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Partially Turboelectric Aircraft Drive Key Performance ParametersThe purpose of this paper is to propose electric drive specific power, electric drive efficiency, and electrical propulsion fraction as the key performance parameters for a partially turboelectric aircraft power system and to investigate their impact on the overall aircraft performance. Breguet range equations for a base conventional turbofan aircraft and a partially turboelectric aircraft are found. The benefits and costs that may result from the partially turboelectric system are enumerated. A break even analysis is conducted to find the minimum allowable electric drive specific power and efficiency, for a given electrical propulsion fraction, that can preserve the range, fuel weight, operating empty weight, and payload weight of the conventional aircraft. Current and future power system performance is compared to the required performance to determine the potential benefit.
Document ID
20170006220
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Jansen, Ralph H.
(NASA Glenn Research Center Cleveland, OH United States)
Duffy, Kirsten P.
(Toledo Univ. OH, United States)
Brown, Gerald V.
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
July 10, 2017
Publication Date
July 10, 2017
Subject Category
Statistics And Probability
Aircraft Propulsion And Power
Report/Patent Number
E-19381
AIAA Paper 2017-4702
GRC-E-DAA-TN43444
Meeting Information
Meeting: AIAA Propulsion and Energy Forum 2017
Location: Atlanta, GA
Country: United States
Start Date: July 10, 2017
End Date: July 12, 2017
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 081876.02.03.05.02.03
CONTRACT_GRANT: NNC13BA10B
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
turbogenerator
hybrid propulsion
aircraft engines
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