A Diagnosis Method of S2 Flow Field Based on Measurement Parameters Between Stages of Axial Flow Compressor

Abstract

A S2 flow field diagnosis method based on inter-stage measurement parameters of an axial flow compressor, specifically: 1. Establishing a corresponding S2 flow field calculation streamline curvature control equation according to the inter-stage measurement parameters of a multi-stage axial flow compressor; 2. According to the possibility that the total temperature rise of the multi-stage compressor may be high, the variable ratio thermal working medium is used to account for the influence of the inter-stage measurement parameters; 3. According to the thermodynamic relationship and the stator model, the stator lagging angle and entropy distribution parameters in the flow field are obtained; 4. 1. Carry out flow field calculation to obtain the inversion result of flow field of axial flow compressor S2 based on interstage measurement parameters; 5. Analyze and diagnose according to calculation results of flow field parameters and performance parameters obtained by inversion. This method adopts a variable ratio thermal working medium, and the accuracy is higher when dealing with a large number of compressor stages and a large temperature rise. It breaks the assumption that the static pressure at different heights in the multi-stage compressor test is equal to the wall static pressure, the flow field result automatically satisfies the radial balance equation, the S2 flow field diagnosis accuracy is higher, and the compressor design cycle is reduced.

Description

technical field [0001] The invention relates to an S2 flow field diagnosis method based on interstage measurement parameters of an axial flow compressor, which relates to aerodynamics and aerodynamic gas turbine engine compressor test flow field diagnosis, and belongs to the field of aerodynamic design analysis of aerogas turbine engine compressors . Background technique [0002] The aero engine is the power source of the aircraft, so the improvement of the performance of the aircraft requires the engine of the aircraft to be strong enough. Foreign advanced engines can now reach a thrust-to-weight ratio of 10, and the temperature before the turbine is 2000K. The use of high-thrust-to-weight ratio and high-thrust engines has greatly improved the performance of the aircraft, so the requirements for engine performance are also rising. Our country is striving to shorten the gap with advanced foreign countries. [0003] The traditional design process of the engine, no matter t...

AI Technical Summary

Problems solved by technology

However, the static-rotary interface acts as a mixing surface, which homogenizes the non-uniform flow at the outlet of the front blades, artificially adds mixing, and generates additional entropy increase

At the same time, the leakage flow, disk cavity flow, geometric shape and other parameters in the multi-stage compressor may have large differences between CFD and the real physical prototype

Then the error generated by this processing method may not be very large when the number of stages is small, but once the number of stages increases, the calculation results of the subsequent stages will deviate, and the matching of multi-stage compressors will be destroyed. The more stages, the more cumulative error

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