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Computational Investigations in the Trailing Edge Region of Cooled Turbine Vane: Comparison of Different Channel Shapes

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

Indian Institute of Technology – Madras, Chennai, India

Paper No. GT2007-27421, pp. 385-396; 12 pages
doi:10.1115/GT2007-27421
From:
  • ASME Turbo Expo 2007: Power for Land, Sea, and Air
  • Volume 4: Turbo Expo 2007, Parts A and B
  • Montreal, Canada, May 14–17, 2007
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4793-4 | eISBN: 0-7918-3796-3
  • Copyright © 2007 by ASME

abstract

Thermal hydraulic characteristics of coolant flow through passages consisting of rib turbulators, pin fin array and trailing edge slot are reported. Channels of straight, trapezoidal and curved shapes are considered. Continuity, momentum and energy equations for a three dimensional incompressible flows are solved. A constant heat flux value is specified over the coolant channel walls, rib surfaces and circumferential faces of the pin-fins. Total pressure loss coefficient, pin end-wall and pin surface averaged Nusselt number are estimated and presented for the pin array, for Reynolds number ranging from 20,000 to 40,000. Cambered channels showed highest pin end wall averaged heat transfer than trapezoidal channel, which is higher than the straight channel.

Copyright © 2007 by ASME

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