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.
An Experimental Evaluation of the Performance Deficit of an Aircraft Engine Starter Turbine
Sae Technical Papers
Aerospace Congress and Exposition ; 1980
01.09.1980
Aufsatz (Konferenz)
Englisch