A method is provided for a hybrid electric propulsion system (12) that includes a gas turbine engine (14) and an electric motor (16) configured to assist the gas turbine engine (14) by rotating a first shaft (22, 24) of the gas turbine engine (14). The method includes receiving a throttle command, and determining, based on an amount of electric power available to the electric motor (16), a power allocation between the gas turbine engine (14) and the electric motor (16) for an acceleration period during which a rotational speed of the first shaft (22, 24) is accelerated to implement the throttle command. The method also includes determining a target clearance between a tip (62T) of a rotor blade (62) and a case structure (64) for the acceleration period and, during the acceleration period, implementing the power allocation and operating an active clearance control system to establish the target clearance. A system for an aircraft and a method for a hybrid electric propulsion system (12) are also disclosed.


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    Titel :

    ACTIVE TURBINE ENGINE TIP CLEARANCE CONTROL UTILIZING ELECTRIC MACHINE


    Weitere Titelangaben:

    AKTIVE STEUERUNG DES SCHAUFELSPITZENSPIELS EINES TURBINENMOTORS UNTER VERWENDUNG EINER ELEKTRISCHEN MASCHINE
    COMMANDE DE JEU D'EXTRÉMITÉ DE MOTEUR À TURBINE UTILISANT UNE MACHINE ÉLECTRIQUE


    Beteiligte:
    PHILBRICK GRAHAM R (Autor:in) / COLLOPY GARY (Autor:in) / VIRTUE JR JOHN P (Autor:in)

    Erscheinungsdatum :

    02.07.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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