AIRCRAFT PROPULSION SYSTEM THERMAL MANAGEMENT SYSTEM

A propulsion system for an aircraft (20) is provided that includes a thermal engine (30), an electrical power motive system (28), a propulsion unit (40), and a thermal management system (38). The electrical power motive system (28) has an electric motor (46). The thermal management system (38) includes a first heat exchanger (56), and is configured to cycle a flow of lubricant (64) into and out of the thermal engine (30) and into and out of the first heat exchanger (56) in a first loop (60), and is configured to cycle a flow of coolant (66) into and out of thermal engagement with the electrical power motive system (28) and into and out of the first heat exchanger (56) in a second loop (62). The first heat exchanger (56) is configured to permit heat transfer between the flow of lubricant (64) and the flow of coolant (66) to occur within the first heat exchanger (56).