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The Effect of Ultrapolish on a Transonic Axial Rotor

[+] Author Affiliations
William B. Roberts

Airfoil Technologies International, Freemont, CA

Patricia S. Prahst

AP Solutions, Solon, OH

Scott Thorp, Anthony J. Strazisar

NASA Glenn Research Center, Cleveland, OH

Paper No. GT2005-69132, pp. 381-387; 7 pages
doi:10.1115/GT2005-69132
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4730-6 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

Back-to-back testing has been done using NASA fan rotor 67 in the Glenn Research Center W8 Axial Compressor Test Facility. The rotor was baseline tested with a normal industrial RMS surface finish of 0.5–0.6 μm (20–24 microinches) at 60, 80 and 100% of design speed. At design speed the tip relative Mach number was 1.38. The blades were then removed from the facility and ultrapolished to a surface finish of 0.125 μm (5 microinch) or less and retested. At 100% speed near the design point, the ultrapolished blades showed approximately 0.3–0.5% increase in adiabatic efficiency. The difference was greater near maximum flow. Due to increased relative measurement error at 60 and 80% speed, the performance difference between the normal and ultrapolished blades was indeterminate at these speeds.

Copyright © 2005 by ASME
Topics: Rotors

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