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A Simple Method for Supersonic Compressor Cascading Performance Prediction FREE

[+] Author Affiliations
B.-A. Gustafson

Chalmers University of Technology, Gothenburg, Sweden

Paper No. 76-GT-64, pp. V01AT01A064; 10 pages
doi:10.1115/76-GT-64
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

This investigation is an effort to break down the very complicated flow of a supersonic compressor cascade into a simple model which, in spite of the simplifications, is able to predict realistic values of overall cascade performance parameters. The investigation is limited to high reaction cascades and is focused on design conditions for Double-Circular-Arc blading. The selected flow model includes the inlet flow, which determines the incidence angle and the massflow, the λ-shaped passage shock followed by a boundary-layer separation, the formation of a jet and wake flow, the second shock, and finally the mixing process to a uniform flow downstream of the cascade. Calculated results (inlet Mach number range 1.1 to 1.5) are compared to measured data taken from the literature.

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

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