A Practical Method of Predicting Transonic-Compressor Performance

[+] Author and Article Information
W. C. Swan

Research—Mechanical Engineering Staff, Transport Division, Boeing Airplane Company, Renton, Wash.

J. Eng. Power 83(3), 322-330 (Jul 01, 1961) (9 pages) doi:10.1115/1.3673194 History: Received September 10, 1960; Online January 10, 2012


A real fluid-stream filament axial-flow-compressor performance method is deduced from theory and statistics. The nonisentropic complete radial equilibrium-momentum equation is combined with the continuity, energy, and flow-process equations to yield a group of equations which is readily adaptable to solution on a digital computer. The real fluid effects, such as subsonic viscous losses and shocks at cascade entry, are deduced from statistics in terms of a blade-loading parameter. A program suitable for rapid calculations on a digital computer is presented in schematic form. A comparison between the deduced and the measured performances of an arbitrary stage is made. The correlation obtained indicates that the performance method is reliable.

Copyright © 1961 by ASME
Your Session has timed out. Please sign back in to continue.





Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In