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Passive Boundary Layer Control on a Highly Loaded Low Pressure Turbine Cascade

[+] Author Affiliations
Markus Martinstetter, Reinhard Niehuis

University of the Federal Armed Forces Munich, Neubiberg, Germany

Matthias Franke

MTU Aero Engines GmbH, Munich, Germany

Paper No. GT2010-22739, pp. 1315-1326; 12 pages
doi:10.1115/GT2010-22739
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 7: Turbomachinery, Parts A, B, and C
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4402-1 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

The objective of this work is to investigate the performance of a highly loaded Low Pressure Turbine (LPT)-Cascade over a wide range of turbomachinery realistic Reynolds numbers, while maintaining a constant real engine Mach number. Fundamental investigations show a strong increase in total pressure loss at low Reynolds number due to an enlarged separation region on the suction surface. The aim of this paper is to reduce total pressure loss through the application of passive turbulators on the suction surface. Both, steady inflow conditions, as well as effects of rotor-stator-interaction, are considered. To identify the importance of turbulator geometry on loss reduction, three dimensional turbulator elements have been compared to a two dimensional trip. Both passive devices were located on the suction surface and the three dimensional elements performed better at high Reynolds numbers. Based on the experimental investigations, the use of passive boundary layer control can be recommended as a promising approach for loss reduction on highly loaded low pressure turbine profiles.

Copyright © 2010 by ASME

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