This paper presents results of a detailed investigation of turbine tip-leakage flows at high Mach numbers. The experimental work was carried out using a small blow-down wind tunnel. An idealized blade test section was used to study blade tip-clearance effects in transonic conditions. Unshrouded blade tips are considered and different tip gap heights are investigated. A high blade exit Mach number of Me = 2 was selected deliberately. While conventional transonic turbine stages generally operate at lower supersonic exit Mach numbers, the conditions are representative for ORC turbines. Both experimental and numerical results are presented in this contribution. The results indicate, that tip leakage flow under transonic conditions leads to a complex three-dimensional flow field. A strong interaction between tip gap vortex and trailing edge shocks was observed, that also had a profound effect on the base region. While no final statement on losses could be made in the present configuration, the results indicate a weakened shock system.
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ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition
June 11–15, 2018
Oslo, Norway
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-5100-5
PROCEEDINGS PAPER
An Experimental and Numerical Study of Tip-Leakage Flows in an Idealized Turbine Tip Gap at High Mach Numbers
Maximilian Passmann,
Maximilian Passmann
Muenster University of Applied Sciences, Steinfurt, Germany
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Stefan aus der Wiesche,
Stefan aus der Wiesche
Muenster University of Applied Sciences, Steinfurt, Germany
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Franz Joos
Franz Joos
Helmut-Schmidt University, Hamburg, Germany
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Maximilian Passmann
Muenster University of Applied Sciences, Steinfurt, Germany
Stefan aus der Wiesche
Muenster University of Applied Sciences, Steinfurt, Germany
Franz Joos
Helmut-Schmidt University, Hamburg, Germany
Paper No:
GT2018-76366, V02BT41A023; 12 pages
Published Online:
August 30, 2018
Citation
Passmann, M, aus der Wiesche, S, & Joos, F. "An Experimental and Numerical Study of Tip-Leakage Flows in an Idealized Turbine Tip Gap at High Mach Numbers." Proceedings of the ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. Volume 2B: Turbomachinery. Oslo, Norway. June 11–15, 2018. V02BT41A023. ASME. https://doi.org/10.1115/GT2018-76366
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