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.
ACTIVE TURBINE ENGINE TIP CLEARANCE CONTROL UTILIZING ELECTRIC MACHINE
AKTIVE STEUERUNG DES SCHAUFELSPITZENSPIELS EINES TURBINENMOTORS UNTER VERWENDUNG EINER ELEKTRISCHEN MASCHINE
COMMANDE DE JEU D'EXTRÉMITÉ DE MOTEUR À TURBINE UTILISANT UNE MACHINE ÉLECTRIQUE
02.07.2025
Patent
Elektronische Ressource
Englisch
TURBINE ENGINE TIP CLEARANCE CONTROL UTILIZING ELECTRIC MACHINE
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