THE effect of higher turbine inlet temperature on the performance of an aircraft gas turbine engine can be quite dramatic. It can be used to increase the exhaust velocity of a dry turbojet to providea higher specific thrust; to increase the bypass ratio of a turbofan engine to improve its propulsive efficiency; to optimize the thermodynamic cycle at a higher pressure ratio to improve its specific fuel consumption; to reduce the amount of afterburner fuel flow in an augmented turbojet to improve its specific fuel consumption, or to increase the work output of a turboshaft engine. If the thrust or power of the engine is held constant, a size, cost and/or weight reduction can result. If the size of the engine is held constant growth capability can be provided.


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    Titel :

    High Temperature Turbine Design Considerations


    Untertitel :

    A discussion of the major technological developments which have led to the trend of using higher temperatures in modern gas turbine aero engines from a paper first presented at an AGARD conference in September


    Beteiligte:
    Suciu, S.N. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.12.1970


    Format / Umfang :

    8 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    High Temperature Turbine Design Considerations

    Suciu, S. N. | SAE Technical Papers | 1971




    DESIGN CONSIDERATIONS FOR A HELICOPTER GAS TURBINE POWERPLANT

    KOETTING, J. L. | SAE Technical Papers | 1953