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Advanced supersonic propulsion study, phase 2A continuation of the NASA/P and WA study to evaluate various types of propulsion systems for advanced commercial supersonic transports has resulted in the identification of two very promising engine concepts. They are the Variable Stream Control Engine which provides independent temperature and velocity control for two coannular exhaust streams, and a derivative of this engine, a Variable Cycle Engine that employs a rear flow-inverter valve to vary the bypass ratio of the cycle. Both concepts are based on advanced engine technology and have the potential for significant improvements in jet noise, exhaust emissions and economic characteristics relative to current technology supersonic engines. Extensive research and technology programs are required in several critical areas that are unique to these supersonic Variable Cycle Engines to realize these potential improvements. Parametric cycle and integration studies of conventional and Variable Cycle Engines are reviewed, features of the two most promising engine concepts are described, and critical technology requirements and required programs are summarized.
Document ID
19760006012
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Howlett, R. A.
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Date Acquired
September 3, 2013
Publication Date
September 1, 1975
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-134904
PWA-5312
Accession Number
76N13100
Funding Number(s)
CONTRACT_GRANT: NAS3-16948
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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