US Patent 11912427 Thermal management system and method of use

An aircraft engine thermal management system includes a body having a coolant passage in thermal communication with an electronic device, wherein the body and the electronic device are located in a first portion of the aircraft. A generator is fluidically connected by a coolant path to the coolant passage wherein the generator is located in a second portion of the aircraft, with at least a portion of the coolant path is located within a cooling location having a lower average temperature than either the first portion or the second portion of the aircraft.