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Edge Matching: Part II — Numerical Investigations

[+] Author Affiliations
J. Chen

Beijing University of Aeronautics and Astronautics, Beijing, China

L. C. Ji

Chinese Academy of Sciences, Beijing, China

Paper No. GT2005-68477, pp. 1363-1370; 8 pages
  • 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


Edge Matching (EM), presented in accompanying paper [1], may make it manipulable to utilize time-accurate unsteady flow simulation in daily design of multistage turbomachinery. The spatial relation between a blade trailing edge and the leading edge of the sequent blade row is taken into account in improving turbomachinery performance. This paper presents numerical investigations to further illustrate and validate the EM theory and its implementations. A single stage transonic axial compressor and a single stage steam turbine are modified with EM. Numerical results show that EM might provide an effective degree of freedom (DOF) for unsteady design of turbomachinery.

Copyright © 2005 by ASME



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