A compressor cascade experimental device

An experimental device, compressor technology, applied in mechanical equipment, machine/engine, pump control, etc., can solve the problem that the blade surface and the end wall of the blade cascade, and suction experiments cannot be carried out at the same time, so as to reduce the loss and weaken the secondary Flow, the effect of improving flow

Inactive Publication Date: 2011-12-21
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0005] In order to overcome the deficiency in the prior art that the suction test of the blade surface and the end wall of the cascade cannot be carried out simultaneously, the present invention proposes a compressor cascade experimental device

Method used

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  • A compressor cascade experimental device
  • A compressor cascade experimental device
  • A compressor cascade experimental device

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Embodiment Construction

[0032] This embodiment is an experimental device for a combined suction type compressor cascade on the surface of the blade and the end wall of the cascade, which mainly consists of the blade 1, the suction blade 2, the first suction cover 3, the mounting frame and the second Suction cover 7 forms. In the present invention, according to the grid pitch of the compressor cascade, the number of blades 1 is determined to be 4 to 8, the number of suction blades 2 is 1 to 5, and the number of blades 1 is an even number, and the number of suction blades 2 is an odd number. In the present invention, a rectangular blade suction slot is opened on the suction surface of the suction blade 2, and the center of the blade suction slot is distributed in the chord direction position of the suction blade 2 on the suction blade 2. 25-60% of the chord length. In this embodiment, taking 8 blades 1 and 3 suction blades 2 as an example, taking the center of the blade suction slot on the suction bl...

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Abstract

A compressor cascade experimental device includes an even number of blades and an odd number of suction blades. An even number of blades and an odd number of suction blades are installed on the mounting surfaces of the first grid plate and the second grid plate, and the suction blades are located at the center of the first grid plate and the second grid plate. There is an end wall suction slot between each mounting slot. The installation groove of the suction vane and the suction groove of the end wall are provided with through gas suction slots. The first suction hood and the second suction hood are respectively installed at the centers of the outer surfaces of the first grid plate and the second grid plate, and the central air hole of the suction cover corresponds to the gas suction slit and the end wall suction groove respectively. In the present invention, through the combined suction of the blade surface of the compressor cascade and the end wall of the cascade, and connecting the second suction cover and the first suction cover to the suction equipment, the surface of the blade and the surface of the blade under different gas suction quantities can be simultaneously performed. The combined suction experiment of the end wall of the cascade obtains the optimal suction volume of the compressor cascade and improves the pressure ratio and efficiency of the compressor cascade.

Description

technical field [0001] The invention relates to the field of engine experiments, in particular to an experimental device for combined suction-type air compressor blade cascades with blade surfaces and blade cascade end walls. Background technique [0002] Higher stage pressure ratio and higher efficiency have always been the goals pursued by compressor designers. Since Kerrebrock et al. of MIT first proposed the new concept of adsorption compressor in 1997, adsorption compressor has gradually become an important research direction to improve the stage pressure ratio and efficiency of the compressor. [0003] Researchers at home and abroad have done a lot of research work on the adsorption compressor cascade. Lan Faxiang, Zhou Baihao, Liang Dewang and Huang Guoping from Nanjing University of Aeronautics and Astronautics / China Gas Turbine Research Institute introduced a trans-supersonic adsorption compressor planar Cascade test system, in which cascade test pieces include le...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D27/00
Inventor 刘波曹志远赵鹏程朱柱国赵旭民黄建李志鹏
Owner NORTHWESTERN POLYTECHNICAL UNIV
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