Multidimensional coupled design method for transition section-high-pressure compressor through-flow aerodynamic layout of gas turbine engine

Abstract

The present invention aims to provide a multidimensional coupled design method for transition section-high-pressure compressor through-flow aerodynamic layout of a gas turbine engine. In the present invention, a transition section and a high-pressure compressor are integrated as a system for coupled design, and full integration with the upstream transition section is performed in dimensions and links of aerodynamic design of the high-pressure compressor, achieving integrated collaborative design of transition section-high-pressure compressor through-flow layout; as a result, the aerodynamic design of transition section-high-pressure compressor in different dimensions enters systematization, parametrization and refinement phases, which effectively improves the aerodynamic performance of the high-pressure compressor, enhances aerodynamic design accuracy, saves a lot of design iteration time, and shortens a design cycle; and therefore, the method is very suitable for engineering design applications. The present invention is not limited to gas turbine engine high-pressure compressors, but is also applicable to the aerodynamic design process of aeroengine high-pressure compressors, and various industrial axial-flow compressors having transition through-flow structures.

Description

A multi-dimensional coupling design method for the flow aerodynamic layout of the transition section and high-pressure compressor of a gas turbine Technical Field

[0001] The present invention relates to a gas turbine design method, in particular to a compressor design method. Background Art

[0002] As one of the three core components of a gas turbine, the performance of the compressor directly determines the technical specifications of the gas turbine. The aerodynamic design of the compressor is the primary key technology and bottleneck in the development of a high-performance gas turbine. In a three-spool simple cycle gas turbine, the high-pressure compressor presents extremely high aerodynamic design challenges due to the complex and changing incoming flow environment and the significant influence of real structural factors such as the upstream transition section. High-efficiency and high-stability aerodynamic design technology for high-pressure compressors has become a core technical link that restricts the gas turbine R&D system.

[0003] Due to the inherent characteristics of the overall layout of the three-rotor simple cycle gas turbine, the transition section structure connecting the low-pressure and high-pressure compressors will have a significant impact on the intake resistance and uniformity of the high-pressure compressor, directly leading to an increase in the inlet flow resistance of the high-pressure compressor and a decrease in the intake uniformity, which will rapidly deteriorate the flow capacity and internal flow matching of the high-pressure compressor. Therefore, in order to develop effective technical means to improve the aerodynamic performance indicators of the high-pressure compressor, it is necessary to first solve the problem of the pressure loss of the transition section and the uneven outlet caused by the overall layout on the flow of the downstream high-pressure compressor. The current aerodynamic design method of the high-pressure compressor is basically to perform low-dimensional flow design according to the uniform inlet flow conditions, and does not take the influence of the transition section into consideration. The public solutions to the transition section problem can be summarized into two main types, but both have obvious shortcomings: (1) Optimize the flow of the transition section to minimize the influence of the transition section. This method can improve the high-pressure compressor inflow conditions to a certain extent, but it does not incorporate the transition section flow factors into the aerodynamic design of the high-pressure compressor. Due to the inevitable loss and uneven flow state in the transition section, the performance of the high-pressure compressor is still affected by the upstream inflow; (2) The high-pressure compressor is aerodynamically designed according to the uniform inflow, and then the internal flow of the high-pressure compressor is iteratively optimized through three-dimensional CFD or experimental testing. This method is helpful to improve the performance of the high-pressure compressor, but it requires a large number of three-dimensional CFD calculations or test processes, and repeated iterative adjustments between the high-pressure compressor geometry, which consumes a lot of time and resources. At the same time, the final high-pressure compressor scheme obtained by a large number of geometric adjustments is quite different from the original design, which often causes the internal load distribution and flow matching of the high-pressure compressor to deviate seriously from the design expectations. It can be seen that the existing method is limited in performance improvement because it treats the transition section and the high-pressure compressor as independent objects for design optimization and lacks systematic consideration of the overall flow layout of the transition section-high-pressure compressor. The performance level of the high-pressure compressor is still a short board bottleneck in the current development of three-rotor gas turbine technology.

[0004] As gas turbine technical specifications continue to rise, higher demands are placed on compressor aerodynamic design. Designing a low-loss, adaptable transition section-to-high-pressure compressor flow aerodynamic layout directly impacts the performance of the entire transition section-to-high-pressure compressor system. The interaction between the transition section and the high-pressure compressor is complex and highly correlated. Designing the two as a cohesive whole is a logical approach to addressing these challenges and achieving high performance. Summary of the Invention

[0005] The purpose of the present invention is to provide a multi-dimensional coupling design method for the flow aerodynamic layout of a gas turbine transition section-high-pressure compressor that can solve the problem of improving the aerodynamic performance level of the gas turbine transition section-high-pressure compressor system.

[0006] The object of the present invention is achieved like this:

[0007] The present invention provides a multi-dimensional coupling design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout, which is characterized by comprising the following steps:

[0008] (1) Design index decomposition: Decompose the overall performance index of the gas turbine transition section-high-pressure compressor into the transition section performance index and the high-pressure compressor performance index;

[0009] (2) Transition section flow design and optimization: According to the performance index requirements of the transition section, the transition section flow aerodynamic design and optimization are carried out, including the end wall flow channel profile design, the support plate profile design and three-dimensional CFD calculation analysis. The three-dimensional CFD calculation and analysis results are used to determine whether the design requirements are met. If the design requirements are not met, the transition section end wall flow channel profile and support plate profile are optimized according to the calculation results. Through repeated iterations, a transition section flow aerodynamic design scheme that meets the performance index requirements of the transition section is obtained;

[0010] (3) Extraction of coupling parameters in different dimensions: Based on the transition section flow aerodynamic design results in step (2), the key coupling design parameters of the transition section-high pressure compressor in different dimensions are extracted and converted into parameterized inputs for the design of the transition section-high pressure compressor integrated flow aerodynamic layout in each dimension;

[0011] (4) Transition section-high pressure compressor integrated flow aerodynamic layout design: According to the high pressure compressor performance index requirements, the transition section-high pressure compressor integrated flow aerodynamic layout design is carried out, including one-dimensional inverse problem flow design, one-dimensional characteristic analysis, S2 inverse problem flow design, blade shape design and three-dimensional CFD calculation analysis. The three-dimensional CFD calculation analysis results are used to judge whether the design requirements are met. If the design requirements are met, the current aerodynamic design scheme is the final design scheme; if not, the high pressure compressor is optimized according to the calculation results. Through repeated iterations, the high pressure compressor aerodynamic design scheme that meets the performance index requirements is finally obtained.

[0012] The present invention may also include:

[0013] 1. In step (1), the performance index of the gas turbine for the transition section-high-pressure compressor as a whole is decomposed into the transition section performance index and the high-pressure compressor performance index. Based on the flow capacity, boosting capacity, efficiency and stable operating range requirements of the gas turbine for the transition section-high-pressure compressor as a whole, the requirements for the reduced flow rate and total pressure loss of the transition section flow part at different incoming flow Mach numbers are extracted as the transition section performance index. The requirements for the reduced flow rate, pressure ratio, efficiency and surge margin at different speeds of the high-pressure compressor at the design point considering the influence of the transition section are extracted as the high-pressure compressor performance index.

[0014] 2. The end wall flow channel profile design described in step (2) uses an n-order Bezier curve to perform parameterized design on the end wall flow channel of the transition section, and the structural size constraints of the gas turbine on the low-pressure compressor, high-pressure compressor and transition section are used as the boundary conditions of the Bezier curve.

[0015] 3. The support plate profile design described in step (2) uses a polynomial or multi-arc airfoil as the thickness distribution curve, discretizes the cross-sectional profile thickness distribution of the support plate, and uses the airfoil axial length, leading edge radius, trailing edge radius and thickness distribution coefficient as variable parameters to achieve parametric design of the support plate profile.

[0016] 4. The optimization design of the transition section end wall flow channel profile described in step (2) adopts a global optimization method combining the experimental design method with the gradient optimization algorithm to optimize the transition section end wall flow channel.

[0017] 5. The support plate profile is optimized in step (2) by using a combination optimization strategy of experimental design method and multi-island genetic algorithm to optimize the support plate profile.

[0018] 6. Extract the key coupling design parameters of the transition section-high pressure compressor in different dimensions as described in step (3), including the one-dimensional coupling parameters of the transition section-high pressure compressor, the S2 flow surface coupling parameters, and the three-dimensional coupling parameters.

[0019] 7. The one-dimensional coupling parameter is the total pressure recovery coefficient of the transition section.

[0020] 8. The S2 flow surface coupling parameter is the two-dimensional coordinate value of the transition section flow channel and the support plate profile.

[0021] 9. The three-dimensional coupling parameters are the three-dimensional calculation model of the transition section fluid domain, including the three-dimensional coordinate values ​​of the inner and outer wall flow channels and the support plate profile.

[0022] 10. The conversion described in step (3) into parameterized inputs for the design of each dimension of the transition section-high-pressure compressor integrated flow aerodynamic layout 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 and analysis.

[0023] 11. The parameterized input of the one-dimensional inverse problem flow design and one-dimensional characteristic analysis is achieved by giving a total pressure recovery coefficient value of the transition section.

[0024] 12. The parametric input of the S2 inverse problem flow design is obtained by connecting, fitting and smoothing the meridional flow lines of the transition section flow channel and the high-pressure compressor main flow channel obtained by the one-dimensional inverse problem flow design, and discretizing them into the two-dimensional coordinate values ​​of the transition section-high-pressure compressor integrated meridional flow required for the S2 inverse problem flow design.

[0025] 13. The parameterized input of the three-dimensional CFD calculation analysis is formed by connecting the three-dimensional calculation model of the transition section fluid domain with the three-dimensional calculation model of the high-pressure compressor fluid domain according to the actual geometric position, thereby forming an integrated three-dimensional CFD calculation model of the transition section and the high-pressure compressor.

[0026] 14. For the S2 inverse flow design described in step (4), the transition section-high pressure compressor integrated meridional flow is divided into calculation stations along the flow direction and radial direction. Five flow direction calculation stations and 12 radial calculation stations are divided in the transition section flow part and the flow part of each blade row of the high pressure compressor. The streamline curvature method is used to solve the S2 inverse problem of the transition section-high pressure compressor integrated flow.

[0027] 15. The optimization design of the high-pressure compressor described in step (4) includes optimizing and adjusting the key parameters of the axial velocity, pressure ratio and reaction degree of each stage of the high-pressure compressor in the one-dimensional inverse flow design, optimizing and adjusting the key parameters of the absolute tangential velocity, pressure ratio and loss coefficient at the inlet of each stage of the high-pressure compressor in the S2 inverse flow design, and optimizing the inlet and outlet geometric angle matching and the three-dimensional design of the end area of ​​each stage of the high-pressure compressor blade in the blade shape design.

[0028] The advantages of the present invention are:

[0029] 1. The present invention adopts a systematic approach to couple the design of the transition section and the high-pressure compressor as a whole, and incorporates the influencing factors of the transition section into the design process of all dimensions of the high-pressure compressor. From the very beginning of the design of the high-pressure compressor, the strong impact of the pressure loss and outlet unevenness of the transition section on the high-pressure compressor is fully taken into account. This can fundamentally solve the aerodynamic design problems of the high-pressure compressor caused by the transition section and improve the performance level of the high-pressure compressor.

[0030] 2. The present invention creatively fully links the transition section flow design with the high-pressure compressor aerodynamic design, and focuses on the main factors affecting the performance of the entire transition section-high-pressure compressor system. It not only forms a low-loss transition section flow scheme, but also obtains a high-pressure compressor aerodynamic scheme based on the transition section flow layout characteristics, so that the performance of both the transition section components and the high-pressure compressor components of the gas turbine are maximized, thereby achieving a significant improvement in performance level.

[0031] 3. The present invention fully explains the coupling design process and the key parameters in each link, and runs through the entire aerodynamic design process of the transition section-high-pressure compressor system. Through the method of the present invention, the transition section flow loss and the high-pressure compressor flow matching can be finely controlled, realizing the parameterized and refined coupled aerodynamic design of the transition section-high-pressure compressor system in different dimensions, effectively improving the design accuracy.

[0032] 4. The present invention fully integrates the upstream transition section in all dimensions and links of the high-pressure compressor aerodynamic design. It fully considers the influencing factors brought by the transition section from the low-dimensional level and performs parameterization. It can effectively reduce the number of iterations in the design and development process and maintain the consistency of the high-pressure compressor scheme with the original design to the greatest extent. While obtaining a high-performance aerodynamic scheme, it saves optimization time and shortens the R&D cycle.

[0033] 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 transitional flow structures. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] FIG1 is a flow chart of the present invention. DETAILED DESCRIPTION

[0035] The present invention will be described in more detail below with reference to the accompanying drawings:

[0036] 1 , a specific embodiment of a multi-dimensional coupled design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to the present invention is implemented by the following steps:

[0037] Step 1: Decomposition of design indicators. Decompose the overall performance indicators of the gas turbine transition section-high-pressure compressor into transition section performance indicators and high-pressure compressor performance indicators.

[0038] According to the gas turbine's requirements for the overall flow capacity, boost capacity, efficiency and stable operating range of the transition section-high-pressure compressor, the requirements for the reduced flow rate and total pressure loss of the transition section flow part at different incoming flow Mach numbers are extracted as the transition section performance indicators. The requirements for the reduced flow rate, pressure ratio, efficiency and surge margin at different speeds of the high-pressure compressor at the design point considering the influence of the transition section are extracted as the high-pressure compressor performance indicators.

[0039] Step 2: Transition section flow design and optimization. According to the performance index requirements of the transition section, the aerodynamic design and optimization of the transition section flow are carried out, including the design of the end wall flow channel profile, the support plate profile design and 3D CFD calculation analysis, etc.

[0040] The end wall flow channel profile design of the transition section is parametrically described using the n-order Bezier curve, and the structural size constraints of the gas turbine on the low-pressure compressor, high-pressure compressor and transition section are used as the boundary conditions of the Bezier curve to realize the parametric design of the end wall flow channel profile of the transition section.

[0041] The strut profile design of the transition section adopts a polynomial or multi-arc airfoil as the thickness distribution curve, discretizes the thickness distribution of the cross-sectional profile of the strut, and uses the airfoil axial length, leading edge radius, trailing edge radius and thickness distribution coefficient as variable parameters to realize the parametric design of the strut profile.

[0042] The results of three-dimensional CFD calculation and analysis are used to determine whether the aerodynamic design scheme of the transition section flow meets the design requirements. If it does not meet the design requirements, the transition section end wall flow channel profile and support plate profile are optimized according to the calculation results.

[0043] In the optimization design of the flow channel profile of the transition section end wall, a global optimization method combining the experimental design method with the gradient optimization algorithm is used to optimize the flow channel of the transition section end wall.

[0044] In the optimization design of the branch plate profile of the transition section, a combined optimization strategy of experimental design method and multi-island genetic algorithm is adopted to optimize the branch plate profile.

[0045] Through repeated iterations of the above work, an aerodynamic design scheme for the transition section flow that meets the performance index requirements of the transition section was obtained.

[0046] Step 3: Extract coupling parameters in different dimensions. Based on the aerodynamic design results of the transition section flow in step 2, extract the key coupling design parameters of the transition section-high-pressure compressor in different dimensions, including the one-dimensional coupling parameters of the transition section-high-pressure compressor, the S2 flow surface coupling parameters, and the three-dimensional coupling parameters. Among them:

[0047] One-dimensional coupling parameter: total pressure recovery coefficient of transition section;

[0048] S2 flow surface coupling parameter: the two-dimensional coordinate value of the transition section flow channel and the support plate profile;

[0049] Three-dimensional coupling parameters: It is the three-dimensional calculation model of the fluid domain in the transition section, including the three-dimensional coordinate values ​​of the inner and outer wall flow channels and the support plate profile.

[0050] The above coupled design parameters are converted into parameterized inputs for the design of each dimension of the transition section-high-pressure compressor integrated flow aerodynamic layout, including parameterized inputs for one-dimensional inverse flow design and one-dimensional characteristic analysis, parameterized inputs for S2 inverse flow design, and parameterized inputs for three-dimensional CFD calculation and analysis.

[0051] The parameterized input of one-dimensional inverse flow design and one-dimensional characteristic analysis is achieved by giving the total pressure recovery coefficient value of the transition section;

[0052] The parametric input of the S2 inverse flow design is obtained by connecting, fitting and smoothing the meridian flow profiles of the transition section flow channel and the high-pressure compressor main flow channel obtained by the one-dimensional inverse flow design, and discretizing them into the two-dimensional coordinate values ​​of the transition section-high-pressure compressor integrated meridian flow required by the S2 inverse flow design.

[0053] The parametric input of the 3D CFD calculation analysis forms an integrated 3D CFD calculation model of the transition section and the high-pressure compressor by connecting the 3D calculation model of the transition section fluid domain with the 3D calculation model of the high-pressure compressor fluid domain according to the actual geometric position.

[0054] Step 4: Aerodynamic layout design of transition section-high pressure compressor integrated flow. According to the performance index requirements of the high pressure compressor, the aerodynamic layout design of the transition section-high pressure compressor integrated flow is carried out, including one-dimensional inverse problem flow design, one-dimensional characteristic analysis, S2 inverse problem flow design, blade shape design and three-dimensional CFD calculation analysis. In the S2 inverse problem flow design, the transition section-high pressure compressor integrated meridional flow is divided into calculation stations along the flow direction and radial direction. The transition section flow part and the flow part of each blade row of the high pressure compressor are divided into 5 flow direction calculation stations and 12 radial calculation stations. The streamline curvature method is used to solve the S2 inverse problem of the transition section-high pressure compressor integrated flow.

[0055] Based on the results of the three-dimensional CFD calculation and analysis, it is determined whether the current solution meets the design requirements. If it does, the current aerodynamic design solution can be considered the final design solution. If it does not, the high-pressure compressor is optimized based on the calculation results. This includes optimizing the distribution of key parameters such as the axial velocity, pressure ratio, and reaction degree of each stage of the high-pressure compressor in the one-dimensional inverse flow design, optimizing the distribution of key parameters such as the absolute tangential velocity, pressure ratio, and loss coefficient at the inlet of each stage of the high-pressure compressor in the S2 inverse flow design, and optimizing the inlet and outlet geometric angle matching and the three-dimensional design of the end area of ​​each stage of the high-pressure compressor in the blade shape design. Through repeated iterations of the above work, an aerodynamic design solution for the high-pressure compressor that meets the performance index requirements is finally obtained.

[0056] The method proposed in the present invention is universal 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

1. A multi-dimensional coupled design method for a gas turbine transition section-high-pressure compressor flow aerodynamic layout, characterized by: The following steps are involved: (1) Design index decomposition: Decompose the overall performance index of the gas turbine transition section-high-pressure compressor into the transition section performance index and the high-pressure compressor performance index; (2) Transition section flow design and optimization: According to the performance index requirements of the transition section, the transition section flow aerodynamic design and optimization are carried out, including the end wall flow channel profile design, the support plate profile design and three-dimensional CFD calculation analysis. The three-dimensional CFD calculation and analysis results are used to determine whether the design requirements are met. If the design requirements are not met, the transition section end wall flow channel profile and support plate profile are optimized according to the calculation results. Through repeated iterations, a transition section flow aerodynamic design scheme that meets the performance index requirements of the transition section is obtained; (3) Extraction of coupling parameters in different dimensions: Based on the transition section flow aerodynamic design results in step (2), the key coupling design parameters of the transition section-high pressure compressor in different dimensions are extracted and converted into parameterized inputs for the design of the transition section-high pressure compressor integrated flow aerodynamic layout in each dimension; Extract key coupling design parameters of the transition section-high pressure compressor in different dimensions, including one-dimensional coupling parameters of the transition section-high pressure compressor, S2 flow surface coupling parameters, and three-dimensional coupling parameters; Converted into parameterized input for the design of each dimension of the transition section-high-pressure compressor integrated flow aerodynamic layout, including parameterized input for one-dimensional inverse flow design and one-dimensional characteristic analysis, parameterized input for S2 inverse flow design, and parameterized input for three-dimensional CFD calculation and analysis; (4) Transition section-high pressure compressor integrated flow aerodynamic layout design: According to the high pressure compressor performance index requirements, the transition section-high pressure compressor integrated flow aerodynamic layout design is carried out, including one-dimensional inverse flow design, one-dimensional characteristic analysis, S2 inverse flow design, blade shape design and three-dimensional CFD calculation analysis. The three-dimensional CFD calculation analysis results are used to determine whether the design requirements are met. If the design requirements are met, the current aerodynamic design scheme is the final design scheme; If the design requirements are not met, the high-pressure compressor will be optimized based on the calculation results. Through repeated iterations, the aerodynamic design scheme of the high-pressure compressor that meets the performance index requirements will eventually be obtained.

2. The multi-dimensional coupled design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1 is characterized by: In step (1), the overall performance index of the gas turbine for the transition section-high-pressure compressor is decomposed into the transition section performance index and the high-pressure compressor performance index. Based on the overall flow capacity, boost capacity, efficiency and stable operating range requirements of the gas turbine for the transition section-high-pressure compressor, the requirements for the equivalent flow rate and total pressure loss of the transition section flow part at different incoming flow Mach numbers are extracted as the transition section performance index. The requirements for the equivalent flow rate, pressure ratio, efficiency and surge margin at different speeds of the high-pressure compressor at the design point considering the influence of the transition section are extracted as the high-pressure compressor performance index.

3. The multi-dimensional coupled design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1 is characterized by: The end wall flow channel profile design described in step (2) uses an n-order Bezier curve to perform parameterized design on the end wall flow channel of the transition section, and the structural size constraints of the gas turbine on the low-pressure compressor, high-pressure compressor and transition section are used as the boundary conditions of the Bezier curve.

4. The multi-dimensional coupling design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1 is characterized by: The support plate profile design described in step (2) uses a polynomial or multi-arc airfoil as a thickness distribution curve, discretizes the cross-sectional profile thickness distribution of the support plate, and uses the airfoil axial length, leading edge radius, trailing edge radius and thickness distribution coefficient as variable parameters to achieve parametric design of the support plate profile.

5. The multi-dimensional coupling design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1 is characterized by: The optimization design of the transition section end wall flow channel profile described in step (2) adopts a global optimization method combining the experimental design method with the gradient optimization algorithm to optimize the transition section end wall flow channel.

6. The multi-dimensional coupled design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1 is characterized by: The optimization design of the support plate profile described in step (2) adopts a combined optimization strategy of experimental design method and multi-island genetic algorithm to optimize the support plate profile.

7. The multi-dimensional coupling design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1 is characterized by: The one-dimensional coupling parameter is the total pressure recovery coefficient of the transition section.

8. The multi-dimensional coupled design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1 is characterized by: The S2 flow surface coupling parameter is the two-dimensional coordinate value of the transition section flow channel and the support plate profile.

9. The multi-dimensional coupled design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1 is characterized by: The three-dimensional coupling parameters are a three-dimensional calculation model of the transition section fluid domain, including the three-dimensional coordinate values ​​of the inner and outer wall flow channels and the support plate profile.

10. The multi-dimensional coupling design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1, characterized in that: The parameterized input of the one-dimensional inverse problem flow design and one-dimensional characteristic analysis is achieved by giving a total pressure recovery coefficient value of the transition section.

11. The multi-dimensional coupling design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1, characterized in that: The parameterized input of the S2 inverse problem flow design is discretized into the two-dimensional coordinate values ​​of the transition section-high-pressure compressor integrated meridional flow required for the S2 inverse problem flow design by connecting, fitting and smoothing the meridional flow profiles of the transition section flow channel and the high-pressure compressor main body flow channel obtained by the one-dimensional inverse problem flow design.

12. The multi-dimensional coupling design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1, characterized in that: The parameterized input of the three-dimensional CFD calculation analysis forms an integrated three-dimensional CFD calculation model of the transition section and the high-pressure compressor by connecting the three-dimensional calculation model of the transition section fluid domain with the three-dimensional calculation model of the high-pressure compressor fluid domain according to the actual geometric position.

13. The multi-dimensional coupling design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1, characterized in that: The S2 inverse problem flow design described in step (4) divides the transition section-high pressure compressor integrated meridional flow into calculation stations along the flow direction and radial direction. The transition section flow part and the flow part of each blade row of the high pressure compressor are divided into 5 flow direction calculation stations and 12 radial calculation stations. The streamline curvature method is used to solve the S2 inverse problem of the transition section-high pressure compressor integrated flow.

14. The multi-dimensional coupling design method for a gas turbine transition section-high pressure compressor flow aerodynamic layout according to claim 1, characterized in that: The optimization design of the high-pressure compressor described in step (4) includes optimizing and adjusting the key parameters of the axial velocity, pressure ratio and reaction degree of each stage of the high-pressure compressor in the one-dimensional inverse problem flow design, optimizing and adjusting the key parameters of the absolute tangential velocity, pressure ratio and loss coefficient at the inlet of each stage of the high-pressure compressor along the diameter in the S2 inverse problem flow design, and optimizing the inlet and outlet geometric angle matching and the three-dimensional design of the end area of ​​the blades of each stage of the high-pressure compressor in the blade shape design.

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