0
RESEARCH PAPERS

Boundary Layer Development in Axial Compressors and Turbines: Part 3 of 4— LP Turbines

[+] Author and Article Information
D. E. Halstead, D. C. Wisler, H.-W. Shin

GE Aircraft Engines, Cincinnati, OH 45215

T. H. Okiishi

Iowa State University, Ames, IA 50011

G. J. Walker

University of Tasmania, Hobart, Tasmania

H. P. Hodson

University of Cambridge, Cambridge, United Kingdom

J. Turbomach 119(2), 225-237 (Apr 01, 1997) (13 pages) doi:10.1115/1.2841105 History: Received April 07, 1995; Online January 29, 2008

Abstract

This is Part Three of a four-part paper. It begins with Section 11.0 and continues to describe the comprehensive experiments and computational analyses that have led to a detailed picture of boundary layer development on airfoil surfaces in multistage turbomachinery. In this part, we present the experimental evidence that we used to construct the composite picture for LP turbines that was given in the discussion in Section 5.0 of Part 1. We present and interpret the data from the surface hot-film gages and the boundary layer surveys for the baseline operating condition. We then show how this picture changes with variations in Reynolds number, airfoil loading, and nozzle–nozzle clocking.

Copyright © 1997 by The American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Tables

Errata

Discussions

Related

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