Stationary blade distortion-resistant axial flow compressor and axial flow compressor stationary blade distortion-resistant method

Abstract

The invention provides a stationary blade distortion-resistant axial flow compressor and an axial flow compressor stationary blade distortion-resistant method.The cascade consistency of a stationary blade distortion area of the compressor is greater than that of a non-distortion area, and the cascade consistency of the non-distortion area is the original consistency. In the design, stationary blades of a stationary blade axial flow compressor are non-uniformly distributed, and the cascade consistency is increased in a stationary blade area influenced by air inlet distortion fluid without changing the blade consistency of original stationary blades in other areas, so that the aim of regulating and controlling a non-uniform flow field by using the non-uniformly arranged stationary blades is achieved, the performance (flow, pressure ratio, efficiency and the like) of the air compressor is ensured not to change under the condition of a uniform incoming flow, and the aerodynamic performance and the stability margin under the condition of air inlet distortion are improved at the same time.

Description

technical field [0001] The invention belongs to the production field of axial-flow compressors, and in particular relates to an anti-distortion axial-flow compressor of a stationary vane and an anti-distortion method for a stationary vane of the axial-flow compressor. Background technique [0002] The traditional axial flow compressor design method is to assume that the compressor inlet is a uniform intake, that is, the aerodynamic parameters of the incoming flow and the structural load are uniform. Therefore, the vanes in the axial flow compressor are uniformly arranged, and the corresponding consistency for a certain value. The emerging boundary layer ingestion propulsion system (boundary layer ingestion, BLI) has great potential in reducing aircraft drag and engine power requirements. The BLI propulsion system often uses a buried S-shaped inlet, and the inlet and the engine are installed at the rear of the wing or fuselage to absorb the thicker boundary layer as much as ...

AI Technical Summary

Problems solved by technology

This layout enables the engine to continuously inhale a large amount of boundary layer (low-energy fluid) under normal operating conditions. Under the same reverse pressure gradient, the airflow is more likely to separate in the intake port, resulting in continuous generation of Intake distortion, this distorted flow field is transmitted by the fan and then enters the core engine, further affecting the work of the compressor

[0003] Intake distortion changes the original design conditions of the compressor, destroys the axisymmetric flow of the airflow, and causes an increase in the load on the local stator blades. In light cases, the stability margin of the compressor decreases and performance deteriorates, and in severe cases, it causes compressor stall and panting. Vibration seriously affects the normal operation of the entire engine

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