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CFD-FE Automation and Thermo-Fluid Characterisation of an IP Turbine Cavity

[+] Author Affiliations
David Bagshaw, Sohail Alizadeh, Christophe Mabilat

Atkins (Fluid Mechanics), Epsom, Surrey, UK

Leo Lewis

Rolls-Royce plc, Derby, Derbyshire, UK

Paper No. GT2010-22710, pp. 1061-1070; 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 Rolls-Royce plc


This paper shows a method by which the combined CFD-FE analysis process for prediction of aero engine disc temperatures and thermal growths is sped up, with relatively small computational power requirements. The method, known as the temperature influence coefficients method (Lewis et al. (2004)) is further developed into an integrated/automated system, providing a complete thermo-mechanical solution with minimal user input and which fits within aero engine design timescales. 3-D CFD solutions are produced, adiabatically and diabatically, at three key engine operating conditions, for a turbine rotor-stator cavity in a large-scale aero-engine. A standardised method is developed for characterisation of the surface and near-wall coefficients. The variation of these parameters along the disc surface is presented, showing the nature of the flow field adjacent to the disc. The paper describes the development of the automated transfer process of the coefficients into the separate axisymmetric FE model, which can then be run through any cycle. The temperature results and the process time results from the temperature influence coefficients method are compared with existing methods for a 13000 second flight cycle.

Copyright © 2010 by Rolls-Royce plc



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