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Interaction of Shroud Leakage Flow and Main Flow in a Three-Stage LP Turbine

[+] Author Affiliations
Jochen Gier, Bertram Stubert, Bernard Brouillet, Laurent de Vito

MTU Aero Engines, Munich, Germany

Paper No. GT2003-38025, pp. 105-116; 12 pages
doi:10.1115/GT2003-38025
From:
  • ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference
  • Volume 6: Turbo Expo 2003, Parts A and B
  • Atlanta, Georgia, USA, June 16–19, 2003
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-3689-4 | eISBN: 0-7918-3671-1
  • Copyright © 2003 by ASME

abstract

Endwall losses significantly contribute to the overall losses in modern turbomachinery, especially when aerodynamic airfoil load and pressure ratios are increased. In turbines with shrouded airfoils a large portion of these losses are generated by the leakage flow across the shroud clearance. Generally the related losses can be grouped into losses of the leakage flow itself and losses caused by the interaction with the main flow in subsequent airfoil rows. In order to reduce the impact of the leakage flow and shroud design related losses a thorough understanding of the leakage losses and especially of the losses connected to enhancing secondary flows and other main flow interactions has to be understood. Therefore, a three stage LP turbine typical for jet engines is being investigated. For the three-stage test turbine 3D Navier-Stokes computations are performed simulating the turbine including the entire shroud cavity geometry in comparison with computations in the ideal flow path. Numerical results compare favourably against measurements carried out at the high altitude test facility at Stuttgart University. The differences of the simulations with and without shroud cavities are analysed for several points of operation and a very detailed quantitative loss breakdown is presented.

Copyright © 2003 by ASME

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