Axial flow compressor casing with large circumferential spacing and small through holes

Abstract

The invention relates to an axial flow compressor circumferential-direction large-interval small-through-hole cartridge receiver. The axial flow compressor circumferential-direction large-interval small-through-hole cartridge receiver is structurally comprises a cartridge receiver body, a through hole and a rotor; the through hole is formed in the outer surface of the cartridge receiver and directly connected to ambient atmosphere outside the cartridge receiver, and the rotor is arranged inside the cartridge receiver; air at the through hole is driven to flow through opposite motion of the cartridge receiver and the rotor and differential pressure inside and outside the cartridge receiver at the through hole, and airflow in the through hole achieves the periodic excitation function on flowin a compressor by periodically sweeping past a flow channel of the rotor of the compressor. The axial flow compressor circumferential-direction large-interval small-through-hole cartridge receiver has the advantages of capable of inhibiting influencing range and strength of adverse low energy flow next to a blade tip of the axial flow compressor and accordingly remarkably enlarging the steady operating margin of the axial flow compressor, utilizing the unsteady excitation effect so as to have a small influence on the axial flow compressor efficiency, and being simple in structure and convenient to apply and conduct.

Description

Technical field [0001] The invention relates to a casing of an axial flow compressor with large circumferential intervals and small through holes, belonging to the technical field of compressor design. Background technique [0002] With the requirements of modern aeroengines for high thrust-to-weight ratio, low fuel consumption, and small windward area, compressors need to have a higher stage pressure ratio to meet these performance requirements. However, the higher the stage pressure ratio of the compressor, the larger the load, which is prone to unstable conditions such as rotating stall and surge. Unstable working conditions such as rotating stall and surge will bring about a sharp drop in engine performance and serious vibration problems, which will adversely affect the life of the engine. Therefore, it is necessary to develop effective flow control methods to expand the stability margin of the compressor. [0003] Due to the high Mach number of the blade tip flow field, the ...

AI Technical Summary

Problems solved by technology

The former has been researched by many scholars, and a variety of control methods have been designed to effectively increase the stability margin, such as constant air injection at the blade tip. At the same time, the efficiency of the compressor will be reduced, and complex pipeline structures and control valves are required, which increases the weight and cost of the engine

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