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performance of a high-work low aspect ratio turbine tested with a realistic inlet radial temperature profileExperimental results are presented for a 0.767 scale model of the first stage of a two-stage turbine designed for a high by-pass ratio engine. The turbine was tested with both uniform inlet conditions and with an inlet radial temperature profile simulating engine conditions. The inlet temperature profile was essentially mixed-out in the rotor. There was also substantial underturning of the exit flow at the mean diameter. Both of these effects were attributed to strong secondary flows in the rotor blading. There were no significant differences in the stage performance with either inlet condition when differences in tip clearance were considered. Performance was very close to design intent in both cases. Previously announced in STAR as N84-24589
Document ID
19840057452
Document Type
Conference Paper
Authors
Stabe, R. G.
(NASA Lewis Research Center Cleveland, OH, United States)
Whitney, W. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Moffitt, T. P.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1984
Subject Category
AIRCRAFT PROPULSION AND POWER
Report/Patent Number
AIAA PAPER 84-1161
Distribution Limits
Public
Copyright
Other