[특허]Aircraft spillover fuel tank

The Boeing Company

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Aircraft spillover fuel tank

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-037/04
미국특허분류(USC)	244/135C; 244/135R; 244/135B
출원번호	US-0199069 (2008-08-27)
등록번호	US-8172182 (2012-05-08)
발명자 / 주소	Tanner, Richard Bruce
출원인 / 주소	The Boeing Company
대리인 / 주소	Hope Baldauff Hartman, LLC
인용정보	피인용 횟수 : 4 인용 특허 : 11

초록

Apparatus and methods described herein provide for a spillover tank to extend the fuel capacity of the main wing tank of an aircraft. The spillover tank is located in the wing of the aircraft adjacent to the main wing tank. At least one aperture exists through the shared barrier between the main wing tank and the spillover tank that allows fuel to flow passively between the tanks. A scavenge pump mechanism driven by motive flow from the main fuel pumps continuously pumps fuel from the spillover tank into the main wing tank.

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1. A spillover fuel tank for an aircraft, comprising: a barrier enclosing a fuel chamber within a wing of the aircraft inboard of and adjacent to a main wing tank, the main wing tank housing a main fuel pickup of a primary fuel pump, the barrier comprising an aperture between the fuel chamber and the main wing tank configured to allow aircraft fuel to passively flow between the main wing tank and the fuel chamber; the aperture positioned on an upper portion of the barrier between the fuel chamber and the main wing tank such as to prevent a reserved amount of fuel in the main wing tank sufficient to cover the fuel pickup from flowing into the fuel chamber; anda pump mechanism operative to provide a continuous flow of fuel from the fuel chamber into the main wing tank such that the reserve amount of fuel remains in the main wing tank as the fuel in the fuel chamber is exhausted. 2. The spillover fuel tank of claim 1, wherein an entirety of the fuel chamber is disposed outside a rotor burst zone of an aircraft engine mounted on the wing. 3. The spillover fuel tank of claim 1, further comprising a plurality of apertures between the fuel chamber and the main wing tank configured to allow aircraft fuel to flow between the main wing tank and the fuel chamber. 4. The spillover fuel tank of claim 3, wherein a number and a size of the plurality of apertures is configured to allow a flow rate of aircraft fuel from the main wing tank to the fuel chamber greater than or equal to a rate of refueling of the aircraft. 5. The spillover fuel tank of claim 1, further comprising a flapper valve through the barrier between the fuel chamber and the main wing tank configured to allow aircraft fuel to flow from the fuel chamber to the main wing tank and to prevent aircraft fuel from flowing from the main wing tank to the fuel chamber. 6. The spillover fuel tank of claim 5, wherein the flapper valve is positioned on a lower portion of the barrier between the fuel chamber and the main wing tank such as to allow aircraft fuel to flow from the fuel chamber to the main wing tank when a level of aircraft fuel in the main wing tank becomes lower than a level of aircraft fuel in the fuel chamber. 7. The spillover fuel tank of claim 1, wherein the pump mechanism comprises one or more scavenge pumps located within the fuel chamber. 8. The spillover fuel tank of claim 7, wherein the one or more scavenge pumps are driven by motive flow from a main engine pump mechanism. 9. A method of extending a main wing tank of an aircraft, comprising: enclosing a chamber within a wing of the aircraft adjacent to and inboard of the main wing tank to create a spillover tank;providing an aperture in a barrier between the spillover tank and the main wing tank on an upper portion of the barrier configured to allow aircraft fuel to passively flow between the main wing tank and the spillover tank such that a reserved amount of fuel remains in the main wing tank sufficient to cover a fuel pickup for a primary fuel pump and a hydraulic heat exchanger; andproviding a pump mechanism operative to provide a continuous flow of aircraft fuel from the spillover tank into the main wing tank such that the reserve amount of fuel remains in the main wing tank as the fuel in the spillover tank is exhausted. 10. The method of claim 9, wherein the spillover tank is disposed outside a rotor burst zone of an aircraft engine mounted on the wing. 11. The method of claim 9, further comprising providing a plurality of apertures in the barrier between the spillover tank and the main wing tank to allow a flow rate of aircraft fuel from the main wing tank to the spillover tank greater than or equal to a rate of refueling of the aircraft. 12. The method of claim 9, further comprising positioning a flapper valve in the barrier between the spillover tank and the main wing tank on a lower portion of the barrier such as to allow aircraft fuel to flow from the spillover tank to the main wing tank when a level of aircraft fuel in the main wing tank becomes lower than a level of aircraft fuel in the spillover tank. 13. The method of claim 9, wherein the pump mechanism comprises one or more scavenge pumps located within the spillover tank. 14. The method of claim 13, wherein the one or more scavenge pumps are driven by motive flow from a main engine pump mechanism. 15. A method of passive and active fuel flow control to provide fuel to an aircraft engine from an extension spillover tank comprising: providing motive fuel flow from a main fuel pump mechanism of a main wing tank to a scavenge pump mechanism in the extension spillover tank, the extension spillover tank connected to the main wing tank by at least one aperture in a barrier between the extension spillover tank and the main wing tank configured to allow fuel to passively flow between the main wing tank and the spillover tank, the at least one aperture positioned on an upper portion of the barrier such as to prevent a reserved amount of fuel in the main wing tank sufficient to cover a fuel pickup of the main fuel pump mechanism from flowing into the extension spillover tank;passively pumping fuel from the extension spillover tank into the main wing tank utilizing the scavenge pump mechanism; andactively pumping fuel from the main wing tank to the aircraft engine using the main fuel pump mechanism. 16. The method of claim 15, wherein the extension spillover tank is contained within a primary wing structure of an aircraft inboard of and adjacent to the main wing tank. 17. The method of claim 16, wherein the extension spillover tank is disposed outside a rotor burst zone of the aircraft engine mounted on a wing of the aircraft. 18. The method of claim 16, further comprising positioning a flapper valve in a barrier between the extension spillover tank and the main wing on a lower portion of the barrier such as to allow fuel to passively flow from the spillover tank to the main wing tank when a level of fuel in the main wing tank becomes lower than a level of fuel in the spillover tank. 19. The spillover fuel tank of claim 1, wherein the main wing tank further houses a hydraulic system heat exchanger and wherein the reserved amount of fuel in the main wing tank is further sufficient to cover the hydraulic system heat exchanger.

이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 4

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Aircraft spillover fuel tank

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Aircraft spillover fuel tank

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이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 4

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IPC 상세정보(version : 201201)

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