Theoretical and Experimental Determination of Pressure Losses in a Single-Stage Axial Flow Compressor

[+] Author and Article Information
Y. Le Bot, J. Paulon, P. Belaygue

O. N. E. R. A., 92 Chatillon-sous-Bagneux, France

J. Eng. Power 92(4), 407-414 (Oct 01, 1970) (8 pages) doi:10.1115/1.3445371 History: Received February 02, 1970; Online July 14, 2010


A single, isolated, test axial compressor rotor in a constant section annular duct is used for determination of off-design pressure losses. The results obtained are interpreted by means of loss coefficients and description of the flow field is deduced from a simplified actuator theory that takes into account pressure losses. Rotor stall limit is interpreted as that limit mass flow rate for which no continuous solution of the equations can be obtained. Unstable operations that take place for mass flow rates smaller than the stall limit are shown to be either rotating stall or wall separation, according to the shape of the downstream pressure profile. Experiments on the rotor confirm validity of these assumptions.

Copyright © 1970 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