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Reduction of Tip Clearance Losses Through 3-D Airfoil Designs FREE

[+] Author Affiliations
J. Brent Staubach, Om P. Sharma, Gary M. Stetson

Pratt and Whitney, E. Hartford, CT

Paper No. 96-TA-013, pp. V001T08A003; 12 pages
doi:10.1115/96-TA-013
From:
  • ASME 1996 Turbo Asia Conference
  • ASME 1996 Turbo Asia Conference
  • Jakarta, Indonesia, November 5–7, 1996
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7877-4
  • Copyright © 1996 by ASME

abstract

Results are presented from a program, conducted to investigate the impact of spanwise stacking of turbine airfoil sections on tip clearance flows. Numerical as well as physical experiments were performed to demonstrate that these airfoils yielded about 40% reduction in tip clearance losses compared to those designed with a conventional approach. Three dimensional, steady Euler and Reynolds Averaged Navier Stokes (RANS) codes were used to execute the numerical experiments. Initial physical experiments were performed in a water tunnel by using linear cascades to validate the design concepts. The verification of the overall design concepts was executed in an uncooled full scale rotating rig.

Copyright © 1996 by ASME
This article is only available in the PDF format.

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