This paper presents the performance obtained from testing single-stage, full-admission, axial supersonic turbine configurations. A matrix of four nozzle and two rotor blade configurations was evaluated. Turbine pressure ratios were varied from 33 to 140 for velocity ratios of 0.2 to 0.5. The test results indicate that constant-channel width and variable-channel width rotor blading give comparable performance. Optimal nozzle and blade configurations yielded turbine efficiencies of 77 percent.
Experimental Investigation of Supersonic Turbine Performance
Kurzrock, JW. "Experimental Investigation of Supersonic Turbine Performance." Proceedings of the ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. Volume 1: Turbomachinery. Toronto, Ontario, Canada. June 4–8, 1989. V001T01A094. ASME. https://doi.org/10.1115/89-GT-238
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