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Supersonic porous adsorption type compressor blade with corrugated grooves in suction surface

A porous adsorption and suction surface technology, applied in the field of compressors, can solve the problems of poor suction control of the boundary layer, high shock wave intensity, and severe separation of the boundary layer induced by shock waves

Active Publication Date: 2021-12-28
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] In order to overcome the deficiencies in the prior art of high shock wave intensity, severe shock wave-induced boundary layer separation, and poor boundary layer suction control effect, the present invention proposes a supersonic porous adsorption with corrugated grooves on the suction surface. compressor blade

Method used

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  • Supersonic porous adsorption type compressor blade with corrugated grooves in suction surface
  • Supersonic porous adsorption type compressor blade with corrugated grooves in suction surface
  • Supersonic porous adsorption type compressor blade with corrugated grooves in suction surface

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Embodiment Construction

[0036] This embodiment is a supersonic porous adsorption compressor blade with corrugated grooves on the suction surface; the blade is obtained by improving a porous-based supersonic adsorption compressor blade disclosed in CN113153815A.

[0037] The blade shape of the supersonic porous adsorption compressor blade 1 adopts the linear blade shape of the inlet section or the pre-compression blade shape. When a straight airfoil at the inlet section is used, the suction surface of the straight airfoil at the inlet section is a straight line, the straight line is tangent to the arc of the rear section of the suction surface, and the airflow turning angle of the straight section of the blade inlet is 0°. When the pre-compression airfoil is used, the suction surface of the pre-compression airfoil is a smooth curve with a negative angle of the inlet section, and the airfoil line of the front section of the suction is tangent to the airfoil line of the rear section. The maximum thicknes...

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Abstract

According to a supersonic porous adsorption type compressor blade with corrugated grooves in the suction surface, the corrugated grooves are distributed in the suction surface of the blade, and the corrugated curve form of the corrugated grooves is a multi-section circular curve or a sine curve. Suction holes are formed in wave troughs of the corrugated grooves, and a plurality of rows of suction holes are formed in the spanwise direction of the adsorption type compressor blade. The corrugated grooves are provided for blade shock wave intensity control, and the shock wave / wall surface interference effect is weakened; the pre-compression blade profile design is used for further reducing the front Mach number of the shock wave and reducing the shock wave intensity; and the plurality of rows of suction holes are formed in the wave troughs of the corrugated grooves to control flow separation of the supersonic blade. According to the coupling control method of the corrugated grooves and the pre-compression blade profile, the supersonic adsorption type compressor blade can achieve a good control effect under the low suction flow, and the structural strength of the blade is enhanced.

Description

technical field [0001] The invention relates to the field of compressors, in particular to a supersonic adsorption compressor blade with corrugated grooves on the suction surface for controlling shock wave / wall interference. Background technique [0002] The demand for higher thrust-to-weight ratio engines in modern aviation aircraft technology promotes the development of aero-engines to higher stage loads and fewer stages. With the increase of compressor load, the shock wave intensity in transonic and supersonic compressors increases continuously, and the shock wave loss and flow interference caused by strong shock waves limit the improvement of compressor performance. Therefore, it is necessary to control the shock wave in the trans- and supersonic compressors to weaken the shock wave intensity. In addition, higher stage loads often result in inevitable flow separation, resulting in greater losses, resulting in reduced compressor stage loads. Therefore, it is of great si...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/38
CPCF04D29/384
Inventor 曹志远张翔宋澄高玺张飞
Owner NORTHWESTERN POLYTECHNICAL UNIV
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