A method for aerodynamic design of a high-pressure compressor of a gas turbine taking into account the influence of the throughflow structure of the transition section

Abstract

The present application aims at providing a kind of gas turbine high-pressure compressor aerodynamic design method considering the influence of transition section through-flow structure, the present application fully considers the influence mechanism of transition section through-flow structure on high-pressure compressor aerodynamic performance in each dimension, and introduces key influencing factors into corresponding link of high-pressure compressor aerodynamic design, realizes the parameterization association of key influencing factors of transition section through-flow structure and high-pressure compressor aerodynamic design, can effectively improve the aerodynamic performance of gas turbine high-pressure compressor, also can make high-pressure compressor aerodynamic design more refined, and save a lot of design iteration time, shorten design cycle.The present application is not only limited to gas turbine high-pressure compressor, but also applicable to the aerodynamic design process of aero-engine high-pressure compressor, various industrial axial flow compressors with transition through-flow structure.

Description

TECHNICAL FIELD

[0001] The present application relates to a gas turbine design method, in particular, a compressor design method. BACKGROUND

[0002] Three-rotor gas turbines are widely used in the fields of ship power, ocean engineering and industrial driving due to wide application scenarios and strong stable operation ability under variable working conditions. In the overall layout of the three-rotor gas turbine, the high-pressure compressor has a complex inflow environment due to the influence of the upstream transition section and other real structures, and the aerodynamic design is extremely difficult, which has become a difficult problem in gas turbine design. The transition section is a connecting component between the low-pressure and high-pressure compressors in the entire compression system, and the internal flow is affected by structural constraints, having typical pipe flow resistance characteristics. The non-uniform inlet caused by the transition section flow structure and the pressure loss will directly affect the performance of the high-pressure compressor. How to design a high-pressure compressor with excellent performance under the above influences is directly related to the performance level of the entire gas turbine compression system, and is a core technical link in the aerodynamic design system of the compressor. It is urgent to explore new design concepts and methods to solve the performance degradation problem of the high-pressure compressor caused by the transition section flow structure, so as to improve the performance indicators of the gas turbine compressor component. SUMMARY

[0003] The present application relates to a gas turbine design method, in particular, a compressor design method.

[0004] The purpose of the present application is achieved in that:

[0005] The present application relates to a gas turbine design method, in particular, a compressor design method.

[0006] (1) One-dimensional flow design: according to the performance index requirements and design conditions of the high-pressure compressor, the input parameters of the high-pressure compressor design point inlet total temperature, total pressure, rotational speed, pressure ratio, flow rate, and inlet and outlet flow angles are determined, and the influence of the transition section flow structure on the one-dimensional flow of the high-pressure compressor is simulated by correcting the inlet resistance, and on the basis of considering the influence of the transition section flow structure, the key aerodynamic parameters of the high-pressure compressor including the step-by-step distribution rules of the flow coefficient, the load coefficient and the reaction degree are given, and the one-dimensional inverse problem design is carried out;

[0007] (2) S1 / S2 flow surface through-flow design: on the basis of the one-dimensional through-flow design result, a transition section through-flow structure is introduced to form a transition section-high pressure compressor overall quasi-three-dimensional through-flow layout, and calculation stations are divided, through the radial twist law design of the high pressure compressor blades, the distribution of key aerodynamic parameters at different blade height section positions is given, and the streamline curvature method is used for solving;

[0008] (3) blade modeling design: on the basis of the S1 / S2 flow surface through-flow design result, two-dimensional blade profile design of different blade height section positions of the high pressure compressor blades and base stacking law design of the blades are carried out, and three-dimensional modeling of the high pressure compressor blades is obtained;

[0009] (4) three-dimensional CFD analysis: on the basis of the high pressure compressor flow passage and blade geometric model obtained in the above steps, a transition section three-dimensional fluid domain model is introduced, and three-dimensional CFD numerical calculation and analysis of the high pressure compressor design point and variable conditions are carried out according to the actual layout state of the transition section and the high pressure compressor;

[0010] According to the three-dimensional CFD calculation result, it is judged whether the high pressure compressor aerodynamic design scheme meets the design requirements, if not, the corresponding step is returned for iteration, and finally the high pressure compressor aerodynamic design scheme meeting the performance index requirements is obtained.

[0011] The application can also include:

[0012] 1. The influence of the transition section through-flow structure on the one-dimensional flow of the high pressure compressor is simulated by correcting the inlet resistance in step (1), and the following method is adopted: by giving the total pressure recovery coefficient of the transition section under the condition of the high pressure compressor design point, the inlet total pressure loss in the one-dimensional design of the high pressure compressor is corrected.

[0013] 2. The transition section through-flow structure is introduced in step (2), and the following method is adopted: when the calculation station of the S1 / S2 flow surface through-flow layout of the high pressure compressor is divided, the transition section end wall flow passage profile and the thickness distribution of the branch plate are added according to the actual position relationship between the transition section and the high pressure compressor.

[0014] The advantages of the application are:

[0015] 1. The application fully considers the influence mechanism of the transition section through-flow structure on the aerodynamic performance of the high pressure compressor in each dimension, and introduces the key influencing factors into the corresponding link of the high pressure compressor aerodynamic design, effectively solves the performance degradation problem of the high pressure compressor caused by the transition section through-flow structure, and improves the aerodynamic performance of the high pressure compressor.

[0016] 2. This invention realizes the parametric correlation between the key influencing factors of the transition section flow structure and the aerodynamic design of the high-pressure compressor, which effectively improves the precision of the aerodynamic design of the high-pressure compressor, and can also save a lot of design iteration time and shorten the design cycle.

[0017] 3. This invention is not limited to high-pressure compressors for gas turbines, but is also applicable to the aerodynamic design process of high-pressure compressors for aero engines and various industrial axial compressors with transition flow structures. Attached Figure Description

[0018] Figure 1 This is a flowchart of the present invention. Detailed Implementation

[0019] The invention will now be described in more detail with reference to the accompanying drawings:

[0020] Combination Figure 1 The present invention is achieved through the following steps:

[0021] Step 1: One-dimensional flow path design. Based on the performance requirements and design conditions of the high-pressure compressor, determine the input parameters such as total inlet temperature, total pressure, speed, pressure ratio, flow rate, and inlet / outlet airflow angle at the design point of the high-pressure compressor. Then, simulate the influence of the transition section flow path structure on the one-dimensional flow of the high-pressure compressor by correcting the inlet resistance. Specifically, the following method is used: by giving the total pressure recovery coefficient of the transition section under the design point conditions of the high-pressure compressor, correct the inlet total pressure loss in the one-dimensional design of the high-pressure compressor.

[0022] Considering the influence of the flow path structure in the transition section, and given the stepwise distribution law of key aerodynamic parameters such as flow coefficient, load coefficient and reaction degree of each stage of the high-pressure compressor, a one-dimensional inverse problem design is carried out.

[0023] Step 2: S1 / S2 flow surface design. Based on the one-dimensional flow design results, a transition section flow structure is introduced, specifically as follows: When dividing the flow layout of the S1 / S2 flow surface of the high-pressure compressor into calculation stations, the flow channel profile and support plate thickness distribution of the transition section end wall are added according to the actual positional relationship between the transition section and the high-pressure compressor.

[0024] Based on this, a quasi-three-dimensional flow layout of the transition section-high pressure compressor is formed, and calculation stations are divided. By designing the radial torsion law of each stage of the high pressure compressor blades, the distribution of key aerodynamic parameters at different blade height sections is given, and the streamline curvature method is used for solution.

[0025] Step 3: Blade Design. Based on the flow path design results of S1 / S2 flow surfaces, two-dimensional airfoil design is carried out for different blade height sections of each row of blades in the high-pressure compressor, as well as the base stacking rule design of each row of blades, to obtain the three-dimensional shape of each row of blades in the high-pressure compressor;

[0026] Step four: three-dimensional CFD analysis. Based on the high-pressure compressor flow passage and blade geometry model obtained in the above steps, a three-dimensional fluid domain model of the transition section is introduced, and three-dimensional CFD numerical calculation and analysis of the high-pressure compressor design point and variable working conditions are carried out according to the actual layout state of the transition section and the high-pressure compressor;

[0027] According to the three-dimensional CFD calculation results, it is judged whether the high-pressure compressor aerodynamic design scheme meets the design requirements, if not, return to the corresponding step for iteration, and finally obtain a high-pressure compressor aerodynamic design scheme that meets the performance index requirements.

[0028] The gas turbine high-pressure compressor aerodynamic design method considering the influence of the transition section flow structure has universality, and is not limited to the gas turbine high-pressure compressor, but also applicable to the aerodynamic design process of the high-pressure compressor of an aero-engine, various industrial axial flow compressors with transition flow structure.

Claims

1. An aerodynamic design method for a gas turbine high-pressure compressor that considers the influence of the transition section flow path structure, characterized in that: Includes the following steps: (1) One-dimensional flow design: Based on the performance requirements and design conditions of the high-pressure compressor, determine the input parameters of the high-pressure compressor design point, including total inlet temperature, total pressure, speed, pressure ratio, flow rate, and inlet / outlet airflow angle. Simulate the influence of the transition section flow structure on the one-dimensional flow of the high-pressure compressor by correcting the inlet resistance. Considering the influence of the transition section flow structure, give the key aerodynamic parameters of the high-pressure compressor, including the stepwise distribution law of each stage flow coefficient, load coefficient, and reaction degree, and carry out one-dimensional inverse problem design. (2) S1 / S2 flow surface design: Based on the one-dimensional flow design results, a transition section flow structure is introduced to form a quasi-three-dimensional flow layout of the transition section-high pressure compressor. The calculation station is divided, and the distribution of key aerodynamic parameters at different blade height sections is given by the radial torsion law design of each stage of the high pressure compressor. The streamline curvature method is used to solve the problem. (3) Blade design: Based on the flow design results of S1 / S2 flow surface, two-dimensional blade profile design of different blade height sections of each row of blades of the high-pressure compressor and the base stacking law design of each row of blades are carried out to obtain the three-dimensional shape of each row of blades of the high-pressure compressor. (4) Three-dimensional CFD analysis: Based on the geometric model of the high-pressure compressor flow channel and blades obtained in the above steps, a three-dimensional fluid domain model of the transition section is introduced. According to the actual layout of the transition section and the high-pressure compressor, a three-dimensional CFD numerical calculation analysis of the high-pressure compressor design point and variable operating conditions is carried out. Based on the three-dimensional CFD calculation results, it is determined whether the aerodynamic design scheme of the high-pressure compressor meets the design requirements. If it does not meet the requirements, the corresponding steps are returned for iteration, and finally a high-pressure compressor aerodynamic design scheme that meets the performance index requirements is obtained. The effect of the transition section flow structure on the one-dimensional flow of the high-pressure compressor by modifying the intake resistance described in step (1) is as follows: by giving the total pressure recovery coefficient of the transition section under the design point condition of the high-pressure compressor, the intake total pressure loss in the one-dimensional design of the high-pressure compressor is corrected.

2. The aerodynamic design method for a gas turbine high-pressure compressor considering the influence of the transition section flow structure according to claim 1, characterized in that: The transition section flow structure introduced in step (2) is implemented in the following way: when dividing the flow layout of the high-pressure compressor S1 / S2 flow surface into calculation stations, the flow channel profile and support plate thickness distribution of the transition section end wall are added according to the actual positional relationship between the transition section and the high-pressure compressor.

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