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.
HYBRID GAS TURBINE ENGINE STARTING CONTROL
STARTSTEUERUNG EINES HYBRIDGASTURBINENMOTORS
COMMANDE DE DÉMARRAGE DE MOTEUR DE TURBINE À GAZ HYBRIDE
2025-03-26
Patent
Electronic Resource
English
Hybrid aircraft turbine engine starting system and method
European Patent Office | 2020
|HYBRID AIRCRAFT TURBINE ENGINE STARTING SYSTEM AND METHOD
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|Turbine technology for engine starting
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