Porous-based ultrasonic-speed adsorption type compressor blade

Abstract

The invention discloses a porous-based ultrasonic-speed adsorption type compressor blade. A suction chamber which is through in a blade extending direction is arranged between a suction surface and a pressure surface of the ultrasonic-speed adsorption type compressor blade. A plurality of suction holes which communicate with the suction chamber are distributed in the suction surface of the ultrasonic-speed adsorption type compressor blade. Each suction hole is a circular hole or a rectangular hole with the same cross section area. Blade spacing on a gate plate, of the ultrasonic-speed adsorption type compressor blade is 30.55 mm, and a mounting angle is 47 degrees; during numerical simulation under a designed working condition, an inlet gas flow angle is 61 degrees, and an inlet Mach number is 1.5. The porous-based ultrasonic-speed adsorption type compressor blade avoids reflection, on the suction force, of shock waves, reduces loss of passing shock waves; and meanwhile, shock wave impact points are in the suction holes, so that mutual interference between the shock waves and the attaching layer of the suction force are effectively weakened, an attaching layer separation phenomenon after shock waves is effectively inhibited, too great Mach after before shock waves due to continuous acceleration, on the suction force, of the gas flow is avoided, and Mach number before waves and shock wave loss are reduced.

Description

technical field [0001] The invention relates to the field of compressors, in particular to a supersonic adsorption compressor blade based on porous control shock wave / wall interference. Background technique [0002] The development of modern aero-vehicle technology requires to further increase the thrust-to-weight ratio of aero-engines, that is, fewer stages and higher stage loads. Inside the compressor, higher stage loads are usually accompanied by unavoidable flow separation, and the flow loss and blockage caused by strong flow separation limit the increase of compressor stage loads, especially in trans- and supersonic compressors. Waves complicate the flow inside the compressor. Therefore, it is necessary to control the flow separation inside the compressor. [0003] Since Kerrebrock of MIT first proposed the adsorption compressor in 1997, the adsorption compressor has gradually become an important research direction to improve the performance of the compressor. Schule...

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Problems solved by technology

[0006] Conventional trans / supersonic adsorption compressor blades / cascades all use boundary layer suction to pump out low-energy fluid after the shock wave to improve the aerodynamic performance of the compressor, but there is still flow separation on the suction surface of the blade after suction

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