Patent ID: 11912427
Assignee: HAMILTON SUNDSTRAND CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC B  F  Y | IPC B  F

Claim 0:
1. An aircraft engine thermal management system comprising:
a coolant path extending between a belly fairing and an engine nacelle of an aircraft;
a generator power electronics module in thermal communication with a body, the body having a coolant passage, fluidically connected to the coolant path, wherein the generator power electronics module and the body are located in the belly fairing of the aircraft;
a generator fluidically connected to the coolant path wherein the generator is located in the engine nacelle, and wherein at least a portion of the coolant path is located within a wing of the aircraft, having a lower average temperature than either the belly fairing or engine nacelle; and
a heat exchanger fluidically connected to the body and fluidically connected to the generator by way of the coolant path.