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Passive Shroud Cooling Concepts for HP Turbines: Experimental Investigations

[+] Author Affiliations
Vasudevan Kanjirakkad, Richard Thomas, Howard Hodson

University of Cambridge, Cambridge, UK

Erik Janke, Frank Haselbach

Rolls-Royce Deutschland, Dahlewitz, Germany

Chris Whitney

Alstom Power Technology Centre, Whetstone, Leicester, UK

Paper No. GT2006-91250, pp. 1065-1074; 10 pages
  • 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


The cooling of rotor shrouds in the first stage of a high-pressure turbine requires special attention as flatter turbine inlet temperature profiles and more highly loaded blades result in increased thermal and mechanical stresses. The use of film cooling and/or internal convective cooling makes the rotor shroud heavier and oversized, restricting the maximum rotational speed. Alternative methods are therefore sought to achieve improved cooling of the shroud. This paper discusses the low speed experimental investigation of two ‘passive’ cooling concepts known as ‘rail cooling’ and ‘platform cooling’. It has been shown experimentally that the modified cooling method, namely the platform cooling, substantially improves the rotor shroud coolant distribution in the critical areas whilst employing significantly lower amounts of coolant.

Copyright © 2006 by ASME
Topics: Cooling , Turbines



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