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A thermal management system for a gas turbine powerplant with an engine oil line and an engine fuel line incorporates a heat transfer control module that includes a reversible heat pump with a heat pump compressor for circulating working fluid in forward and reverse directions through a working flui

A thermal management system for a gas turbine powerplant with an engine oil line and an engine fuel line incorporates a heat transfer control module that includes a reversible heat pump with a heat pump compressor for circulating working fluid in forward and reverse directions through a working fluid line of the heat pump. The heat control module also includes a first heat exchanger having a heat exchange path for the working fluid between the compressor and a heat pump expansion valve and another heat exchange path for the engine oil. A second heat exchanger has a heat exchange path for the working fluid between the compressor and the expansion valve and another heat exchange path for the engine fuel. The heat pump can be operated in forward or reverse directions depending on whether heat is to be transferred from the engine oil or the fuel to the heat pump working fluid. In another embodiment an engine oil reservoir located between the first heat exchanger and the engine collects the oil before it is introduced to the engine and thus acts as a heat capacitor for the system.

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1. A thermal management system for a gas turbine powerplant having a first supply line for introducing a first operating fluid to a first powerplant subsystem and a second supply line for introducing a second operating fluid to a first a second powerplant subsystem, the thermal management system inc

1. A thermal management system for a gas turbine powerplant having a first supply line for introducing a first operating fluid to a first powerplant subsystem and a second supply line for introducing a second operating fluid to a first a second powerplant subsystem, the thermal management system including a heat transfer control module comprising: a reversible heat pump including a working fluid line having therein a heat pump compressor for circulating working fluid in forward and reverse directions through said fluid line and an expansion valve for expanding working fluid passing therethrough;a first heat exchanger having a first heat exchange path for the working fluid between said compressor and said expansion valve and a second heat exchange path included in the first supply line, wherein said first and second heat exchange paths permit heat to he exchanged between fluids therein; anda second heat exchanger having a first heat exchange path for the working fluid between said compressor and said expansion valve and a second heat exchange path included in the second supply line, wherein said first and second heat exchange paths permit heat to be exchanged between fluids therein. 2. A system as in claim 1, wherein the first powerplant subsystem comprises a powerplant fuel system and the second powerplant subsystem comprises a powerplant lubrication system. 3. A thermal management system as in claim 1, wherein: said first supply line comprises an oil line for introducing lubricating oil to an inlet of said second beat exchange path of said first heat exchanger and to the powerplant from an outlet of said second heat exchange path of said first heat exchanger, the lubricating oil being re-introduced to said inlet from the powerplant;an oil reservoir for collecting the lubricating oil before introduction to the powerplant is disposed in said oil line between said first heat exchanger and the powerplant; andsaid second supply line comprises a fuel line for introducing powerplant fuel to an inlet of said second heat exchange path of said second heat exchanger and to a powerplant combustor from an outlet of said second heat exchange path of said second heat exchanger. 4. A system as in claim 1, wherein said first subsystem comprises a powerplant main lubrication system and said second subsystem comprises a powerplant gearbox lubrication system. 5. A thermal management system for a gas turbine powerplant, the system comprising: a first heat transfer control module including (a) a first reversible heat pump including a working fluid line having therein a heat pump compressor for circulating working fluid in forward and reverse directions through said fluid line and an expansion valve for expanding working fluid passing therethrough, (b) a first heat exchanger having a first heat exchange path for the working fluid between said compressor and said expansion valve and a second heat exchange path included in a first supply line for a powerplant operating fluid, wherein said first and second heat exchange paths permit heat to be exchanged between fluids therein, and (c) a second heat exchanger having a first heat exchange path for the working fluid between said compressor and said expansion valve and a second heat exchange path included in a second supply line for a powerplant operating fluid, wherein said first and second heat exchange paths permit heat to be exchanged between fluids therein; anda second heat transfer control modulo including (a) a reversible heat pump including a working fluid line having therein a heat pump compressor for circulating working fluid in forward and reverse directions through said fluid line and an expansion valve for expanding working fluid passing therethrough, (b) a first heat exchanger having a first heat exchange path for the working fluid between said compressor and said expansion valve and a second heat exchange path included in a third supply line for a powerplant operating fluid, wherein said first and second heat exchange paths permit heat to be exchanged between fluids therein, and (c) a second heat exchanger having a first heat exchange path for the working fluid between said compressor and said expansion valve and a second heat exchange path included in a fourth supply line for a powerplant operating fluid, wherein said first and second heat exchange paths permit heat to be exchanged between fluids therein. 6. A system as in claim 5 for use with a gas turbine engine mounted on an aircraft, wherein the first, second, third, and fourth operating fluids are selected from the group comprising: (a) a fuel for the engine, (b) a lubricant for the engine, (c) a coolant for the aircraft, and (d) a hydraulic fluid for the aircraft. 7. A system as in claim 6, wherein the first operating fluid comprises an engine fuel, the second operating fluid comprises an engine lubricant within a main engine lubrication system, the third operating fluid comprises an engine lubricant within the main engine lubrication system, and the fourth operating fluid comprises lubricant within a gearbox lubrication system. 8. A method for controlling the temperature of first and second operating fluids used in a as turbine engine mounted on an aircraft with a first supply line for the first operating fluid, a second supply line for the second operating fluid, and a heat transfer control module including (1) a reversible heat pump including a working fluid line having therein a heat pump compressor for circulating working fluid in forward and reverse directions through said fluid line and an expansion valve for expanding working fluid passing therethrough, (2) a first heat exchanger having a first heat exchange path for the working fluid between said compressor and said expansion valve and a second heat exchange path included in the first supply line, wherein said first and second heat exchange paths permit heat to be exchanged between fluids therein, and (3) a second heat exchanger having a first heat exchange path for the working fluid between said compressor and said expansion valve and a second heat exchange path included in the second supply line, wherein said first and second heat exchange paths permit heat to be exchanged between fluids therein, the method comprising selectively operating said heat pump in one of a forward direction and a reverse direction, wherein: operation in said forward direction pumps the working fluid to said second heat exchanger, said expansion valve, said first heat exchanger, and back to said heat pump compressor, for transferring heat from the first operating fluid to the working fluid in said first heat exchanger and from the working fluid to the second operating fluid in said second heat exchanger; andoperation in said reverse direction pumps the working fluid to said first heat exchanger, said expansion valve, said second heat exchanger, and back to said heat pump compressor, for transferring heat from the working fluid to the first operating fluid in said first heat exchanger and from the second operating fluid to the working fluid in said second heat exchanger. 9. A method as in claim 8, further comprising: operating said heat pump in said forward direction if the temperature of the first operating fluid exceeds a predetermined value; andoperating said heat pump in said reverse direction if the temperature of the second operating fluid exceeds a predetermined value. 10. A method as in claim 9, further comprising controlling heat exchange between fluids in said heat exchangers by modulating the operation of said heat pump. 11. A method as in claim 10, further comprising using operational information from aircraft and engine subsystems to control said heat pump operation. 12. A method as in claim 11, wherein the operational information includes at least one of aircraft mission data, fuel quantity, and fuel temperature. 13. A method as in claim 11, wherein the operational information includes temperature information provided by at least one temperature sensor in the engine or the aircraft. 14. A thermal management system for a gas turbine engine mounted on an aircraft, the system having a first supply line for introducing an engine fluid used for operation of the engine to an engine subsystem and a second supply line for introducing an aircraft fluid to an aircraft subsystem, the thermal management system including a heat transfer control module comprising: a reversible heat pump including a working fluid line having therein a heat pump compressor for circulating working fluid in forward and reverse directions through said fluid line and an expansion valve for expanding working fluid passing therethrough;a first heat exchanger having a first heat exchange path for the working fluid between said compressor and said expansion valve and a second heat exchange path included in the first supply line, wherein said first and second heat exchange paths permit heat to be exchanged between fluids therein; anda second heat exchanger having a first heat exchange path for the working fluid between said compressor and said expansion valve and a second heat exchange path included in the second supply line, wherein said first and second heat exchange paths permit heat to be exchanged between fluids therein. 15. A thermal management system as in claim 14, wherein: said first supply line introduces the engine fluid to an inlet of said second heat exchange path of one of said first and second heat exchangers and to said engine from an outlet of said second heat exchange path; andsaid second supply line introduces the aircraft fluid to an inlet of said second heat exchange path of the other of said first and second heat exchangers and to the aircraft from an outlet of said second heat exchange path. 16. A thermal management system as in claim 15, wherein: the engine fluid is re-introduced from the engine to said inlet of said second heat exchange path of said one of said first and second heat exchangers; andthe aircraft fluid is re-introduced from the aircraft to said inlet of said second heat exchange path of said other of said first and second heat exchangers. 17. A thermal management system as in claim 15, wherein: the engine fluid comprises a lubricant for the engine; andthe aircraft fluid comprises at least one of a lubricant for the aircraft, a coolant, and hydraulic fluid.