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Aerodynamic Performance of Large Centrifugal Compressors PUBLIC ACCESS

[+] Author Affiliations
Fumikata Kano, Noriyuki Tazawa, Yoshiteru Fukao

Kobe Steel, Ltd., Kobe, Japan

Paper No. 82-GT-17, pp. V001T01A009; 10 pages
doi:10.1115/82-GT-17
From:
  • ASME 1982 International Gas Turbine Conference and Exhibit
  • Volume 1: Turbomachinery
  • London, England, April 18–22, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7956-6
  • Copyright © 1982 by ASME

abstract

The aerodynamic performance of impellers and diffusers of the large centrifugal compressor were studied. A performance design procedure based on the quasi-three-dimensional flow analysis which is combined with the boundary layer theory was developed. The conditions of the boundary layer at the impeller exit and at the diffuser vane throat were calculated, and the three-dimensional measurements were carried out. This result shows that the low momentum flow is accumulated at the corner of the shroud and the blade suction side of the impeller. These results were applied to the development of a large four-stage isothermal compressor which handles the air for an air separation apparatus. This was tested in the field and showed an isothermal efficiency of 76 percent.

Copyright © 1982 by ASME
Topics: Compressors
This article is only available in the PDF format.

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