An aircraft power system includes an internal combustion core engine (22) where an inlet airflow (26) is mixed with a fuel and ignited to generate shaft power and a primary gas flow (34), a boost combustor (36) where a portion of the primary gas flow (34) from the core engine (22) is combined with fuel and ignited to generate a boosted gas flow (38), and a drive turbine (40) that includes a drive output shaft (42) wherein the boosted gas flow (38) is expanded to generate shaft power.


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    Title :

    COMPOUNDED TURBO POWER UNIT WITH BOOST COMBUSTOR


    Additional title:

    ZUSAMMENGESETZTE TURBOTRIEBWERKEINHEIT MIT VERSTÄRKUNGSBRENNKAMMER
    UNITÉ DE TURBO-PUISSANCE COMPOSÉE AVEC CHAMBRE DE COMBUSTION DE SURALIMENTATION


    Contributors:

    Publication date :

    2024-05-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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