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Film Cooling Flow by Double Rows of Compound Angle and Compound Angle Shaped Holes

[+] Author Affiliations
Farzad Bazdidi-Tehrani

Iran University of Science & Technology, Tehran, Iran

Pegah Pezeshkpour

University of Stuttgart, Stuttgart, Germany

Paper No. GT2013-95272, pp. V03BT13A048; 9 pages
  • ASME Turbo Expo 2013: Turbine Technical Conference and Exposition
  • Volume 3B: Heat Transfer
  • San Antonio, Texas, USA, June 3–7, 2013
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5515-7
  • Copyright © 2013 by ASME


The present paper describes a three-dimensional finite volume numerical simulation of turbulent flow and heat transfer over a flat plate embedded with four different configurations of film cooling jet holes. Recently, more advanced techniques are introduced to improve the effectiveness of film cooling method such as the Compound Angle Shaped Holes (CASH). The first two studied configurations in this article comprise double rows of staggered compound angle holes. The presented final configurations encompass double rows of the CASH geometry, with inline and staggered arrangements, consecutively. The second order upwind scheme is employed for the discretization of equations and the pressure-velocity coupling is performed by using the SIMPLEC algorithm. Moreover, the k-ω shear stress transport turbulence model is applied for the flow simulation. Present results on the compound angle holes show that the span wise-averaged cooling effectiveness is higher when 6D span wise hole spacing is employed as compared with 7.8D spacing. Results have emerged that the double rows of staggered CASH geometry display higher cooling effectiveness than that of the inline arrangement. Furthermore, comparison of the present spanwise effectiveness and ratio of Stanton numbers with the available experimental data shows reasonable agreement for the first and second configurations.

Copyright © 2013 by ASME



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