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 Aircraft Eng v 41 n 2 Feb 1969 p 20-4) (12805)
Potential technology improvements for CF6 turbofan
SAE Paper
SAE Meeting ; 1968 General electric
SAE Papers ; 41 , n 2
1968
11 pages
Conference paper
English
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