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A kind of aerodynamic design method of subsonic adsorption axial flow compressor

A technology of axial flow compressor and aerodynamic design, applied in mechanical equipment, machines/engines, non-variable pumps, etc., can solve problems such as increased blade rotation angle, difficult suction pipeline layout, separated flow, etc., to ensure high efficiency Effect of flow, avoidance blade strength and suction structure design

Active Publication Date: 2015-08-05
HARBIN INST OF TECH
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  • Abstract
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AI Technical Summary

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.

Method used

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  • A kind of aerodynamic design method of subsonic adsorption axial flow compressor
  • A kind of aerodynamic design method of subsonic adsorption axial flow compressor
  • A kind of aerodynamic design method of subsonic adsorption axial flow compressor

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Embodiment Construction

[0020] For the axial compressor stage whose inlet relative velocity is subsonic speed, in conventional design, the axial velocity of the rotor blade inlet, rotor blade outlet and stator blade outlet are usually equal or not changed much. Under the premise that the inlet velocity triangle of the rotor remains unchanged, as the stage load increases to a certain level, the boundary layer flow separation will occur inside the rotor. At this time, by increasing the contraction amplitude of the meridian channel, the axial velocity of the rotor blade outlet is increased to reduce the reverse pressure gradient of the gas in the rotor blade, avoiding the separation flow of the surface layer in the rotor blade and improving the gas flow efficiency in the rotor blade. From a one-dimensional point of view, the method for determining the value of the increase in the axial velocity of the outlet is as follows:

[0021] D = 1 - w 2 w 1 + Δ w u 2 τ w ...

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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 a pneumatic design method of a subsonic axial flow compressor, and belongs to the technical field of axial flow compressors. Background technique [0002] The basic components of an axial compressor are composed of a rotor and a stator. For the compressor, its single-stage pressure ratio increase can effectively reduce the size and weight of the engine, and increase the thrust-to-weight ratio of aero engines. Generally, there are two main methods for increasing the compressor stage pressure ratio, increasing the circumferential speed of the rotor or increasing the turning angle of the rotor blades to obtain a large torsion speed gain. When the peripheral speed remains the same, under the premise of ensuring the efficiency of the compressor stage, further increasing the torsion speed of the rotor is the only way to increase the pressure ratio of the compressor stage. [0003] In the aerodynamic design of the traditional subsonic axia...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/38
Inventor 王松涛胡应交
Owner HARBIN INST OF TECH
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