Aerodynamic design method of subsonic adsorption type axial compressor

Abstract

The invention belongs to the technical field of axial compressors, and relates to an aerodynamic design method of a subsonic adsorption type axial compressor, in order to solve the problems of increasing of blade rotating angles of a subsonic axial compressor and boundary layer separated in a moving blade during stage load increasing as well as the problems of suction pipeline layout difficulty, blade strength reduction and the like caused by boundary layer suction in the moving blade. On the premise of unchanging an inlet velocity triangle, with design stage load coefficient increasing gradually and exceeding a conventional design value, outlet axial velocity of the moving blade is increased greatly so as to reduce diffusion factors in the moving blade, so that efficient flow of the moving blade is guaranteed; and boundary layer suction is utilized for achieving internal flow of a fixed blade. As boundary layer suction is performed in the moving blade as well as the fixed blade, problems of poor blade strength of a rotatable part and difficulty in suction structure design are solved effectively; and as compared with a tandem cascade technique, the aerodynamic design method has the advantages that blades can be decreased, and accordingly size and weight of an engine are reduced. The method can be applied to aerodynamic design of aero-engines with high thrust-weight ratio.

Description

technical field [0001] The invention relates to an aerodynamic design method of a subsonic axial flow compressor, which belongs to the technical field of axial flow compressors. Background technique [0002] The basic components of an axial flow compressor are composed of a rotor and a stator. For the compressor, its single-stage pressure ratio is increased, which can effectively reduce the size and weight of the engine and increase the thrust-to-weight ratio of the aeroengine. Generally, there are two main methods to increase the pressure ratio of the compressor stage, increasing the circumferential speed of the rotor or increasing the bending angle of the rotor blades to obtain a large torsional speed gain. When the peripheral speed remains constant, on the premise of ensuring the efficiency of the compressor stage, further increasing the twisting speed of the rotor is the only way to increase the pressure ratio of the compressor stage. [0003] In the aerodynamic design...

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Problems solved by technology

[0005] The purpose of the present invention is to solve the problem of boundary layer separation flow in the moving blade when the blade rotation angle increases and the stage load increases, and at the same time avoid the problem caused by the boundary layer suction in the moving blade. Such as difficulty in the layout of the suction pipeline, the decrease of blade strength, etc.

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