An experimental investigation was made 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
Aerospace Congr. ; 1980 ; Los Angeles
1980-01-01
Conference paper
No indication
English
An Experimental Evaluation of the Performance Deficit of an Aircraft Engine Starter Turbine
SAE Technical Papers | 1980
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