A compressor suction type discrete inclined seam casing processing control device and method

Abstract

The invention discloses a suction type discrete and inclined seam casing treatment control device and method of a compressor. A plurality of discrete and inclined seams are formed in the wall surfaceof a compressor treatment casing in the circumferential direction, and the seams are inclined to the rotor rotation direction by a certain angle; then a certain number of suction holes are formed in the tops of the seams, and a back cavity is additionally arranged on the upper portion of the suction holes; by adjusting the angle of the suction holes, the air pumping volume and the air pumping position, flow vortex structures in the discrete and inclined seams and axial flow amount of the air flow of inflow and outflow of the discrete and inclined seams can be changed, and then the momentum ofa tip leakage flow and a mainstream can be changed; and the position of the interface of the tip leakage flow and the mainstream and flow loss caused by interaction between the seams and the tip flowfield can be adjusted. Compared with traditional discrete and inclined seam casing treatment, suction type discrete and inclined seam casing treatment can achieve the goal of reducing the efficiency loss while increasing the stable working range of the compressor.

Description

technical field [0001] The invention relates to a treatment control device and a flow control method for an air-breathing discrete inclined seam casing of a compressor, which are used to improve the stable working range of a compressor, and belong to the field of impeller machinery. Background technique [0002] The function of the compressor is to process the air flow passing through it with the lowest possible flow resistance loss to increase its pressure. The compressor is one of the core components of gas turbines and aero-engines. With the development of gas turbines and aero-engines in the direction of high compactness, low fuel consumption and high stability, the compressor load and efficiency must be increased while ensuring that the compressor has a high Stall margin is a goal that researchers are constantly pursuing. When the flow through the compressor decreases to a certain extent at a certain speed, unstable flow phenomena such as rotating stall and surge will ...

AI Technical Summary

Problems solved by technology

The interaction between the strong shock wave and the leakage vortex exists in the blade tip area of ​​the high-load compressor, which is easy to cause a large flow blockage

The flow blockage in the blade tip area of ​​the compressor is an important cause of the rotating stall, which restricts the stable working range of the compressor

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