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Turbine Stator Well Heat Transfer and Cooling Flow Optimisation

[+] Author Affiliations
Jeffrey A. Dixon, Ivan L. Brunton, Timothy J. Scanlon, Grzegorz Wojciechowski

Rolls-Royce plc, Derby, UK

Vassilis Stefanis, Peter R. N. Childs

University of Sussex, Brighton, UK

Paper No. GT2006-90306, pp. 1375-1383; 9 pages
doi:10.1115/GT2006-90306
From:
  • ASME Turbo Expo 2006: Power for Land, Sea, and Air
  • Volume 3: Heat Transfer, Parts A and B
  • Barcelona, Spain, May 8–11, 2006
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4238-X | eISBN: 0-7918-3774-2
  • Copyright © 2006 by ASME

abstract

CFD methods are increasingly being used in gas turbine secondary flow system analysis and design to establish flow distribution and convective heat transfer in internal cavities. A key area of concern is the complex flows adjacent to turbine disc rims, where undesirable levels of hot annulus gas would be ingested were it not for the cooling air supplied to limit its effects on disc rim and blade fixing temperature levels. This paper presents results from a study to investigate the practicality of applying this method to the flow distribution and heat transfer in the disc rim sealing cavity between two adjacent turbine stages, referred to here as a turbine stator well. Also described is the test facility designed to validate the CFD analysis and some preliminary results from comparisons of 3D flow solutions, with measured test data.

Copyright © 2006 by ASME

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