodynamic layout of the gas turbine transition section - high-pressure compressor of the present invention is realized by the following steps. Step 1: Decomposition of design indicators. Decompose the performance indicators for the entire gas turbine transition section - high-pressure compressor into the performance indicators of the transition section and the performance indicators of the high-pressure compressor. 【0011】 Based on the requirements for the flow capacity, supercharging capacity, efficiency, and stable operating range of the entire gas turbine transition section - high-pressure compressor, extract the converted flow rate and total pressure loss requirements at different incoming flow Mach numbers in the flow passage part of the transition section, and use them as the performance indicators of the transition section. Extract the design point converted flow rate, pressure ratio, efficiency, and surge margin requirements at different rotational speeds of the high-pressure compressor considering the influence of the transition section, and use them as the performance indicators of the high-pressure compressor. 【0012】 Step 2: Flow passage design and optimization of the transition section. According to the performance indicator requirements of the transition section, perform flow aerodynamic design and optimization of the transition section, including end wall flow path shape line design, support plate shape line design, and three-dimensional CFD calculation and analysis. Here, For the end wall flow path shape line design of the transition section, use the nth-order Bezier curve for parametric description, and use the structural dimension constraint conditions for the low-pressure compressor, high-pressure compressor, and transition section of the gas turbine as the boundary conditions of the Bezier curve to realize the parametric design of the end wall flow path shape line of the transition section. 【0013】 For the support plate shape line design of the transition section, use a polynomial or multi-arc airfoil as the thickness distribution curve, perform cross-sectional shape line thickness distribution discretization on the support plate, and use the airfoil axial length, leading edge radius, trailing edge radius, and thickness distribution coefficient as variable parameters to realize the parametric design of the support plate shape line. 【0014】 Based on the three-dimensional CFD calculation and analysis results, judge whether the flow aerodynamic design means of the transition section meets the design requirements. If it does not meet the design requirements, perform optimization design of the end wall flow path shape line and support plate shape line of the transition section based on the calculation results. 【0015】 In the optimization design of the end-wall flow path shape line of the transition section, a global optimization method that combines the test design method and the gradient optimization algorithm is adopted to optimize the end-wall flow path of the transition section. 【0016】 In the optimization design of the support plate shape line of the transition section, an optimization policy that combines the test design method and the multi-island genetic algorithm is adopted to optimize the support plate shape line. 【0017】 By repeating the above operations iteratively, a through-flow aerodynamic design method for the transition section that meets the performance index requirements of the transition section is obtained. 【0018】 Step 3: Extraction of coupling parameters in different dimensions. Based on the through-flow aerodynamic design results of the transition section in Step 2, key coupling design parameters in different dimensions of the transition section - high-pressure compressor are extracted, including the one-dimensional coupling parameters, S2 flow surface coupling parameters, and three-dimensional coupling parameters of the transition section - high-pressure compressor. Here, One-dimensional coupling parameter: It is the total pressure recovery coefficient of the transition section, S2 flow surface coupling parameter: It is the two-dimensional coordinate values of the flow path of the transition section and the support plate shape line, Three-dimensional coupling parameter: It is the three-dimensional calculation model of the fluid domain of the transition section, including the three-dimensional coordinate values of the inner and outer wall flow paths and the support plate shape line. 【0019】 The above coupling design parameters are converted into parameterized inputs for the design of each dimension of the integrated through-flow aerodynamic layout of the transition section - high-pressure compressor, including the parameterized inputs for one-dimensional inverse problem through-flow design and one-dimensional characteristic analysis, the parameterized inputs for S2 inverse problem through-flow design, and the parameterized inputs for three-dimensional CFD calculation analysis. Here, The parameterized input for one-dimensional inverse problem through-flow design and one-dimensional characteristic analysis is realized by giving the total pressure recovery coefficient value of the transition section, The parameterized input for S2 inverse problem through-flow design is to discretize the integrated meridian through-flow two-dimensional coordinate values of the transition section - high-pressure compressor required for S2 inverse problem through-flow design by connecting, fitting, and smoothing the meridian through-flow shape lines of the flow path of the transition section and the high-pressure compressor body flow path obtained by one-dimensional inverse problem through-flow design. The parameterized input for the three-dimensional CFD calculation analysis forms an integrated transition-high-pressure compressor three-dimensional CFD calculation model by connecting the three-dimensional calculation model of the transition fluid domain to the three-dimensional calculation model of the high-pressure compressor fluid domain according to the actual geometric position. 【0020】 Step 4: Design of the integrated flow aerodynamic configuration for the transition section and high-pressure compressor. Depending on the performance indicator requirements for the high-pressure compressor, the integrated flow aerodynamic configuration for the transition section and high-pressure compressor is designed, including one-dimensional inverse problem flow design, one-dimensional characteristic analysis, S2 inverse problem flow design, blade shaping design, and three-dimensional CFD calculation analysis. In the S2 inverse problem flow design, the calculation station is divided along the flow direction and radial direction for the integrated meridional flow of the transition section and high-pressure compressor. Five flow calculation stations and twelve radial calculation stations are divided for both the flow section of the transition section and each blade row flow section of the high-pressure compressor, and the S2 inverse problem is solved for the integrated flow of the transition section and high-pressure compressor using the streamline curvature method. 【0021】 Based on the results of three-dimensional CFD calculation and analysis, it is determined whether the current means meets the design requirements. If the design requirements are met, the current aerodynamic design means is considered the final design means. If the design requirements are not met, the high-pressure compressor is optimized based on the calculation results. This includes performing stepwise distribution optimization adjustments for key parameters such as axial velocity, pressure ratio, and reaction rate of each stage of the high-pressure compressor in one-dimensional inverse problem flow design, performing radial distribution optimization adjustments for key parameters such as absolute tangential velocity, pressure ratio, and loss coefficient at the inlet of each stage of the high-pressure compressor in S2 inverse problem flow design, and performing inlet / outlet geometric matching optimization and three-dimensional design optimization of the end region for each stage blade of the high-pressure compressor in blade shaping design. By repeatedly performing the above operations, an aerodynamic design means for a high-pressure compressor that ultimately meets the performance index requirements is obtained. 【0022】 The method provided by the present invention is versatile and is not limited to gas turbine high-pressure compressors, but is also applicable to the aerodynamic design process of aircraft engine high-pressure compressors and various industrial axial flow compressors with transition flow structures.

Claims

[Claim 1] A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section - high-pressure compressor, (1) Decomposition of design indicators: A step of decomposing the performance indicators for the entire gas turbine transition section-high pressure compressor into performance indicators for the transition section and performance indicators for the high pressure compressor, (2) Flow design and optimization of the transition section: In accordance with the performance indicator requirements of the transition section, flow aerodynamic design and optimization of the transition section are performed, including end wall flow path shape line design, support plate shape line design and three-dimensional CFD calculation analysis, and it is determined whether the design requirements are met based on the results of the three-dimensional CFD calculation analysis. If the design requirements are not met, the end wall flow path shape line and support plate shape line of the transition section are optimized based on the calculation results, and a flow aerodynamic design means for the transition section that satisfies the performance indicator requirements of the transition section is obtained through repeated iterations. (3) Extraction of coupling parameters in different dimensions: Based on the flow aerodynamic design results of the transition section in step (2), key coupling design parameters in different dimensions of the transition section-high pressure compressor are extracted and converted into parameterized inputs for the design of each dimension of the integrated flow aerodynamic arrangement of the transition section-high pressure compressor. Extraction of key coupling design parameters in different dimensions of the transition section-high pressure compressor includes one-dimensional coupling parameters, S2 flow surface coupling parameters, and three-dimensional coupling parameters of the transition section-high pressure compressor. The conversion of the transition section-high-pressure compressor integrated flow aerodynamic arrangement into parameterized inputs for each dimension of the design includes steps such as parameterized inputs for one-dimensional inverse problem flow design and one-dimensional characteristic analysis, parameterized inputs for S2 inverse problem flow design, and parameterized inputs for three-dimensional CFD calculation analysis. (4) Integrated flow aerodynamic arrangement design of the transition section and high-pressure compressor: In accordance with the performance indicator requirements of the high-pressure compressor, an integrated flow aerodynamic arrangement design of the transition section and high-pressure compressor is performed, including one-dimensional inverse problem flow design, one-dimensional characteristic analysis, S2 inverse problem flow design, blade shaping design and three-dimensional CFD calculation analysis, and it is determined whether the design requirements are met based on the results of the three-dimensional CFD calculation analysis, if the design requirements are met, the current aerodynamic design means is the final design means, if the design requirements are not met, an optimized design of the high-pressure compressor is performed based on the calculation results, and by iteratively obtaining an aerodynamic design means for the high-pressure compressor that finally meets the performance indicator requirements. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor, characterized by the above. [Claim 2] Step (1) involves decomposing the performance indicators for the entire gas turbine transition section-high-pressure compressor into performance indicators for the transition section and performance indicators for the high-pressure compressor. This is done by extracting the converted flow rate and total pressure loss requirements for different incoming Mach numbers in the flow section of the transition section, based on the requirements for flow capacity, supercharging capacity, efficiency, and stable operating range for the entire gas turbine transition section-high-pressure compressor, and using these as performance indicators for the transition section. It also involves extracting the design point converted flow rate, pressure ratio, efficiency, and surge margin requirements for the high-pressure compressor at different rotational speeds, taking into account the influence of the transition section, and using these as performance indicators for the high-pressure compressor. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1. [Claim 3] The end wall flow path shape design described in step (2) employs an nth-order Bezier curve to perform parameterized design for the end wall flow path of the transition section, and uses the structural dimensional constraints for the low-pressure compressor, high-pressure compressor, and transition section of the gas turbine as boundary conditions for the Bezier curve. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1. [Claim 4] Step (2) describes the support plate shape line design, which employs a polynomial or polyarc airfoil to create a thickness distribution curve, performs cross-sectional shape line thickness distribution discrete analysis on the support plate, and uses the airfoil axial length, leading edge radius, trailing edge radius, and thickness distribution coefficient as variable parameters to realize parameterized design of the support plate shape line. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1. [Claim 5] Step (2) describes the optimization design of the end wall channel shape of the transition section, employing a global optimization method that combines a test design method and a gradient optimization algorithm to optimize the end wall channel of the transition section. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1. [Claim 6] Step (2) describes the optimization design of the support plate shape line, which employs a combined optimization policy of the test design method and the multi-island genetic algorithm to optimize the support plate shape line. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1. [Claim 7] The aforementioned one-dimensional coupling parameter is the total pressure recovery coefficient of the transition region. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1. [Claim 8] The S2 flow surface coupling parameter is the two-dimensional coordinate value of the transition section flow path and the support plate shape line. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1. [Claim 9] The aforementioned three-dimensional coupling parameters are a three-dimensional computational model of the transition fluid region, and include three-dimensional coordinate values ​​of the inner and outer wall flow paths and support plate shape lines. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1. [Claim 10] The parameterized inputs for the one-dimensional inverse problem flow design and one-dimensional characteristic analysis are provided by giving the total pressure recovery coefficient value of the transition section. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1. [Claim 11] The parameterized inputs for the S2 inverse flow design are discretely broken down into two-dimensional coordinate values ​​of the integrated meridian flow between the transition section and the high-pressure compressor, which are necessary for the S2 inverse flow design, by connecting, fitting, and smoothing the meridian flow shape lines to the transition section flow path and the high-pressure compressor main flow path obtained by the one-dimensional inverse flow design. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1. [Claim 12] The parameterized inputs for the aforementioned three-dimensional CFD calculation analysis connect the three-dimensional calculation model of the transition fluid region to the three-dimensional calculation model of the high-pressure compressor fluid region according to the actual geometric position, thereby forming an integrated three-dimensional CFD calculation model of the transition region and the high-pressure compressor. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1. [Claim 13] The S2 inverse problem flow design described in step (4) involves dividing the calculation stations along the flow direction and radial direction for the meridional flow of the transition section and high-pressure compressor integrated system. In both the flow section of the transition section and the flow section of each blade row of the high-pressure compressor, five flow calculation stations and twelve radial calculation stations are divided, and the streamline curvature method is employed to solve the S2 inverse problem for the integrated flow of the transition section and high-pressure compressor. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1. [Claim 14] The optimization design of the high-pressure compressor described in step (4) includes performing stepwise distribution optimization adjustments for key parameters such as axial velocity, pressure ratio, and reaction rate of each stage of the high-pressure compressor in the one-dimensional inverse problem flow design, performing radial distribution optimization adjustments for key parameters such as absolute tangential velocity, pressure ratio, and loss coefficient at the inlet of each stage of the high-pressure compressor in the S2 inverse problem flow design, and performing inlet / outlet geometric matching optimization and three-dimensional design optimization of the end region for each stage blade of the high-pressure compressor in the blade design. A multidimensional coupling design method for the flow aerodynamic arrangement of a gas turbine transition section-high pressure compressor as described in claim 1.

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