Patent ID: 11885229
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  H  B  Y | IPC B  F  H

Claim 12:
13. An electric propulsion system for an aircraft, the system comprising:
an electric motor comprising a stator, a rotor, and a drive shaft operably coupled to the rotor;
a motor cooling conduit that defines a pathway for conveying a cooling fluid through or around at least a portion of the electric motor, the motor cooling conduit having a thermally conductive relationship with the at least a portion of the electric motor;
a casing assembly that circumferentially surrounds at least a portion of the electric motor, the casing assembly comprising:
a motor casing;
a nacelle; and
a casing assembly conduit integrally formed within at least a portion of the casing assembly wherein the casing assembly conduit and the at least a portion of the casing assembly define a monolithic, single-piece construction, the casing assembly conduit defining a pathway for conveying the cooling fluid through the at least a portion of the casing assembly, and the casing assembly conduit having a thermally conductive relationship with an external surface of the casing assembly; and

a pump or compressor operably coupled to the drive shaft, the pump or compressor being operably configured to circulate cooling fluid through the motor cooling conduit and the casing assembly conduit,
wherein, during operation, airflow passes over the external surface of the casing assembly, thereby transferring heat to the airflow from the cooling fluid circulating through the casing assembly conduit by the thermally conductive relationship with the external surface of the casing assembly.