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Aerodynamic Research on Highload Axial Compressor With a Chordwise Split PUBLIC ACCESS

[+] Author Affiliations
Zhi-Gang Zhang, Ping-Cheng Shen

Shanghai Institute of Mechanical Engineering, Shanghai, China

Hong Zhu

Shanghai Blowing Works, Shanghai, China

Jia-Hua Lu

Shanghai University of Engineering Science, Shanghai, China

Yan-Sheng Li

SIME, Shanghai, China

Paper No. 89-GT-11, pp. V001T01A004; 6 pages
doi:10.1115/89-GT-11
From:
  • ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Toronto, Ontario, Canada, June 4–8, 1989
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7913-9
  • Copyright © 1989 by ASME

abstract

This paper deals with a novel configuration of axial compressor cascade with chordwise split. Contrast to tandem cascade and cascade with a slot from pressure surface to suction surface, the cascade with a chordwise split not only controls the separation of boundary layer, increases flow turning angle and stage load, thus the compressor length can be shortened or pressure ratio increased, but also the flow pattern in the split is different.

The research work done shows that the cascade with chordwise split avoids or delays the separation of boundary layer on blade surface effectively thus may lead to a larger camber angle. The theoretical model and program for locating the split position and predicting flow field in cascade passage by using Finite Element Method are given.

Experiments have verified the mathematical model and the preferable effects of the chordwise split. The results of calculation correspond to the test data satisfactorily.

Copyright © 1989 by ASME
Topics: Compressors
This article is only available in the PDF format.

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