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Effect of Coolant Entry Orientation on Flow and Heat Transfer in the Trailing Region Channels of a Gas Turbine Vane

[+] Author Affiliations
N. Kulasekharan, B. V. S. S. S. Prasad

Indian Institute of Technology - Madras, Chennai, India

Paper No. GT2008-50951, pp. 849-863; 15 pages
doi:10.1115/GT2008-50951
From:
  • ASME Turbo Expo 2008: Power for Land, Sea, and Air
  • Volume 4: Heat Transfer, Parts A and B
  • Berlin, Germany, June 9–13, 2008
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4314-7 | eISBN: 0-7918-3824-2
  • Copyright © 2008 by ASME

abstract

The present work is concerned with the computational analysis of flow and heat transfer from the circular pin fin channels in the trailing edge region of a gas turbine vane. Combined effects of channel shape, conjugate boundary condition and flow orientation are studied. Four different channel shapes: Straight Rectangular, Straight Converged, Cambered Rectangular and Cambered Converged are considered. Both straight and lateral coolant entry are investigated at a nominal Reynolds number of 20,000. Numerical simulations are performed for the steady, incompressible, turbulent flow with the help of a computational fluid dynamics code. A structured hexahedral mesh having about 5 million cells is generated in the domain. The computational methodology is validated against the data from a standard ERCOFTAC bench mark test case. Flow and heat transfer characteristics at various locations in the channel and the axial temperature variation for a chosen pin are reported.

Copyright © 2008 by ASME

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