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Contingency power concepts for helicopter turboshaft engineTwin helicopter engines are often sized by power requirement of safe mission completion after the failure of one of the two engines. This study was undertaken for NASA Lewis by General Electric Co. to evaluate the merits of special design features to provide a 2-1/2 minute Contingency Power rating, permitting an engine size reduction. The merits of water injection, cooling flow modulation, throttle push and an auxiliary power plant were evaluated using military life cycle cost (LCC) and commercial helicopter direct operating cost (DOC) merit factors in a rubber engine/rubber aircraft scenario.
Document ID
19850049854
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hirschkron, R.
(General Electric Co. Lynn, MA, United States)
Davis, R. H.
(General Electric Co. Lynn, MA, United States)
Goldstein, D. N.
(General Electric Co. Lynn, MA, United States)
Haynes, J. F.
(General Electric Co. Lynn, MA, United States)
Gauntner, J. W.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1984
Subject Category
Aircraft Propulsion And Power
Meeting Information
Meeting: American Helicopter Society, Annual Forum
Location: Arlington, VA
Start Date: May 16, 1984
End Date: May 18, 1984
Sponsors: American Helicopter Society
Accession Number
85A32005
Funding Number(s)
CONTRACT_GRANT: NAS3-23705
Distribution Limits
Public
Copyright
Other

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