Thermal management system and method of use
Thermal management system and method of use
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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.
Document information
Thermal management system and method of use
2024-02-27
Patent
Electronic Resource
English
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