Comparison of turbine bypass and mixed flow turbofan engines for a high-speed civil transportA comparison of the turbine bypass engine and the mixed flow turbofan for a Mach 2.4 cruise application is presented. A parametric assessment is conducted for each cycle. Parameters that are investigated for the turbine bypass engine include design bypass, combustor exit temperature, and overall pressure ratio. Parameters that are investigated for the mixed flow turbofan include fan pressure ratio, mixer design pressure ratio, and combustor exit temperature. The engines are analyzed for a 5000-nautical-mile, all supersonic cruise mission to determine the aircraft takeoff gross weights. The effects of takeoff noise, cruise emissions, the addition of subsonic cruise legs, and constrained supersonic cruise altitudes are also evaluated.
Document ID
19910069428
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Seidel, Jonathan A. (NASA Lewis Research Center Cleveland, OH, United States)
Haller, William J. (NASA Lewis Research Center Cleveland, OH, United States)
Berton, Jeffrey J. (NASA Lewis Research Center Cleveland, OH, United States)