An integrated aerodynamic design method for the flow path layout of a gas turbine transition section - high-pressure compressor

Abstract

The object of the present invention is to provide an integrated aerodynamic design method for the flow path layout of a gas turbine transition section - high-pressure compressor. By directly introducing the pressure loss caused by the transition section and the influence of non-uniform intake air into the corresponding links in each dimension of the high-pressure compressor aerodynamic design, the overall design of the transition section and the high-pressure compressor flow path layout is truly realized, effectively improving the aerodynamic performance of the high-pressure compressor. Moreover, it can parameterize and refine the aerodynamic design of the transition section - high-pressure compressor system in different dimensions, so as to quickly obtain a high-pressure compressor aerodynamic design scheme with excellent performance, effectively improving the design accuracy, saving a large amount of design iteration time, shortening the design cycle, and being very suitable for engineering design applications. The present invention is not limited to the high-pressure compressor of a gas turbine, and is also applicable to the aerodynamic design process of the high-pressure compressor of an aeroengine and various industrial axial compressors with a transition flow structure.

Description

Technical Field

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

[0002] As one of the three most important core components of a gas turbine, the performance of the compressor plays a decisive role in achieving the technical indicators of the gas turbine. Summarizing the entire development process of gas turbines worldwide, the aerodynamic design technology of the compressor is at the forefront in the development of gas turbines and is the primary key technology and difficult topic. Among them, due to complex reasons such as the significant influence of the upstream transition section and other real structures on the high-pressure compressor, its aerodynamic design is extremely difficult and has become the core bottleneck link in the entire compressor aerodynamic design system.

[0003] Affected by the position of the overall engine layout, the high-pressure compressor in the gas turbine faces non-uniform intake air and pressure loss caused by the upstream transition section, and the complex incoming flow environment will directly affect the performance of the high-pressure compressor. How to fully consider the influence of the transition section in the aerodynamic design of the high-pressure compressor and solve the problem of performance attenuation of the high-pressure compressor caused by the through-flow layout of the transition section is directly related to the performance level of the entire transition section-high-pressure compressor system. Therefore, it is necessary to explore new aerodynamic design means and methods to achieve a breakthrough in the overall through-flow layout design of the transition section-high-pressure compressor in order to better improve the performance indicators of the gas turbine compressor components. Summary of the Invention

[0004] The purpose of the present invention is to provide an integrated aerodynamic design method for the through-flow layout of the transition section-high-pressure compressor of a gas turbine, which can solve the difficult problems in the aerodynamic design of the high-pressure compressor caused by the through-flow layout of the transition section of the gas turbine.

[0005] The purpose of the present invention is achieved as follows:

[0006] An integrated aerodynamic design method for the through-flow layout of the transition section-high-pressure compressor of a gas turbine according to the present invention is characterized by including the following steps:

[0007] (1) Through-flow design of the transition section: Conduct aerodynamic design on the through-flow part of the transition section, including the end-wall flow path profile and internal struts, to obtain the total pressure recovery coefficient, meridional through-flow profile, and three-dimensional CFD calculation model of the transition section;

[0008] (2) One-dimensional inverse problem through-flow design: According to the performance index requirements and design input conditions of the high-pressure compressor, determine the input parameters for the one-dimensional inverse problem through-flow design, including rotational speed, pressure ratio, flow rate, inlet and outlet air flow conditions, and geometric conditions, and at the same time consider the influence of the upstream transition section through-flow structure;

[0009] (3) One-dimensional characteristic analysis: Based on the meridional flow of the high-pressure compressor and the geometric parameters of the elemental stage at the middle section obtained from the one-dimensional inverse problem through-flow design, considering the influence of the upstream transition section's through-flow structure, perform the one-dimensional forward problem characteristic calculation and analysis of the high-pressure compressor to preliminarily predict the overall performance of the high-pressure compressor under the condition of including the upstream transition section;

[0010] (4) S2 inverse problem through-flow design: Based on the meridional flow profile of the transition section obtained in step (1) and the meridional flow profile of the high-pressure compressor obtained in step (2), solve the integrated S2 inverse problem of the transition section - high-pressure compressor with the through-flow aerodynamic layout of the transition section to obtain the radial aerodynamic parameter distribution of the moving and stationary blade rows of each stage of the axial compressor;

[0011] (5) Blade profile design: Based on the radial aerodynamic parameter distribution results of the moving and stationary blade rows of each stage obtained from the S2 inverse problem solution, calculate the angle of attack and stagger angle of each row of blades at different cross-section positions along the radius. At the same time, given the chord length, maximum deflection position, maximum thickness position, two-dimensional blade profile design parameters of the relative maximum thickness, and the bend angle, bend height, sweep angle, and sweep high-end area control parameters of the base stack line, complete the profile design of each row of moving and stationary blades;

[0012] (6) Three-dimensional CFD calculation and analysis: Based on steps (1) and (5), form an integrated three-dimensional CFD calculation model of the transition section - high-pressure compressor, and perform full three-dimensional CFD numerical simulation analysis of the design point and off-design conditions to obtain the performance and internal flow field conditions of the overall transition section - high-pressure compressor at the design point and different rotational speeds, and judge whether it meets the design requirements. If it meets the design requirements, the current aerodynamic design scheme of the transition section - high-pressure compressor is the final design scheme; if it does not meet the design requirements, according to the specific analysis results of the internal flow field, return to the step that needs to be adjusted for design optimization. Through repeated iteration of the above steps, obtain an integrated aerodynamic design scheme of the transition section - high-pressure compressor that finally meets the design index requirements.

[0013] The present invention may further include:

[0014] 1. Considering the influence of the upstream transition section's through-flow structure in steps (2) and (3) means adding the total pressure recovery coefficient of the compressor inlet section in the one-dimensional inverse problem through-flow design, and its value is given according to the final result of the transition section through-flow design, and the influence of the upstream transition section is simulated in the form of the total pressure recovery coefficient of the inlet section.

[0015] 2. For the solution of the inverse S2 problem of the transition section - high - pressure compressor integration with a through - flow aerodynamic layout in step (4), the following method is adopted: First, connect the meridional through - flow profile obtained from the through - flow design of the transition section with the flow passage of the high - pressure compressor body obtained from the one - dimensional inverse problem through - flow design, and perform the fitting and fairing of the transition section - high - pressure compressor integrated flow passage. On this basis, form the meridional through - flow diagram of the transition section - high - pressure compressor integration, divide the calculation stations along the flow direction and the radial direction. Set 5 - 7 calculation stations along the flow direction in the transition section part, and use the streamline curvature method to solve the inverse S2 problem of the whole transition section - high - pressure compressor.

[0016] 3. For the formation of the three - dimensional CFD calculation model of the transition section - high - pressure compressor integration in step (6), the following method is adopted: Connect the flow passage profile of the transition section end wall and the three - dimensional model of the struts with the flow passage profile of the high - pressure compressor end wall and the three - dimensional models of each row of blades according to the real geometric position, and extract the fluid domain of the through - flow part and perform mesh division on the whole transition section - high - pressure compressor, so as to form a three - dimensional CFD calculation model of the transition section - high - pressure compressor integration.

[0017] 4. According to the specific analysis results of the internal flow field in step (6), return to the steps that need to be adjusted for design optimization, including the optimization design of the end wall flow passage profile and the strut profile in the through - flow design of the transition section, the step - by - step distribution optimization adjustment of the key parameters in the one - dimensional inverse problem through - flow design, the radial distribution optimization adjustment of the key parameters in the inverse S2 problem through - flow design, and the three - dimensional design control of the end region and the optimization of the angle - of - attack matching in the blade styling design.

[0018] The advantages of the present invention are as follows:

[0019] 1. The present invention can directly introduce the pressure loss caused by the transition section and the influence of non - uniform intake into the corresponding links in each dimension of the high - pressure compressor aerodynamic design, truly realizing the overall design of the transition section and the through - flow layout of the high - pressure compressor, and effectively improving the aerodynamic performance of the high - pressure compressor.

[0020] 2. The present invention fully considers the influence of the upstream transition section in each dimension and each link of the high - pressure compressor aerodynamic design, can realize the parametric and refined aerodynamic design of the transition section - high - pressure compressor system in different dimensions, effectively improves the design accuracy, and at the same time can save a large amount of design iteration time and shorten the design cycle.

[0021] 3. The present invention is not limited to the high - pressure compressor of gas turbines, and is also applicable to the aerodynamic design process of high - pressure compressors of aero - engines and various industrial axial compressors with transition through - flow structures. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a flow chart of the present invention. Detailed implementation manners

[0023] The present invention will be described in more detail below with reference to the accompanying drawings:

[0024] Combined with Figure 1 , the present invention is realized through the following steps:

[0025] Step 1: Flow path design of the transition section. Aerodynamic design is carried out on the flow path part of the transition section, including the end wall flow path profile, internal struts, etc., to obtain the total pressure recovery coefficient, meridional flow path profile of the transition section, and three-dimensional CFD calculation model.

[0026] Step 2: One-dimensional inverse problem flow path design. According to the performance index requirements and design input conditions of the high-pressure compressor, determine the input parameters of the one-dimensional inverse problem flow path design, including rotational speed, pressure ratio, flow rate, inlet and outlet gas flow conditions, and some geometric conditions. At the same time, the influence of the upstream transition section flow path structure should be taken into account, and the total pressure recovery coefficient of the compressor inlet section is added, and its value is given according to the final result of the transition section flow path design, and the influence of the upstream transition section is simulated in the form of the total pressure recovery coefficient of the inlet section.

[0027] Step 3: One-dimensional characteristic analysis. Based on the meridional flow path and the geometric parameters of the elementary stage at the middle section of the high-pressure compressor obtained from the one-dimensional inverse problem flow path design, and also simulating the pressure loss situation of the upstream transition section in the way of given total pressure recovery coefficient of the inlet section, the HARKIA algorithm based on the stage superposition method is used to calculate the characteristics of the high-pressure compressor under different rotational speeds, and preliminarily predict the overall performance of the high-pressure compressor under the condition including the upstream transition section.

[0028] Step 4: S2 inverse problem flow path design. Based on the meridional flow path profile of the transition section obtained in Step 1 and the meridional flow path profile of the high-pressure compressor obtained in Step 2, solve the S2 inverse problem of the integration of the transition section - high-pressure compressor including the aerodynamic layout of the transition section flow path. The specific method adopted is:

[0029] In order to fully consider the influence of the upstream transition section flow condition on the high-pressure compressor, first connect the meridional flow path profile obtained from the transition section flow path design with the flow path of the high-pressure compressor body obtained from the one-dimensional inverse problem flow path design, and carry out the fitting and fairing of the integrated flow path of the transition section - high-pressure compressor; on this basis, form the integrated meridional flow path diagram of the transition section - high-pressure compressor, and carry out the division of calculation stations along the flow direction and the radial direction. Usually, 5 to 7 calculation stations are set along the flow direction in the transition section part, and the streamline curvature method is used to solve the S2 inverse problem of the whole transition section - high-pressure compressor to obtain the distribution of aerodynamic parameters of the moving and stationary blade rows of each stage of the axial compressor along the radial direction.

[0030] Step 5: Blade profile design. Based on the aerodynamic parameter distribution results of each stage of moving and stationary blade rows along the radius obtained from the solution of the S2 inverse problem, calculate the angle of attack and stagger angle at different cross-section positions along the radius of each row of blades. At the same time, given two-dimensional blade profile design parameters such as chord length, maximum deflection position, maximum thickness position, relative maximum thickness, and end-region control parameters such as bend angle, bend height, sweep angle, and sweep height of the base stacking line, complete the profile design of each row of moving and stationary blades.

[0031] Step 6: Three-dimensional CFD calculation and analysis. On the basis of Steps 1 and 5, form an integrated three-dimensional CFD calculation model of the transition section - high-pressure compressor. The specific method used is as follows:

[0032] Connect the end-wall flow path profile and strut three-dimensional models of the transition section to the end-wall flow path profile of the high-pressure compressor and the three-dimensional models of each row of blades according to the actual geometric positions, extract the fluid domain of the flow passage part of the transition section - high-pressure compressor as a whole and perform mesh division, so as to form an integrated three-dimensional CFD calculation model of the transition section - high-pressure compressor.

[0033] For the integrated three-dimensional CFD calculation model of the transition section - high-pressure compressor, carry out full three-dimensional CFD numerical simulation analysis work for the design point and off-design conditions. Obtain the performance and internal flow field conditions of the transition section - high-pressure compressor as a whole at the design point and different rotational speeds, and judge whether the design requirements are met.

[0034] If the design requirements are met, then it can be considered that the current aerodynamic design scheme of the transition section - high-pressure compressor is the final design scheme;

[0035] If the design requirements are not met, then according to the specific analysis results of the internal flow field, return to the steps that need to be adjusted for design optimization, including the optimization design of the end-wall flow path profile and strut profile in the through-flow design of the transition section, the step-by-step distribution optimization adjustment of key parameters in the one-dimensional inverse problem through-flow design, the along-radius distribution optimization adjustment of key parameters in the S2 inverse problem through-flow design, and the end-region three-dimensional design control and angle of attack matching optimization in the blade profile design, etc.

[0036] Through the repeated iteration of the above-mentioned work in each link, obtain an integrated aerodynamic design scheme of the transition section - high-pressure compressor that finally meets the design index requirements.

[0037] The integrated aerodynamic design method for the through-flow layout of the transition section - high-pressure compressor of a gas turbine proposed by the present invention is universal, not only limited to the high-pressure compressor of a gas turbine, but also applicable to the aerodynamic design process of the high-pressure compressor of an aeroengine and various industrial axial compressors with a transition through-flow structure.

Claims

1. An integrated aerodynamic design method for the flow path layout of a gas turbine transition section - high-pressure compressor, characterized in that: It includes the following steps: (1) Flow path design of the transition section: Conduct aerodynamic design on the flow path part of the transition section, including the end wall flow path profile and the internal struts, to obtain the total pressure recovery coefficient, the meridional flow path profile, and the three-dimensional CFD calculation model of the transition section; (2) One-dimensional inverse problem flow path design: According to the performance index requirements and design input conditions of the high-pressure compressor, determine the input parameters for the one-dimensional inverse problem flow path design, including rotational speed, pressure ratio, flow rate, inlet and outlet gas flow conditions, and geometric conditions, while taking into account the influence of the upstream transition section flow path structure; (3) One-dimensional characteristic analysis: Based on the meridional flow path and the geometric parameters of the elementary stage at the middle section of the high-pressure compressor obtained from the one-dimensional inverse problem flow path design, and taking into account the influence of the upstream transition section flow path structure, conduct one-dimensional forward problem characteristic calculation and analysis of the high-pressure compressor to preliminarily predict the overall performance of the high-pressure compressor under the condition of including the upstream transition section; (4) S2 inverse problem flow path design: Based on the meridional flow path profile of the transition section obtained in step (1) and the meridional flow path profile of the high-pressure compressor obtained in step (2), solve the integrated S2 inverse problem of the transition section - high-pressure compressor including the aerodynamic layout of the transition section flow path to obtain the radial distribution of the aerodynamic parameters of the moving and stationary blade rows of each stage of the axial compressor; (5) Blade profile design: Based on the radial distribution results of the aerodynamic parameters of the moving and stationary blade rows of each stage obtained from the S2 inverse problem solution, calculate the angle of attack and the stagger angle of each row of blades at different cross-sectional positions along the radius, and at the same time specify the chord length, the position of the maximum deflection, the position of the maximum thickness, the two-dimensional blade profile design parameters of the relative maximum thickness, and the bend angle, bend height, sweep angle, and sweep high-end zone control parameters of the base stack line to complete the profile design of each row of moving and stationary blades; (6) Three-dimensional CFD calculation and analysis: Based on steps (1) and (5), form an integrated three-dimensional CFD calculation model of the transition section - high-pressure compressor, and conduct full three-dimensional CFD numerical simulation analysis of the design point and off-design conditions to obtain the performance and internal flow field conditions of the overall transition section - high-pressure compressor at the design point and different rotational speeds, and judge whether it meets the design requirements. If it meets the design requirements, the current aerodynamic design scheme of the transition section - high-pressure compressor is the final design scheme; if it does not meet the design requirements, return to the step that needs to be adjusted for design optimization according to the specific analysis results of the internal flow field. Through repeated iteration of the above steps, an integrated aerodynamic design scheme of the transition section - high-pressure compressor that finally meets the design index requirements is obtained.

2. A gas turbine transition section - high-pressure compressor through-flow layout integrated aerodynamic design method according to claim 1, characterized in that: Taking into account the influence of the upstream transition section flow path structure in steps (2) and (3) means adding the total pressure recovery coefficient of the compressor inlet section in the one-dimensional inverse problem flow path design, and its value is given according to the final result of the transition section flow path design, and the influence of the upstream transition section is simulated in the form of the total pressure recovery coefficient of the inlet section.

3. An integrated aerodynamic design method for the gas turbine transition section - high-pressure compressor flow path layout according to claim 1, characterized in that: In step (4), for the solution of the inverse S2 problem of the integrated transition section - high - pressure compressor with a through - flow aerodynamic layout of the transition section, the following method is adopted: First, the meridian through - flow profile obtained from the through - flow design of the transition section is connected to the flow passage of the high - pressure compressor body obtained from the one - dimensional inverse problem through - flow design, and the fitting and fairing of the integrated flow passage of the transition section - high - pressure compressor are carried out. On this basis, an integrated meridian through - flow diagram of the transition section - high - pressure compressor is formed, and calculation stations are divided along the flow direction and the radial direction. 5 - 7 calculation stations are set along the flow direction in the transition section part, and the streamline curvature method is used to solve the inverse S2 problem of the whole transition section - high - pressure compressor.

4. A gas turbine transition section - high pressure compressor through - flow layout integrated aerodynamic design method according to claim 1, characterized in that: In step (6), for the formation of the integrated three - dimensional CFD calculation model of the transition section - high - pressure compressor, the following method is adopted: The end - wall flow passage profile of the transition section and the three - dimensional model of the struts are connected to the end - wall flow passage profile of the high - pressure compressor and the three - dimensional models of each row of blades according to the actual geometric positions, and the fluid domain of the through - flow part of the whole transition section - high - pressure compressor is extracted and meshed, so as to form the integrated three - dimensional CFD calculation model of the transition section - high - pressure compressor.

5. A gas turbine transition section - high - pressure compressor through - flow layout integrated aerodynamic design method according to claim 1, characterized in that: In step (6), according to the specific analysis results of the internal flow field, return to the steps that need to be adjusted for design optimization, including the optimization design of the end - wall flow passage profile and the strut profile in the through - flow design of the transition section, the step - by - step distribution optimization adjustment of the key parameters in the one - dimensional inverse problem through - flow design, the radial distribution optimization adjustment of the key parameters in the inverse S2 problem through - flow design, and the three - dimensional design control of the end region and the optimization of the angle - of - attack matching in the blade shape design.

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