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

[+] 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(1), 128-139 (Jan 01, 1997) (12 pages) doi:10.1115/1.2841001 History: Received April 07, 1995; Online January 29, 2008


This is Part Four of a four-part paper. It begins with Section 16.0 and concludes the description of 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, the computational predictions made using several modern boundary layer codes are presented. Both steady codes and an unsteady code were evaluated. The results are compared with time-averaged and unsteady integral parameters measured for the boundary layers. Assessments are made to provide guidance in using the predictive codes to locate transition and predict loss. Conclusions from the computational analyses are then presented.

Copyright © 1997 by The American Society of Mechanical Engineers
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