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Endwall Loss in Turbine Cascades

[+] Author Affiliations
John D. Coull

University of Cambridge, Cambridge, UK

Paper No. GT2016-57325, pp. V02BT38A039; 13 pages
doi:10.1115/GT2016-57325
From:
  • ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition
  • Volume 2B: Turbomachinery
  • Seoul, South Korea, June 13–17, 2016
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4970-5
  • Copyright © 2016 by ASME

abstract

Prior to the detailed design of components, turbomachinery engineers must guide a mean-line or throughflow design towards an optimum configuration. This process requires a combination of informed judgement and low-order correlations for the principle sources of loss. With these requirements in mind, this paper examines the impact of key design parameters on endwall loss in turbines, a problem which remains poorly understood.

The analysis focuses on parametric computational studies of linear cascades, which represent a simplified model of real-engine flow. The designs are nominally representative of the Low Pressure Turbine blades of an aero engine. The paper examines the variations across the design space in a quantitative manner, examining the impact of flow angles, blade thickness and suction surface aerodynamics.

Copyright © 2016 by ASME
Topics: Turbines

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