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Scaling of Turbine Blade Roughness for Model Studies

[+] Author Affiliations
Hugh M. McIlroy, Jr.

University of Idaho at Idaho Falls, Idaho Falls, ID

Ralph S. Budwig

University of Idaho, Moscow, ID

Donald M. McEligot

Idaho National Engineering and Environmental Laboratory, Idaho Falls, ID

Paper No. IMECE2003-42167, pp. 99-105; 7 pages
doi:10.1115/IMECE2003-42167
From:
  • ASME 2003 International Mechanical Engineering Congress and Exposition
  • Heat Transfer, Volume 2
  • Washington, DC, USA, November 15–21, 2003
  • Conference Sponsors: Heat Transfer Division
  • ISBN: 0-7918-3718-1 | eISBN: 0-7918-4663-6, 0-7918-4664-4, 0-7918-4665-2
  • Copyright © 2003 by ASME

abstract

The purpose of this note is to provide an approach to scaling turbine blade roughness so a large-scale experiment will yield useful results despite lack of detailed knowledge about the application. In the process, an apparently new approach for scaling of actual turbine blade roughness on an experimental model of a rough turbine blade is presented. Rough surface data from a first-stage high-pressure turbine rotor, estimates of engine operating conditions representative of high-performance aircraft, and assumed matches of the Reynolds number and acceleration parameter ranges are used. A scaling factor is determined by estimating and matching the nondimensional roughness (in wall coordinates) of a typical airfoil for a model.

Copyright © 2003 by ASME

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