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The Control of Shroud Leakage Loss by Reducing Circumferential Mixing

[+] Author Affiliations
Budimir Rosic, John D. Denton

Cambridge University, Cambridge, UK

Paper No. GT2006-90946, pp. 851-859; 9 pages
doi:10.1115/GT2006-90946
From:
  • ASME Turbo Expo 2006: Power for Land, Sea, and Air
  • Volume 6: Turbomachinery, Parts A and B
  • Barcelona, Spain, May 8–11, 2006
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4241-X | eISBN: 0-7918-3774-2
  • Copyright © 2006 by ASME

abstract

Shroud leakage flow undergoes little change in the tangential velocity as it passes over the shroud. Mixing due to the difference in tangential velocity between the main stream flow and the leakage flow creates a significant proportion of the total loss associated with shroud leakage flow. The unturned leakage flow also causes negative incidence and intensifies the secondary flows in the downstream blade row. This paper describes the experimental results of a concept to turn the rotor shroud leakage flow in the direction of the main blade passage flow in order to reduce the aerodynamic mixing losses. A three-stage air model turbine with low aspect ratio blading was used in this study. A series of different stationary turning vane geometries placed into the rotor shroud exit cavity downstream of each rotor blade row was tested. A significant improvement in flow angle and loss in the downstream stator blade rows was measured together with an increase in turbine brake efficiency of 0.4%.

Copyright © 2006 by ASME

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