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Advanced supersonic technology propulsion system studyThis study had the objectives of determining the most promising conventional and variable cycle engine types; the effect of design cruise Mach number (2.2, 2.7 and 3.2) on a commercial supersonic transport; effect of advanced engine technology on the choice of engine cycle; and effect of utilizing hydrogen as the engine fuel. The technology required for the engines was defined, and the levels of development to ensure availability of this technology in advanced aircraft propulsion systems were assessed. No clearcut best conventional or variable cycle engine was identified. The dry bypass turbojet and the duct burning turbofans were initially selected as the best conventional engines, but later results, utilizing augmentation at takeoff, added the mixed-flow augmented turbofan as a promising contender. The modulating air flow, three-rotor variable cycle engine identified the performance features desired from VCE concepts (elimination of inlet drag and reduction in afterbody drag), but was a very heavy and complex engine.
Document ID
19740023161
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Szeliga, R. (General Electric Co. Cincinnati, OH, United States)
Allan, R. D. (General Electric Co. Cincinnati, OH, United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-CR-143634
R74AEG330
Accession Number
74N31274
Funding Number(s)
CONTRACT_GRANT: NAS3-16950
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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