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Experimental Evaluation of an Axial-Flow Transonic Compressor FREE

[+] Author Affiliations
T. Tamaki, S. Nagano

Ishikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan

Paper No. 76-GT-34, pp. V01AT01A034; 11 pages
doi:10.1115/76-GT-34
From:
  • ASME 1976 International Gas Turbine and Fluids Engineering Conference
  • Volume 1A: General
  • New Orleans, Louisiana, USA, March 21–25, 1976
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7974-0
  • Copyright © 1976 by ASME

abstract

A five-stage transonic compressor was designed and tested to obtain overall performance and surge limits over a wide rotational speed range. Compressor surge limits are evaluated using individual stage performance characteristics with the aid of a single-stage test. These show that surging at low rotational speed occurs when rotating stall occurs in the first stage and that the wider operating range multi-stage compressor can be realized with the lower aspect ratio blades. On the basis of these test results, a simple model is constructed in order to evaluate the effect of the axial velocity ratio on the flow in a rotor blade row.

Copyright © 1976 by ASME
This article is only available in the PDF format.

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