[특허]Aircraft fuel system

Airbus Operations Limited

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Aircraft fuel system

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-037/08 B64D-037/14
미국특허분류(USC)	244/135R; 244/135C; 244/136
출원번호	US-0346858 (2012-01-10)
등록번호	US-8777165 (2014-07-15)
우선권정보	GB-1101463.6 (2011-01-28)
발명자 / 주소	Roscoe, Paul Lehuunho, Emmanuel
출원인 / 주소	Airbus Operations Limited
대리인 / 주소	Lowe Hauptman & Ham, LLP
인용정보	피인용 횟수 : 0 인용 특허 : 12

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An aircraft fuel system has a fuel tank with first and second cells separated by one or more baffles. A venting system reduces pressure difference between the interior and exterior of the fuel tank, and an inerting system supplies oxygen-depleted gas to the fuel tank. The baffles permit the flow of fluid between the cells. The venting system has one or more vent nozzles within the fuel tank and in fluid communication with one or more vent ports. The inerting system has one or more inerting nozzles for injecting oxygen-depleted gas into the first and seco...

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1. An aircraft fuel system comprising: a. a fuel tank with first and second cells separated by one or more baffles, the baffles permitting the flow of fluid between the first and second cells;b. a venting system for reducing any pressure difference between an interior and an exterior of the fuel tank, the venting system comprising one or more vent nozzles which are positioned within the fuel tank and in fluid communication with one or more vent ports, wherein the venting system has a venting capacity associated with each cell, and wherein the venting capacity associated with the first cell is greater than the venting capacity associated with the second cell, which may be zero; andc. an inerting system comprising: i. one or more gas sources for generating oxygen-depleted gas;ii. one or more inerting nozzles for injecting oxygen-depleted gas from the gas source(s) into the first cell, where F1 is the sum of the oxygen-depleted gas flow rates from the inerting nozzle(s) into the first cell;iii. one or more inerting nozzles for injecting oxygen-depleted gas from the gas source(s) into the second cell, where F2 is the sum of the oxygen-depleted gas flow rates from the inerting nozzle(s) into the second cell; andiv. a control device for varying the ratio F1/F2 between the flow rates into the first and second cells, wherein the one or more vent nozzles comprise a large vent nozzle in the first cell and a small vent nozzle in the second cell with a smaller cross-sectional flow area than the large vent nozzle, wherein the large vent nozzle is arranged so that gas can be vented from the first cell during ascent of the aircraft through the large vent nozzle and so that air can be fed into the first cell during descent of the aircraft through the large vent nozzle, and wherein the small vent nozzle is arranged so that gas can be vented from the second cell during ascent of the aircraft through the small vent nozzle and so that air can be fed into the second cell during descent of the aircraft through the small vent nozzle. 2. The system of claim 1, wherein at least one of the cells comprises a bay with no internal baffles. 3. The system of claim 1, wherein at least one of the cells comprises a compartment containing one or more internal baffles which divide the compartment into a number of bays and permit the flow of fluid between the bays. 4. The system of claim 1 wherein the second cell contains no vent nozzles, and thus has a vent nozzle capacity of zero. 5. The system of claim 1 wherein the first cell is located in a wing of the aircraft and the second cell is located under a fuselage of the aircraft. 6. An aircraft fuel system comprising: a. a fuel tank with first and second cells separated by one or more baffles, the baffles permitting the flow of fluid between the first and second cells;b. a venting system for reducing any pressure difference between the interior and the exterior of the fuel tank, the venting system comprising one or more vent nozzles which are positioned within the fuel tank and in fluid communication with one or more vent ports, wherein the venting system has a venting capacity associated with each cell, and wherein the venting capacity associated with the first cell is greater than the venting capacity associated with the second cell, which may be zero; andc. an inerting system comprising: i. one or more gas sources for generating oxygen-depleted gas;ii. one or more inerting nozzles for injecting oxygen-depleted gas from the gas source(s) into the first cell, where F1 is the sum of the oxygen-depleted gas flow rates from the inerting nozzle(s) into the first cell;iii. one or more inerting nozzles for injecting oxygen-depleted gas from the gas source(s) into the second cell, where F2 is the sum of the oxygen-depleted gas flow rates from the inerting nozzle(s) into the second cell; andiv. a control device for varying the ratio F1/F2 between the flow rates into the first and second cells, wherein the inerting system comprises a network of inerting pipes which couple the inerting nozzles in both cells to a common gas source, and wherein the control device comprises a valve with a first setting in which the common gas source is coupled to the nozzle(s) in the first cell and decoupled from the nozzle(s) in the second cell, and a second setting in which the common gas source is coupled to the nozzle(s) in the second cell and decoupled from the nozzle(s) in the first cell. 7. The system of claim 1 wherein the (or each) gas source is coupled to the inerting nozzles without passing through the venting system. 8. The system of claim 1 wherein the venting system has a minimum cross-sectional flow area associated with each vent nozzle, and the total cross-sectional flow area associated with the vent nozzles in each cell of the fuel tank defines the venting capacity associated with that cell. 9. A method of operating an aircraft fuel tank system, the fuel tank system comprising: a fuel tank with first and second cells separated by one or more baffles; a venting system comprising one or more vent nozzles which are positioned within the fuel tank; and an inerting system comprising one or more inerting nozzles in the first cell and one or more inerting nozzles in the second cell, the method comprising: a. during cruise of the aircraft: i. introducing oxygen-depleted gas into the first cell at a flow rate F1(cruise), wherein F1 (cruise) is the sum of the oxygen-depleted gas flow rates from the inerting nozzle(s) into the first cell and wherein F1(cruise) may be zero; andii. introducing oxygen-depleted gas into the second cell at a flow rate F2(cruise), wherein F2(cruise) is the sum of the oxygen-depleted gas flow rates from the inerting nozzle(s) into the second cell; andb. during descent of the aircraft: i. operating the venting system to introduce air into at least the first cell through one or more of the vent nozzles in order to reduce a pressure difference between the interior and the exterior of the fuel tank, wherein the total air flow rate from the venting system into the first cell is greater than the total air flow rate from the venting system into the second cell, which may be zero;ii. introducing oxygen-depleted gas into the first cell at a flow rate F1 (descent), wherein F1(descent) is the sum of the oxygen-depleted gas flow rates from the inerting nozzle(s) into the first cell; andiii. introducing oxygen-depleted gas into the second cell at a flow rate F2(descent), wherein F2(descent) is the sum of the oxygen-depleted gas flow rates from the inerting nozzle(s) into the second cell and wherein F2(descent) may be zero; andc. after step b., permitting gas to flow across the baffle(s) between the cells in order to reduce any difference in oxygen concentration between them, wherein the ratio of oxygen-depleted gas flow rates F1(descent)/F2(descent) during descent is greater than the ratio of oxygen-depleted gas flow rates F1 (cruise)/F2(cruise) during cruise.

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Aircraft fuel system

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