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The aerodynamic design and performance of the NASA/GE E3 low pressure turbineThe aerodynamic design and scaled rig test results of the low pressure turbine (LPT) component for the NASA/General Electric Energy Efficient Engine (E3) are presented. The low pressure turbine is a highly loaded five-stage design featuring high outer wall slope, controlled vortex aerodynamics, low stage flow coefficient, and reduced clearances. An assessment of its performance has been made based on a series of scaled air turbine tests which were divided into two phases: Block I (March through August, 1979) and Block II (June through September, 1981). Results from the Block II five-stage test, summarized in the paper, indicate that the E3 LPT will attain an efficiency level of 91.5 percent at the Mach 0.8/35,000 ft. max. climb altitude design point. This is relative to program goals of 91.1 percent for the E3 demonstrator engine and 91.7 percent for a fully developed flight propulsion system LPT.
Document ID
19840061399
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cherry, D. G.
(General Electric Co. Cincinnati, OH, United States)
Dengler, R. 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 84-1162
Accession Number
84A44186
Distribution Limits
Public
Copyright
Other

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