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Boundary Layer Development in Axial Compressors and Turbines: Part 3 of 4 — LP Turbines 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-463, pp. V001T01A111; 15 pages
doi:10.1115/95-GT-463
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 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 gauges 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 © 1995 by ASME
This article is only available in the PDF format.

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