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Advanced core technology - Key to subsonic propulsion benefitsA study was conducted to identify the potential performance benefits and key technology drivers associated with advanced cores for subsonic high bypass turbofan engines. Investigated first were the individual sensitivities of varying compressor efficiency, pressure ratio and bleed (turbine cooling); combustor pressure recovery; and turbine efficiency and inlet temperature on thermal efficiency and core specific power output. Then, engine cycle and mission performance benefits were determined for systems incorporating all potentially achievable technology advancements. The individual thermodynamic sensitivities are shown over a range of turbine temperatures (at cruise) from 2900 to 3500 R and for both constant (current technology) and optimum (maximum thermal efficiency) overall pressure ratios. It is seen that no single parameter alone will provide a large increase in core thermal efficiency, which is the thermodynamic parameter of most concern for transport propulsion. However, when all potentially achievable advancements are considered, there occurs a synergism that produces significant cycle and mission performance benefits. The nature of these benefits are presented along with the technology challenges.
Document ID
19900036835
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Glassman, Arthur J.
(NASA Lewis Research Center Cleveland, OH, United States)
Snyder, Christopher A.
(NASA Lewis Research Center Cleveland, OH, United States)
Knip, Gerald, Jr.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 14, 2013
Publication Date
June 1, 1989
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
ASME PAPER 89-GT-241
Accession Number
90A23890
Distribution Limits
Public
Copyright
Other

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