A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxy
A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.
대표청구항▼
1. A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine, the system comprising: a first engine system comprising an oil comprising an ionic liquid or an ionic liquid blend for heat transfer, the oil having a temperature limit between about 500 degrees Fahrenh
1. A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine, the system comprising: a first engine system comprising an oil comprising an ionic liquid or an ionic liquid blend for heat transfer, the oil having a temperature limit between about 500 degrees Fahrenheit (F) and about 550 degrees F.; and a fuel system, the fuel system comprising a deoxygenation unit for deoxygenating a fuel in the fuel system; a fuel-oil heat exchanger located downstream of the deoxygenation unit, the fuel oil heat exchanger in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system; a supplemental fuel pump located downstream of the fuel-oil neat exchanger for increasing the pressure of the fuel, and a fuel metering unit comprising a fuel bypass valve, the fuel metering unit located downstream of the supplemental fuel pump and used for splitting 100% of the heated and deoxygenated fuel for delivery to one of the combustor and the fuel bypass valve, wherein the bypass valve is positioned upstream of the deoxygenation unit such that a first bypass conduit connects said bypass valve and said deoxygenation unit for sending a first portion of the heated and deoxygenated fuel to the deoxygenation unit and wherein the bypass valve is upstream of the boost pump such that a second bypass conduit connects the bypass valve and the boost pump for sending a second portion of the heated and deoxygenated fuel to the boost pump; wherein the first engine system includes an air-oil heat exchanger located immediately upstream of the fuel-oil heat exchanger. 2. The system of claim 1, wherein the first engine system is a main lubrication oil system of the gas turbine engine, the main lubrication oil system recirculating the oil utilized for heat transfer. 3. The system of claim 2, further comprising a second engine system utilizing an oil for heat transfer, wherein the fuel-oil heat exchanger of the fuel system is a first fuel-oil heat exchanger, wherein the fuel system further comprises a second fuel-oil heat exchanger, wherein the second fuel-oil heat exchanger is in thermal communication with the oil from the second engine system and the fuel from the fuel system for removing heat from the second engine system. 4. The system of claim 3, wherein the main lubrication system is in selective thermal communication with the second engine system. 5. The system of claim 1, wherein the fuel system comprises a fuel tank and an outlet line extending to a combustor of the gas turbine engine, wherein the fuel in the fuel system is configured to receive a total amount of heat from one or more heat exchangers located between the fuel tank and the outlet line, and wherein each of the one or more heat exchangers are configured as fuel-oil heat exchangers. 6. The system of claim 1, wherein during operation of the gas turbine engine the fuel-oil heat exchanger defines a fuel inlet temperature, a fuel outlet temperature, an oil inlet temperature, and an oil outlet temperature, wherein the fuel inlet temperature is up to about 200 degrees F., wherein the fuel outlet temperature is between about 450 degrees F. and about 600 degrees F., wherein the oil inlet temperature is between about 450 degrees F. and about 600 degrees F., and wherein the oil outlet temperature is up to about 250 degrees F. 7. A system for managing thermal transfer, the system comprising: a gas turbine engine; a main lubrication oil system operable with the gas turbine engine for providing the gas turbine engine with a lubrication oil comprising an ionic liquid or an ionic liquid blend, the lubrication oil having a temperature limit between about 500 degrees F. and 550 degrees F.; and a fuel system, the fuel system comprising a deoxygenation unit for deoxygenating a fuel in the fuel system; and a fuel-oil heat exchanger located downstream of the deoxygenation unit in thermal communication with the lubrication oil in the main lubrication oil system, the fuel-oil heat exchanger, during operation of the gas turbine engine, defining a fuel inlet temperature, a fuel outlet temperature, an oil inlet temperature, and an oil outlet temperature, the fuel inlet temperature being up to about 200 degrees F., the fuel outlet temperature being between about 450 degrees F. and about 600 degrees F., the oil inlet temperature being between about 450 degrees F. and about 600 degrees F., and the oil outlet temperature being up to about 250 degrees F.; a supplemental fuel pump located downstream of the fuel-oil heat exchanger for increasing the pressure of the fuel, and a fuel metering unit comprising a fuel bypass valve, the fuel metering unit located downstream of the supplemental fuel pump and used for splitting 100% of the heated and deoxygenated fuel for delivery to one of the combustor and the fuel bypass valve, wherein the bypass valve is positioned upstream of the deoxygenation unit such that a first bypass conduit connects said bypass valve and said deoxygenation unit for sending a first portion of the heated and deoxygenated fuel to the deoxygenation unit and wherein the bypass valve is upstream of the boost pump such that a second bypass conduit connects the bypass valve and the boost pump for sending a second portion of the heated and deoxygenated fuel to the boost pump; wherein the main lubrication oil system includes an air-oil heat exchanger located upstream of the fuel-oil heat exchanger. 8. The system of claim 7, further comprising a second engine system utilizing an oil for heat transfer, wherein the fuel-oil heat exchanger of the fuel system is a first fuel-oil heat exchanger, wherein the fuel system further comprises a second fuel-oil heat exchanger, wherein the second fuel-oil heat exchanger is in thermal communication with the oil from the second engine system and the fuel from the fuel system for removing heat from the second engine system. 9. The system of claim 8, wherein the main lubrication oil system is in selective thermal communication with the second engine system. 10. The system of claim 7, wherein the fuel system comprises a fuel tank and an outlet line extending to a combustor of the gas turbine engine, wherein the fuel in the fuel system is configured to receive a total amount of heat from one or more heat exchangers located between the fuel tank and the outlet line, and wherein each of the one or more heat exchangers are configured as fuel-oil heat exchangers. 11. The system of claim 1, wherein the oil utilized by the first engine system defines a pour temperature between zero degrees F. and about minus 40 degrees F. 12. The system of claim 7, wherein the oil utilized by the first engine system defines a pour temperature between zero degrees F. and about minus 40 degrees F. 13. A system for managing thermal transfer, the system comprising: a gas turbine engine comprising a combustor; a main lubrication oil system operable with the gas turbine engine and utilizing an oil for heat transfer, and a fuel system for providing fuel to the combustor of the gas turbine engine, the fuel system comprising a fuel tank; a fuel pump located downstream of the fuel tank for generating a flow of fuel; a boost pump located downstream of the fuel pump for boosting the pressure of said flow of fuel; a deoxygenation unit located downstream of the fuel pump for deoxygenating a fuel in the fuel system; a first fuel-oil heat exchanger located downstream of the deoxygenation unit, the first fuel-oil heat exchanger in thermal communication with the oil in the main lubrication oil system and the fuel in the fuel system for transferring heat from the oil in the main lubrication oil system to the fuel in the fuel system; a supplemental fuel pump located downstream of the first fuel-oil heat exchanger for increasing the pressure of said heated and deoxygenated fuel, and a fuel metering unit comprising a fuel bypass valve, said fuel metering unit located downstream of said supplemental fuel pump and used for splitting 100% of the heated and deoxygenated fuel for delivery to one of said combustor and said fuel bypass valve, wherein said bypass valve is positioned upstream of said deoxygenation unit such that a first bypass conduit connects said bypass valve and said deoxygenation unit for sending a first portion of the heated and deoxygenated fuel to said deoxygenation unit and wherein said bypass valve is upstream of said boost pump such that a second bypass conduit connects said bypass valve and said boost pump for sending a second portion of the heated and deoxygenated fuel to said boost pump, and wherein the boost pump is located immediately upstream of the deoxygenation unit. 14. The system of claim 13, further comprising: a fuel filter located in said fuel system downstream of said supplemental fuel pump; and a second fuel-oil heat exchanger in series flow communication with the first fuel-oil heat exchanger,wherein the deoxygenation unit is upstream of both the first fuel-oil heat exchanger and the second fuel-oil heat exchanger, andwherein the fuel pump is upstream of the boost pump. 15. The system of claim 1 further comprising a boost pump located downstream of the fuel pump for boosting the pressure of said flow of fuel, wherein the boost pump is located immediately upstream of the deoxygenation unit. 16. The system of claim 7 further comprising a boost pump located downstream of the fuel pump for boosting the pressure of said flow of fuel, wherein the boost pump is located immediately upstream of the deoxygenation unit. 17. The system of claim 3 further comprising a second air-oil heat exchanger. 18. The system of claim 17, wherein the second air-oil cooler is immediately upstream of the second fuel-oil heat exchanger.
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