An aircraft power generation system having an electrical power generator configured to be driven by a gas turbine engine of the aircraft is provided. The electrical power generator is further configured to be electrically coupled to one or more electrical loads of the aircraft, the electrical power generator being cooled by a coolant sub-system. The cooling performance of the coolant sub-system is affected by the operation of the gas turbine engine. The aircraft power generation system further has a control sub-system configured to dynamically control the electrical output power capability of the generator in accordance with the cooling performance of the coolant sub-system.
Aircraft Power Generation System
2021-08-05
Patent
Electronic Resource
English