Dual rotor, high bypass ratio turbofan engine is designed for airline operation of advanced trijet aircraft entering service in 1971; engine incorporates variable stator, high-pressure ratio compressor, annular combustor, aircooled core engine turbine and coaxial front fan driven by five-stage low-pressure turbine; bypass ratio is 6.2 and is optimized for Mach .85 cruise; fan is 86.4 in. in diam; takeoff thrust is 40,000 lb with thrust-to-weight ratio of 5.5; emphasis during design of engine was given to durability, reliability, maintainability, performance, low operating cost and low noise level; status of CF6 development program and potential improvements, performance and testing. (See also SAE -- Paper 680691 for meeting Oct 7-11 1968 11 p) (12805)
Potential technology improvements for CF6 turbofan
Aircr Eng
Aircraft Engineering ; 41 , n 2
1969
5 pages
Aufsatz (Zeitschrift)
Englisch
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Potential technology improvements for CF6 turbofan
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