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


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
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