Systematic experimental investigations of the transonic flow through a plane cascade consisting of profiles designed for a highly loaded gas turbine rotor of a high pressure stage were performed. The experiments comprise side wall pressure distribution measurements in a blade passage and both profile pressure distribution and wake traverse measurements in various planes from midspan to the side wall. The parameters varied are the inlet flow angle and the downstream Mach number. Schlieren photopraphs and oil flow patterns on the blades and on the side wall are included. The experimental results are interpreted with respect to the existing flow models describing shock wave boundary layer interactions and secondary flow effects. The experimental data are compared with three-dimensional viscous numerical results.
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ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
June 3–6, 1991
Orlando, Florida, USA
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-7898-9
PROCEEDINGS PAPER
Detailed Measurements of the Flow Field in a Transonic Turbine Cascade Free
E. Detemple-Laake
E. Detemple-Laake
DLR, Institute for Experimental Fluid Mechanics, Bunsenstr, Göttingen, FRG
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E. Detemple-Laake
DLR, Institute for Experimental Fluid Mechanics, Bunsenstr, Göttingen, FRG
Paper No:
91-GT-029, V001T01A008; 9 pages
Published Online:
March 10, 2015
Citation
Detemple-Laake, E. "Detailed Measurements of the Flow Field in a Transonic Turbine Cascade." Proceedings of the ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. Volume 1: Turbomachinery. Orlando, Florida, USA. June 3–6, 1991. V001T01A008. ASME. https://doi.org/10.1115/91-GT-029
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