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

[+] Author Affiliations
David E. Halstead, David C. Wisler, Hyoun-Woo Shin

GE Aircraft Engines, Cincinnati, OH

Theodore H. Okiishi

Iowa State University, Ames, IA

Gregory J. Walker

University of Tasmania, Hobart, Australia

Howard P. Hodson

University of Cambridge, Cambridge, UK

Paper No. 95-GT-464, pp. V001T01A112; 16 pages
doi:10.1115/95-GT-464
From:
  • ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Houston, Texas, USA, June 5–8, 1995
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7878-1
  • Copyright © 1995 by ASME

abstract

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 modem 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 entire work are then presented.

Copyright © 1995 by ASME
This article is only available in the PDF format.

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