An experimental investigation was made at the 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 10-percent improvement in turbine efficiency was obtained when the honeycomb shroud over the rotor blade tips was filled to obtain a solid shroud surface. (Author)
Reasons for Low Aerodynamic Performance of 13.5-Centimeter-Tip-Diameter Aircraft Engine Starter Turbine
1981
19 pages
Report
Keine Angabe
Englisch
An Experimental Evaluation of the Performance Deficit of an Aircraft Engine Starter Turbine
SAE Technical Papers | 1980
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