A gas turbine engine (20) typically includes a fan section (42), a compressor section (24), a combustor section (26) and a turbine section (46). A speed reduction device (48) such as an epicyclical gear assembly may be utilized to drive the fan section (42) such that the fan section (42) may rotate at a speed different than the turbine section (46) so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft (40) driven by one of the turbine sections (46) provides an input to the epicyclical gear assembly that drives the fan section (42) at a speed different than the turbine section (46) such that both the turbine section (46) and the fan section (42) can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.


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    Titel :

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE


    Weitere Titelangaben:

    ARCHITEKTUR EINES GASTURBINENMOTORS MIT GETRIEBETURBOLÜFTER
    ARCHITECTURE DE MOTEUR DE TURBINE À GAZ ET TURBORÉACTEUR À ENGRENAGES


    Beteiligte:

    Erscheinungsdatum :

    01.04.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B63H Schiffsantrieb oder Steuerung der Schiffe , MARINE PROPULSION OR STEERING / B64C AEROPLANES , Flugzeuge / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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