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The aerodynamic design and performance of the General Electric/NASA EEE fanThe aerodynamic design and test results of the fan and quarter-stage component for the GE/NASA Energy Efficient Engine (EEE) are presented. The fan is a high bypass ratio, single-stage design having 32 part-span shrouded rotor blades, coupled with a unique quarter-stage arrangement that provides additional core-stream pressure ratio and particle separation. The fan produces a bypass pressure ratio of 1.65 at the exit of the low aspect ratio vane/frame and a core-stream pressure ratio of 1.67 at the entrance to the core frame struts. The full-scale fan vehicle was instrumented, assembled and tested as a component in November 1981. Performance mapping was conducted over a range of speeds and bypass ratios using individually-controlled bypass and core-stream discharge valves. The fan bypass and core-stream test data showed excellent results, with the fan exceeding all performance goals at the important engine operating conditions.
Document ID
19830055034
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Sullivan, T. J.
(General Electric Co. Cincinnati, OH, United States)
Hager, R. D.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 11, 2013
Publication Date
June 1, 1983
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 83-1160
Accession Number
83A36252
Distribution Limits
Public
Copyright
Other

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