A Judgment Method of Compressor Stability Boundary Considering the Influence of Inlet Total Pressure Distortion

Abstract

The invention discloses a method for judging the stability boundary of a compressor considering the influence of the distortion of the total intake pressure, comprising the following steps: obtaining the maximum steady-state aerodynamic load H of each stage of the compressor max , the dimensionless diffusion length of the rotor blades at each stage obtains the maximum steady-state aerodynamic load H of each stage of the compressor ef (θ); Calculate the critical distortion angle of the compressor under the condition of intake distortion, if the effective steady-state aerodynamic load is less than H max , the compressor is still in a stable working state, if it is greater than H max , it is considered that the compressor enters an unstable state, and the previous operating point in a stable working state is considered to be the stable boundary point at the current speed; repeat the above steps to finally obtain stable boundary points at different speeds, and connect these stable boundary points line, that is, the stable boundary of the compressor is obtained. The invention can quickly and accurately predict the stability boundary of the compressor under the condition of total intake pressure distortion, can be used in the early stage of compressor design, can reduce the development cycle of the compressor, and reduce the development cost and risk.

Description

technical field [0001] The invention relates to a method for analyzing the internal aerodynamic flow state of an aeroengine compressor, which belongs to the technical field of aviation systems. Background technique [0002] The compressor is the core component of an aero-engine. During use, it is in a stable working state under normal circumstances. However, under special circumstances such as aircraft maneuvering, high angle of attack takeoff, or missile launch, the operating point of the compressor will cross the stability boundary. , the occurrence of aerodynamic instability such as rotating stall and surge will lead to a sharp drop in the thrust of the aeroengine, and will also cause great damage to the structure of the engine. Therefore, in the design process of the compressor, it is necessary to analyze the aerodynamic stability of the compressor. First, it is necessary to accurately know the position of the stability boundary of the compressor under the uniform intake...

AI Technical Summary

Problems solved by technology

Koch's method is suitable for the judgment of the stability boundary of the compressor under uniform intake conditions, but not for the distortion of the total intake pressure. At the same time, the compressor associated with this method was designed before the 1970s, and its performance is poor, so it is not applicable modern advanced compressor

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