Boundary Layer Development in Axial Compressors and Turbines: Part 2 of 4—Compressors

[+] 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(3), 426-444 (Jul 01, 1997) (19 pages) doi:10.1115/1.2841142 History: Received April 07, 1995; Online January 29, 2008


This is Part Two of a four-part paper. It begins with Section 6.0 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 used to construct the composite picture for compressors given in the discussion in Section 5.0 of Part 1. We show the data from the surface hot-film gages and the boundary layer surveys, give a thorough interpretation for the baseline operating condition, and then show how this picture changes with variations in Reynolds number, airfoil loading, frequency of occurrence of wakes and wake turbulence intensity. Detailed flow features are described using raw time traces. The use of rods to simulate airfoil wakes is also evaluated.

Copyright © 1997 by The American Society of Mechanical Engineers
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