0
RESEARCH PAPERS

Numerical Representation of Inlet and Exit Boundary Conditions in Transient Cascade Flow

[+] Author and Article Information
S. Gopalakrishnan

AVCO Lycoming Division, Stratford, Conn.

R. Bozzola

Aerodynamic Analysis, AVCO Lycoming Division, Stratford, Conn.

J. Eng. Power 95(4), 340-344 (Oct 01, 1973) (5 pages) doi:10.1115/1.3445741 History: Received January 11, 1973; Online July 14, 2010

Abstract

An important building block in the development of finite difference time dependent techniques for mixed supersonic-subsonic flow calculation is the treatment of the inlet and exit boundary conditions. For cascade computations, it is convenient to locate the planes at a finite distance from the blade and hence conditions along these planes must be allowed to vary according to the overall cascade performance. It is shown in this paper that as long as the meridional velocity is subsonic, three flow variables must be specified at the inlet and one variable at the exit. The remaining flow variables must be computed as part of the solution. The paper contains a method derived from the theory of characteristics for the computation of the remaining variables under the assumption that the flow is axisymmetric at the inlet and exit planes. The response of typical turbine and compressor cascades to back pressure variations as computed by this technique is also presented.

Copyright © 1973 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Tables

Errata

Discussions

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