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An Experimental Evaluation of the Performance Deficit of an Aircraft Engine Starter Turbine
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English
Abstract
An experimental investigation was made at NASA-Lewis Research Center to determine the reasons for the low aerodynamic performance of a 13.5-centimeter-tip-diameter aircraft engine starter turbine. The investigation consisted of an evaluation of both the stator and the stage. An approximate ten percent improvement in turbine efficiency was obtained when the honeycomb shroud over the rotor blade tips was filled to obtain a solid shroud surface.
Citation
Haas, J., Roelke, R., and Hermann, P., "An Experimental Evaluation of the Performance Deficit of an Aircraft Engine Starter Turbine," SAE Technical Paper 801137, 1980, https://doi.org/10.4271/801137.Also In
References
- Haas J. E. et. al “An Experimental Investigation to Determine the Reasons for the Low Aerodynamic Performance of a 13.5-Centimeter Tip Diameter Aircraft Engine Starter Turbine.” NASA TP