Aircraft Propulsion System with Electric Machine System Cooling Circuit
AssigneeRtx Corporation
InventorsThomas E. CLARK, Murat YAZICI
Life of this patent
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Abstract
An apparatus is provided for an aircraft. This apparatus includes a turbine engine, a first electric machine, a first controller, a second electric machine, a second controller and a first fluid circuit. The first electric machine is operatively coupled to the turbine engine. The first controller is configured to control operation of the first electric machine. The second electric machine is operatively coupled to the turbine engine. The second controller is configured to control operation of the second electric machine. The first fluid circuit is configured to circulate a first liquid to cool and/or lubricate the first electric machine, the first controller, the second electric machine and the second controller.
Claims20
An apparatus for an aircraft, comprising:
- a turbine engine;
- a first electric machine operatively coupled to the turbine engine;
- a first controller configured to control operation of the first electric machine;
- a second electric machine operatively coupled to the turbine engine;
- a second controller configured to control operation of the second electric machine;
- and
- a first fluid circuit configured to circulate a first liquid to cool and/or lubricate the first electric machine, the first controller, the second electric machine and the second controller.
An apparatus for an aircraft, comprising:
- an aircraft propulsion system including a propulsor rotor, an engine case, a first electric machine, a second electric machine, a first controller, a second controller, an electrical system and a first fluid circuit;
- the engine case radially next to and circumscribing the propulsor rotor;
- the first controller configured to electrically couple the first electric machine to the electrical system, the first controller further configured to control operation of the first electric machine;
- the second controller configured to electrically couple the second electric machine to the electrical system, the second controller further configured to control operation of the second electric machine;
- and
- the first fluid circuit configured to circulate a first liquid to service the first electric machine, the second electric machine, the first controller and the second controller.
An apparatus for an aircraft, comprising:
- a turbofan engine comprising an inner case and an outer case spaced radially outboard from the inner case;
- a first electric machine arranged with the inner case;
- a first controller configured to control operation of the first electric machine, the first controller arranged with the outer case;
- a second electric machine arranged with the inner case;
- a second controller configured to control operation of the second electric machine, the second controller arranged with the outer case;
- and
- a first fluid circuit configured to circulate a first liquid to service the first electric machine, the first controller, the second electric machine and the second controller.
Dependencies are inferred from the claim text.