An operating method is provided during which a command is received to increase thrust generated by a propulsor rotor (26) from a first thrust level to a second thrust level. The propulsor rotor (26) is operatively coupled to an engine core (14) and an electric machine (66). The engine core (14) includes a flowpath (32), a compressor section (28), a combustor section (29) and a turbine section (30). The engine core (14) is operated in a transient state to increase power output from the engine core (14) to the propulsor rotor (26) from a first power level to a second power level in response to the command. The electric machine (66) is operated to boost the power output from the engine core (14) to the propulsor rotor (26) while the engine core (14) is operating in the transient state. A clearance control system (20) for the engine core (14) is operated based on the operation of the electric machine (66).
TURBINE ENGINE TIP CLEARANCE CONTROL UTILIZING ELECTRIC MACHINE
STEUERUNG DES SCHAUFELSPITZENSPIELS EINES TURBINENMOTORS UNTER VERWENDUNG EINER ELEKTRISCHEN MASCHINE
COMMANDE DE JEU D'EXTRÉMITÉ DE MOTEUR À TURBINE UTILISANT UNE MACHINE ÉLECTRIQUE
2025-06-18
Patent
Electronic Resource
English
Gas turbine engine turbine blade tip active clearance control system and method
European Patent Office | 2016
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