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)


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    Title :

    Potential technology improvements for CF6 turbofan


    Additional title:

    Aircr Eng


    Contributors:

    Published in:

    Publication date :

    1969


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Potential technology improvements for CF6 turbofan

    Payzer, R.J. | Engineering Index Backfile | 1968


    Potential Technology Improvements for the CF6 Turbofan

    Payzer, R.J. | Emerald Group Publishing | 1969


    POTENTIAL TECHNOLOGY IMPROVEMENTS FOR THE CF6 TURBOFAN

    PAYZER, R. J. | SAE Technical Papers | 1968