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Cooling of Electric Motors Used for Propulsion on SCEPTORNASA is developing a suite of hybrid-electric propulsion technologies for aircraft. These technologies have the benefit of lower emissions, diminished noise, increased efficiency, and reduced fuel burn. These will provide lower operating costs for aircraft operators. Replacing internal combustion engines with distributed electric propulsion is a keystone of this technology suite, but presents many new problems to aircraft system designers. One of the problems is how to cool these electric motors without adding significant aerodynamic drag, cooling system weight or fan power. This paper discusses the options evaluated for cooling the motors on SCEPTOR (Scalable Convergent Electric Propulsion Technology and Operations Research): a project that will demonstrate Distributed Electric Propulsion technology in flight. Options for external and internal cooling, inlet and exhaust locations, ducting and adjustable cowling, and axial and centrifugal fans were evaluated. The final design was based on a trade between effectiveness, simplicity, robustness, mass and performance over a range of ground and flight operation environments.
Document ID
20170004363
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Christie, Robert J.
(NASA Glenn Research Center Cleveland, OH United States)
Dubois, Arthur
(Joby Aviation, Inc. Santa Cruz, CA, United States)
Derlaga, Joseph M.
(NASA Langley Research Center Hampton, VA United States)
Date Acquired
May 4, 2017
Publication Date
April 1, 2017
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-19259
NASA/TM-2017-219134
GRC-E-DAA-TN33041
Funding Number(s)
WBS: WBS 533127.02.15.03.02
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Propulsion
Aircraft
Electric/Power
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