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An aircraft fuel deoxygenation and tank inerting system includes an inert gas source, a fuel deoxygenation system, and an air/fuel heat exchanger. The inert gas source is configured to supply inert gas having an oxygen concentration of less than 3%. The fuel deoxygenation system is adapted to receiv

An aircraft fuel deoxygenation and tank inerting system includes an inert gas source, a fuel deoxygenation system, and an air/fuel heat exchanger. The inert gas source is configured to supply inert gas having an oxygen concentration of less than 3%. The fuel deoxygenation system is adapted to receive fuel from a fuel source and the inert gas from the inert gas source. The fuel deoxygenation system is configured to remove oxygen from the fuel and thereby generate and supply deoxygenated fuel and oxygen-rich purge gas. The air/fuel heat exchanger is adapted to receive compressed air from a compressed air source and the deoxygenated fuel from the fuel deoxygenation system. The air/fuel heat exchanger is configured to transfer heat from the compressed air to the deoxygenated fuel, to thereby supply cooled compressed air and heated deoxygenated fuel.

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1. An aircraft fuel deoxygenation and tank inerting system, comprising: an inert gas source configured to supply inert gas having an oxygen concentration of less than 3%;a fuel deoxygenation system adapted to receive fuel from a fuel source and the inert gas from the inert gas source, the fuel deoxy

1. An aircraft fuel deoxygenation and tank inerting system, comprising: an inert gas source configured to supply inert gas having an oxygen concentration of less than 3%;a fuel deoxygenation system adapted to receive fuel from a fuel source and the inert gas from the inert gas source, the fuel deoxygenation system configured to remove oxygen from the fuel and thereby generate and supply deoxygenated fuel and oxygen-rich purge gas; andan air/fuel heat exchanger adapted to receive compressed air from a compressed air source and the deoxygenated fuel from the fuel deoxygenation system, the air/fuel heat exchanger configured to transfer heat from the compressed air to the deoxygenated fuel, to thereby supply cooled compressed air and heated deoxygenated fuel,wherein the inert gas source comprises: a fuel tank inerting system, the fuel tank inerting system coupled to receive a portion of the cooled compressed air from the air/fuel heat exchanger and configured to generate inert gas having an oxygen concentration of greater than 3%; anda secondary purification system coupled to receive the inert gas having an oxygen concentration of greater than 3% from the fuel tank inerting system and configured to generate and supply the inert gas having an oxygen concentration of less than 3%. 2. The system of claim 1, wherein: the fuel tank inerting system comprises a fuel tank inerting membrane; andthe secondary purification system comprises a second inerting membrane. 3. The system of claim 1, wherein the fuel deoxygenation system comprises: a housing having a fuel inlet, a fuel outlet, a gas inlet, and a gas outlet, the fuel inlet adapted to receive the fuel from the fuel source, the gas inlet coupled to receive the inert gas from the inert gas source; anda disk rotationally mounted in the housing and coupled to receive a drive torque, the disk configured, upon receipt of the drive torque, to rotate and produce a thin film of fuel thereon. 4. The system of claim 3, wherein the fuel deoxygenation system further comprises a torque source coupled to the disk and configured to supply the drive torque thereto. 5. The system of claim 3, wherein the fuel deoxygenation system further comprises a plurality of disks rotationally mounted within the housing and coupled to receive the drive torque, each disk configured, upon receipt of the drive torque, to rotate and produce a thin film of fuel thereon. 6. The system of claim 3, wherein: the housing and the disk define a single stage;the fuel deoxygenation system further comprises a plurality of stages coupled in fluid-series; andgas and fuel flow in opposite directions across stages. 7. The system of claim 3, wherein: the fuel inlet is disposed and configured such that fuel is injected in a direction that is perpendicular to the disk; andthe fuel outlet is disposed adjacent an outer periphery of the disk. 8. The system of claim 3, further comprising a nozzle coupled to the fuel inlet and configured to produce an aerosol of fuel. 9. The system of claim 1, wherein the fuel deoxygenation system comprises: a contactor adapted to receive the fuel from the fuel source and the inert gas from the inert gas source, the contactor configured to mix the fuel and inert gas and supply a fuel/gas mixture;a separator in fluid communication with the contactor and coupled to receive the fuel/gas mixture therefrom, the separator configured to remove oxygen from the fuel and thereby generate and supply the deoxygenated fuel and the oxygen-rich purge gas;a fuel pressure control valve disposed upstream of the contactor and configured to control pressure of the fuel supplied thereto; anda gas pressure control valve disposed upstream of the contactor and configured to control pressure of the inert gas supplied thereto. 10. The system of claim 9, further comprising: a fuel back pressure control valve disposed downstream of the separator and configured to control pressure of the fuel supplied therefrom; anda gas pressure control valve disposed downstream of the separator and configured to control pressure of the purge gas supplied therefrom. 11. The system of claim 1, wherein the fuel deoxygenation system comprises: a contactor adapted to receive the fuel from the fuel source and the inert gas from the inert gas source, the contactor configured to mix the fuel and inert gas and supply a fuel/gas mixture;a nozzle disposed within the contactor and configured to produce an aerosol of fuel; anda separator in fluid communication with the contactor and coupled to receive the fuel/gas mixture therefrom, the separator configured to remove oxygen from the fuel and thereby generate and supply the deoxygenated fuel and the oxygen-rich purge gas. 12. An aircraft fuel deoxygenation and tank inerting system, comprising: an inert gas source configured to supply inert gas having an oxygen concentration of less than 3%;a fuel deoxygenation system adapted to receive fuel from a fuel source and the inert gas from the inert gas source, the fuel deoxygenation system configured to remove oxygen from the fuel and thereby generate and supply deoxygenated fuel and oxygen-rich purge gas; andan air/fuel heat exchanger adapted to receive compressed air from a compressed air source and the deoxygenated fuel from the fuel deoxygenation system, the air/fuel heat exchanger configured to transfer heat from the compressed air to the deoxygenated fuel, to thereby supply cooled compressed air and heated deoxygenated fuel,wherein the fuel deoxygenation system comprises: a housing having a fuel inlet, a fuel outlet, a gas inlet, and a gas outlet, the fuel inlet adapted to receive the fuel from the fuel source, the gas inlet coupled to receive the inert gas from the inert gas source; anda disk rotationally mounted in the housing and coupled to receive a drive torque, the disk configured, upon receipt of the drive torque, to rotate and produce a thin film of fuel thereon,wherein: the housing and the disk define a single stage;the fuel deoxygenation system further comprises a plurality of stages coupled in fluid-series; andgas and fuel flow in opposite directions across stages. 13. The system of claim 12, wherein the fuel deoxygenation system further comprises a torque source coupled to the disk and configured to supply the drive torque thereto. 14. The system of claim 12, wherein the fuel deoxygenation system further comprises a plurality of disks rotationally mounted within the housing and coupled to receive the drive torque, each disk configured, upon receipt of the drive torque, to rotate and produce a thin film of fuel thereon. 15. The system of claim 12, wherein: the fuel inlet is disposed and configured such that fuel is injected in a direction that is perpendicular to the disk; andthe fuel outlet is disposed adjacent an outer periphery of the disk. 16. The system of claim 3, further comprising a nozzle coupled to the fuel inlet and configured to produce an aerosol of fuel. 17. An aircraft fuel deoxygenation and tank inerting system, comprising: an inert gas source configured to supply inert gas having an oxygen concentration of less than 3%;a fuel deoxygenation system adapted to receive fuel from a fuel source and the inert gas from the inert gas source, the fuel deoxygenation system configured to remove oxygen from the fuel and thereby generate and supply deoxygenated fuel and oxygen-rich purge gas; andan air/fuel heat exchanger adapted to receive compressed air from a compressed air source and the deoxygenated fuel from the fuel deoxygenation system, the air/fuel heat exchanger configured to transfer heat from the compressed air to the deoxygenated fuel, to thereby supply cooled compressed air and heated deoxygenated fuel,wherein the fuel deoxygenation system comprises: a contactor adapted to receive the fuel from the fuel source and the inert gas from the inert gas source, the contactor configured to mix the fuel and inert gas and supply a fuel/gas mixture;a separator in fluid communication with the contactor and coupled to receive the fuel/gas mixture therefrom, the separator configured to remove oxygen from the fuel and thereby generate and supply the deoxygenated fuel and the oxygen-rich purge gas;a fuel pressure control valve disposed upstream of the contactor and configured to control pressure of the fuel supplied thereto; anda gas pressure control valve disposed upstream of the contactor and configured to control pressure of the inert gas supplied thereto. 18. The system of claim 17, further comprising: a fuel back pressure control valve disposed downstream of the separator and configured to control pressure of the fuel supplied therefrom; anda gas pressure control valve disposed downstream of the separator and configured to control pressure of the purge gas supplied therefrom. 19. An aircraft fuel deoxygenation and tank inerting system, comprising: an inert gas source configured to supply inert gas having an oxygen concentration of less than 3%;a fuel deoxygenation system adapted to receive fuel from a fuel source and the inert gas from the inert gas source, the fuel deoxygenation system configured to remove oxygen from the fuel and thereby generate and supply deoxygenated fuel and oxygen-rich purge gas; andan air/fuel heat exchanger adapted to receive compressed air from a compressed air source and the deoxygenated fuel from the fuel deoxygenation system, the air/fuel heat exchanger configured to transfer heat from the compressed air to the deoxygenated fuel, to thereby supply cooled compressed air and heated deoxygenated fuel,wherein the fuel deoxygenation system comprises: a contactor adapted to receive the fuel from the fuel source and the inert gas from the inert gas source, the contactor configured to mix the fuel and inert gas and supply a fuel/gas mixture;a nozzle disposed within the contactor and configured to produce an aerosol of fuel; anda separator in fluid communication with the contactor and coupled to receive the fuel/gas mixture therefrom, the separator configured to remove oxygen from the fuel and thereby generate and supply the deoxygenated fuel and the oxygen-rich purge gas.