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Aerodynamic Design of Transonic Tip Sections

[+] Author Affiliations
A. Stein, D. C. Hofer

GE Global Research Center, Niskayuna, NY

V. Filippenko

GE Europe, Moscow, Russia

J. Slepski

GE Energy, Schenectady, NY

Paper No. GT2010-22165, pp. 2109-2118; 10 pages
doi:10.1115/GT2010-22165
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 7: Turbomachinery, Parts A, B, and C
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4402-1 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

This paper systematically explores the aerodynamic design space of transonic tip sections for large steam turbines. The sections studied in this work have subsonic inlet relative Mach numbers, and supersonic exit Mach numbers up to 1.75. Two-dimensional CFD evaluations using numerical solvers MISES and TACOMA are used to assess the performance impact of design parameters. Geometric features including subsonic overlap, supersonic overlap, trailing edge thickness, trailing edge wedge angle and camber distribution are evaluated for their effect on the section performance. An optimal geometry is then generated incorporating the best features from each of the individual parameter studies.

Copyright © 2010 by ASME
Topics: Design

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