A method for inverse design of gas turbine intermediate casing-high pressure compressor through-flow aerodynamic layout integration S2 problem

Abstract

The application aims to provide a gas turbine intermediate casing-high pressure compressor through-flow aerodynamic layout integrated S2 inverse problem design method, which directly introduces the meridian through-flow of the intermediate casing into the S2 inverse problem through-flow design of the high pressure compressor, realizes the overall design concept of the intermediate casing-high pressure compressor system from the core link of the high pressure compressor aerodynamic design, effectively improves the aerodynamic performance of the high pressure compressor, and can realize the parameterization and refinement of the aerodynamic design of the whole intermediate casing-high pressure compressor system, improve the design precision, shorten the design cycle, and is very suitable for engineering design application. The application is not only limited to the high pressure compressor of the gas turbine, but also applicable to the aerodynamic design process of the high pressure compressor of the aero-engine and various industrial axial flow compressors with the intermediate casing.

Description

TECHNICAL FIELD

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

[0002] Affected by the layout position of the gas turbine, the high-pressure compressor in the gas turbine faces the complex inflow environment caused by the upstream intermediate casing, such as pressure loss and non-uniform inlet, which makes the aerodynamic design extremely difficult. Looking at the development history of the world's gas turbine giants, the aerodynamic design of the high-pressure compressor occupies a very important position, and its technical level directly determines the overall performance index of the gas turbine. Up to now, the advanced and efficient aerodynamic design technology of the high-pressure compressor has become one of the main research directions in the field of modern turbomachinery design.

[0003] How to fully consider the influence of the intermediate casing in the aerodynamic design of the high-pressure compressor and solve the performance degradation problem of the high-pressure compressor caused by the through-flow layout of the intermediate casing is directly related to the performance level of the entire intermediate casing-high-pressure compressor system. The key lies in how to introduce the inflow influence caused by the upstream intermediate casing into the aerodynamic design of the high-pressure compressor. At present, the core part of the compressor aerodynamic design system is still the turbomachinery quasi-three-dimensional aerodynamic design system established based on S1 and S2 flow surface theory. In order to solve the above problems, in-depth exploration and research work must be carried out for the core link in the aerodynamic design system of the high-pressure compressor, and the overall design idea of the intermediate casing-high-pressure compressor system is formed, and on this basis, the key design technology is broken through. SUMMARY

[0004] The purpose of the present application is to provide a gas turbine intermediate casing-high-pressure compressor through-flow aerodynamic layout integrated S2 inverse problem design method which can solve the performance degradation problem of the high-pressure compressor caused by the through-flow layout of the intermediate casing of the gas turbine.

[0005] The purpose of the present application is achieved in the following way:

[0006] The gas turbine intermediate casing-high-pressure compressor through-flow aerodynamic layout integrated S2 inverse problem design method of the present application is characterized by comprising the following steps:

[0007] (1) Meridional through-flow calculation station division: according to the one-dimensional inverse problem through-flow design and the intermediate casing through-flow design results, the meridional through-flow calculation station division of the intermediate casing-high-pressure compressor is carried out;

[0008] (2) Radial twist law design: based on the aerodynamic parameters of the high-pressure compressor at the average radius of each stage obtained by the one-dimensional inverse problem through-flow design, the radial distribution law of the absolute tangential velocity at the inlet of each moving blade is calculated;

[0009] (3) S2 flow surface streamline curvature method solution: according to the design results of the radial twist law of each stage, while the radial distribution law of the pressure ratio and loss coefficient of each stage is given, the inverse problem of the typical S2 flow surface is solved by using the streamline curvature method, the radial aerodynamic parameter distribution of the high-pressure compressor blade row of each stage considering the influence of the upstream intermediate casing is obtained, and thus the integrated S2 aerodynamic design scheme of the intermediate casing-high-pressure compressor is obtained.

[0010] The application can also include:

[0011] 1. The intermediate casing-high-pressure compressor integrated meridional throughflow calculation station division in step (1) is divided in the following manner: first, the flow passage profile of the inner and outer end walls of the intermediate casing is described by using a fourth-order Bezier curve, and is connected with the meridional throughflow profile of the high-pressure compressor obtained by one-dimensional inverse problem throughflow design to perform fitting and smoothing of the meridional flow passage, thereby forming an integrated meridional throughflow diagram of the intermediate casing-high-pressure compressor; the meridional throughflow is divided into calculation stations along the flow direction and the radial direction, wherein 5 calculation stations are arranged along the flow direction according to the Bezier curve control point position in the intermediate casing throughflow part, and the integrated meridional throughflow calculation station division of the intermediate casing-high-pressure compressor is completed.

[0012] The advantages of the application are:

[0013] 1. The meridional throughflow of the intermediate casing is directly introduced into the S2 inverse problem throughflow design of the high-pressure compressor, the overall design concept of the intermediate casing-high-pressure compressor system is realized from the core part of the high-pressure compressor aerodynamic design, and the aerodynamic performance of the high-pressure compressor is effectively improved.

[0014] 2. The application realizes parameterization and refinement of the aerodynamic layout integrated design of the intermediate casing-high-pressure compressor throughflow, effectively improves the aerodynamic design accuracy of the high-pressure compressor, shortens the design cycle, and is very suitable for engineering design application.

[0015] 3. The application is 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 aero-engine and various industrial axial compressors with an intermediate casing. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 The flowchart of the application;

[0017] Figure 2 The intermediate casing-high-pressure compressor integrated meridional throughflow calculation station division schematic diagram. DETAILED DESCRIPTION

[0018] The application will be described in more detail below with examples combined with the drawings:

[0019] Combined with the drawings, Figures 1-2The application is realized by the following steps:

[0020] Step one: meridional flow calculation station division. According to the one-dimensional inverse problem flow design and the intermediate casing flow design result, the intermediate casing-high pressure compressor integrated meridional flow calculation station division is carried out. The specific method is as follows:

[0021] Firstly, the flow passage profile of the inner and outer end walls of the intermediate casing is described by using the fourth order Bezier curve, and is connected with the high pressure compressor meridional flow profile obtained by the one-dimensional inverse problem flow design to carry out the fitting and smoothing of the meridional flow passage, and form the intermediate casing-high pressure compressor integrated meridional flow diagram, as shown in Figure 2 .

[0022] On this basis, the calculation station division along the flow direction and the radial direction of the meridional flow is carried out, wherein 5 calculation stations are arranged along the flow direction according to the Bezier curve control point position in the intermediate casing flow part, and the intermediate casing-high pressure compressor integrated meridional flow calculation station division is completed.

[0023] Step two: radial twist law design. The radial distribution law of the absolute tangential velocity at the inlet of the blades of each stage of the high pressure compressor is calculated based on the aerodynamic parameters at the average radius of each stage obtained by the one-dimensional inverse problem flow design. The equal circulation, equal reaction or intermediate flow type can be used to calculate the absolute tangential velocity at the inlet of the blades.

[0024] Step three: S2 flow surface streamline curvature method solving. According to the radial twist law design result of each stage, and the radial distribution law of the pressure ratio and the loss coefficient of each stage, the inverse problem of the typical S2 flow surface is solved by using the streamline curvature method, the radial aerodynamic parameter distribution of the blade rows of each stage of the high pressure compressor considering the influence of the upstream intermediate casing is obtained, and thus the integrated S2 aerodynamic design scheme of the intermediate casing-high pressure compressor is obtained.

[0025] The integrated S2 inverse problem design method of the intermediate casing-high pressure compressor flow aerodynamic layout of the gas turbine provided by the application has universality, and is not limited to the high pressure compressor of the gas turbine, and is also applicable to the aerodynamic design process of the high pressure compressor of the aero-engine and various industrial axial flow compressors with intermediate casings.

Claims

1. A design method for an integrated S2 inverse problem of the flow path aerodynamic layout of a gas turbine intermediate casing-high-pressure compressor, characterized by: It comprises the following steps: (1) meridional flow calculation station division: according to the one-dimensional inverse problem flow design and the intermediate casing flow design results, the intermediate casing-high pressure compressor integrated meridional flow calculation station division is carried out; (2) radial twist law design: based on the aerodynamic parameters at the average radius of each stage of the high pressure compressor obtained by one-dimensional inverse problem flow design, the radial distribution law of the absolute tangential velocity at the inlet of each stage of the moving blade is calculated; (3) S2 flow surface streamline curvature method solution: according to the radial twist law design results of each stage, while giving the radial distribution law of the pressure ratio and loss coefficient of each stage, the inverse problem of the typical S2 flow surface is solved by using the streamline curvature method, the radial aerodynamic parameter distribution of each stage of the moving and stationary blade row of the high pressure compressor considering the influence of the upstream intermediate casing is obtained, and thus the integrated S2 aerodynamic design scheme of the intermediate casing-high pressure compressor is obtained; The calculation station division of the intermediate casing-high pressure compressor integration meridional flow in step (1) is carried out in the following manner: first, the flow passage profile of the inner and outer end walls of the intermediate casing is described by using a fourth-order Bezier curve, and it is connected with the meridional flow profile of the high pressure compressor obtained by one-dimensional inverse problem flow design to carry out the fitting and smoothing of the meridional flow passage, and the integrated meridional flow passage diagram of the intermediate casing-high pressure compressor is formed; the calculation station division along the flow direction and the radial direction of the meridional flow is carried out, wherein 5 calculation stations are arranged along the flow direction according to the Bezier curve control point position in the intermediate casing flow passage part, and the calculation station division of the intermediate casing-high pressure compressor integrated meridional flow is completed.

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