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An experimental evaluation of the performance deficit of an aircraft engine starter turbineAn experimental investigation is presented to determine the aerodynamic performance deficit of a 13.5 - centimeter-tip-diameter aircraft engine starter turbine. The two-phased evaluation comprised both the stator and the stage performance, and the experimental design is described in detail. Data obtained from the investigation of three honeycomb shrouds clearly showed that the filled honeycomb reached a total efficiency of 0.868, 8.2 points higher than the open honeycomb shroud, at design equivalent conditions of speed and blade-jet speed ratio. It was concluded that the use of an open honeycomb shroud caused the large performance deficit for the starter turbine. Further research is suggested to ascertain stator inlet boundary layer measurements.
Document ID
19810049764
Document Type
Conference Paper
Authors
Haas, J. E. (U.S. Army, Research and Technology Laboratories, Cleveland Ohio, United States)
Roelke, R. J. (NASA Lewis Research Center Cleveland, Ohio, United States)
Hermann, P. (Sundstrand Corp. Rockford, Ill., United States)
Date Acquired
August 11, 2013
Publication Date
October 1, 1980
Subject Category
AIRCRAFT PROPULSION AND POWER
Report/Patent Number
SAE PAPER 801137
Meeting Information
Aerospace Congress and Exposition(Los Angeles, CA)
Distribution Limits
Public
Copyright
Other