A system (100A, 100B) includes a gas turbine engine (20) having a low speed spool (30), a high speed spool (32), and a combustor (56). The system also includes a low spool motor (12A) configured to augment rotational power of the low speed spool. The system further includes a controller (256) configured to cause fuel flow. The controller is operable to control the low spool motor (12A) to drive rotation of the low speed spool (30) responsive to a thrust command (270) while the controller does not command fuel flow to the combustor.


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    Title :

    HYBRID GAS TURBINE ENGINE STARTING CONTROL


    Additional title:

    STARTSTEUERUNG EINES HYBRIDGASTURBINENMOTORS
    COMMANDE DE DÉMARRAGE DE MOTEUR DE TURBINE À GAZ HYBRIDE


    Contributors:

    Publication date :

    2025-03-26


    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 / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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