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Conjugate Heat Transfer Analysis of NASA C3X Film Cooled Vane With an Object-Oriented CFD Code

[+] Author Affiliations
Luca Mangani, Matteo Cerutti

CFD Engineering S.r.l, Firenze, Italy

Massimiliano Maritano

Ansaldo Energia S.p.A., Genova, Italy

Martin Spel

R.Tech, Verniolle, France

Paper No. GT2010-23458, pp. 1805-1814; 10 pages
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 4: Heat Transfer, Parts A and B
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4399-4 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME


This paper presents the developments done on a CFD unstructured solver, based on the OpenFOAM® CFD libraries, to perform conjugate heat transfer simulations in turbomachinery applications. The solver uses a SIMPLE-C All-Mach algorithm with a special treatment for the pressure corrector equation to deal with highly compressible flows. Moreover, the solver provides an exhaustive turbulence model library, specific for heat transfer calculations and an implicit treatment for fluid-to-fluid and solid-to-fluid boundaries using a generic grid interface (GGI) that allows a greater mesh generation flexibility. The development of the generic grid interface is described in the current paper. The conjugate numerical methodology was employed to predict the metal temperature of a three-dimensional first stage gas turbine blade at realistic operating conditions. The validation case is based on the 1988 NASA C3X experimental setup of a internally and film cooled vane. The stator vane was internally cooled by an array of radial cooling channels of constant cross-sectional area an externally by rows of film cooling holes. The mesh has been generated with GridPRO® , using a multi block structured approach. The optimization methods used in the grid generator provide a full hex grid maintaining mesh orthogonality at the walls and within the domain and allowing the nodes to be moved to an optimal position. Numerical and experimental results are compared in terms of pressure and temperature distribution on the blade wall at mid-span, as well as heat transfer coefficient profiles.

Copyright © 2010 by ASME



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