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Aerodynamic Performance Measurements of a Film-Cooled Turbine Stage: Experimental Results

[+] Author Affiliations
R. C. Keogh, G. R. Guenette, C. M. Spadaccini

Massachusetts Institute of Technology, Cambridge, MA

T. P. Sommer, S. Florjancic

Alstom (Switzerland), Ltd., Baden, Switzerland

Paper No. GT2002-30344, pp. 189-197; 9 pages
doi:10.1115/GT2002-30344
From:
  • ASME Turbo Expo 2002: Power for Land, Sea, and Air
  • Volume 5: Turbo Expo 2002, Parts A and B
  • Amsterdam, The Netherlands, June 3–6, 2002
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-3610-X | eISBN: 0-7918-3601-0
  • Copyright © 2002 by ASME

abstract

Modern high performance gas turbine engines utilize film cooling to reduce the heat load on high-pressure turbine stage components, thereby increasing the maximum turbine inlet temperature at which the cycle can operate. However, increased turbine inlet temperature comes at the expense of a reduction in turbine efficiency. The objective of this research is to measure the aerodynamic performance of a film cooled turbine stage and to quantify the loss caused by film cooling. An un-cooled turbine stage was first fabricated with solid blading and tested using a newly developed short duration measurement technique. The stage was then modified to incorporate vane, blade and rotor casing film cooling. The film-cooled stage was then tested over a range of coolant-to-mainstream mass flow and temperature ratios for the same range of operating conditions (pressure ratios and corrected speeds) as the un-cooled turbine. This paper presents the experimental results for these two series of tests.

Copyright © 2002 by ASME
Topics: Measurement , Turbines

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