[특허]Fuel flow anti-interruption

Rolls-Royce Corporation

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Fuel flow anti-interruption

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02M-037/00 F02M-037/20
미국특허분류(USC)	123/510; 123/516
출원번호	UP-0150054 (2008-04-24)
등록번호	US-7784448 (2010-09-20)
발명자 / 주소	Murray, Stephen G.
출원인 / 주소	Rolls-Royce Corporation
대리인 / 주소	Krieg DeVault LLP
인용정보	피인용 횟수 : 1 인용 특허 : 13

초록
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An anti-flow interruption system is configured to provide a supply of fuel in the event of a fuel flow interruption from a fuel tank. The anti-flow interruption system includes a reservoir, a reservoir conduit, and a vapor bleed system. The reservoir conduit has an end disposed at the bottom of the reservoir and another connected to a fuel pump. The vapor bleed system includes a vapor bleed conduit and a vapor bleed restrictor. One end of the vapor bleed conduit is attached to the top of the reservoir and the other end is connected to the fuel pump. The vapor bleed restrictor is disposed in the vapor bleed conduit between the fuel pump and the reservoir. If fuel flow is interrupted and results in vapor being present in the reservoir, liquid fuel remaining in the reservoir continues to be supplied to the fuel pump while the vapor bleed system removes the vapor.

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What is claimed is: 1. An apparatus comprising: a fuel tank; a fuel reservoir; a fuel pump located above the fuel tank and operable to receive fuel from the fuel reservoir; a first fuel path having a first fuel path intake in fluid communication with the fuel reservoir and a first fuel path outlet; a second fuel path having a second fuel path intake in fluid communication with the fuel tank and a second fuel path outlet in fluid communication with the fuel reservoir, wherein the second fuel path outlet is above the first fuel path inlet; and wherein in operation the fuel pump pulls fuel through the second fuel path outlet and into the reservoir. 2. The apparatus of claim 1, the first fuel path outlet in fluid communication with the fuel pump. 3. The apparatus of claim 2, which further includes a fuel vapor bleed off in fluid communication with the fuel reservoir. 4. The apparatus of claim 3, wherein the fuel vapor bleed off is connected between the fuel reservoir and the fuel pump and operable to convey vapor from the fuel reservoir. 5. The apparatus of claim 2, which further includes a fuel tank vent to connect the interior of the fuel tank to an exterior source of air. 6. The apparatus of claim 2, which further includes an aircraft having an engine; and wherein the apparatus provides fuel to the engine. 7. An apparatus comprising: a fuel reservoir; a fuel pump disposed in fluid communication with the fuel reservoir and configured to receive fuel from a first elevation within the fuel reservoir; and a fuel tank located below the fuel reservoir and disposed in fluid communication with the fuel reservoir at an elevation above the first elevation, wherein the fuel reservoir provides fuel to the fuel pump when the fuel flow is interrupted from the fuel tank; and wherein the fuel pump is capable of pumping fuel through the elevation and into the second elevation when fuel is not interrupted from the fuel tank. 8. The apparatus of claim 7, wherein the fuel pump is a high lift suction fuel pump. 9. The apparatus of claim 7, which further includes a vapor bleed connected between the fuel reservoir and the fuel pump. 10. The apparatus of claim 7, which further includes a vent disposed in the fuel tank, wherein the fuel tank is vented to an exterior pressure source. 11. A fuel delivery system comprising: a fuel tank and a fuel container downstream of the fuel tank; a fuel pump to pull fuel from the fuel container; and means for removing vapor from the fuel container and mitigating fuel flow interruption to the fuel pump when fuel flow from the fuel tank is interrupted. 12. The fuel delivery system of claim 11, wherein the means includes a vapor bleed conduit in fluid communication between the fuel container and the fuel pump. 13. The fuel delivery system of claim 11, which further includes a fuel vent. 14. The fuel delivery system of claim 11, which further includes an aircraft having a gas turbine engine; and wherein the fuel delivery system is operable to provide fuel to the engine. 15. A method comprising: coupling a fuel passageway in fluid communication with a fuel reservoir; configuring a pump to receive fuel from a fuel reservoir through the fuel passageway; locating an outlet of the fuel passageway above an intake of the fuel passageway; routing a fuel supply passage from a relatively low height of a fuel tank to a relatively high height of the fuel reservoir; and positioning an outlet of the fuel supply passage above the intake of the fuel passageway. 16. The method of claim 15, which further includes installing a vapor bleed circuit. 17. The method of claim 15, which further includes connecting the fuel passageway to a fuel pump, wherein the fuel pump is a high lift suction fuel pump. 18. The apparatus of claim 1, which further includes a fuel vapor bleed off having an opening that withdraws fuel vapor from the fuel reservoir when fuel is interrupted from the fuel tank. 19. The apparatus of claim 7, which further includes a fluid passage structured to convey fuel vapor from the fuel reservoir when fuel vapor is present in the reservoir. 20. The apparatus of claim 7, wherein the fuel pump is external of the fuel reservoir.

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이 특허를 인용한 특허 피인용횟수: 1

Heitz, Steven A.. Fuel pump system for bubble control. USP2018059964081.

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Fuel flow anti-interruption

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Fuel flow anti-interruption

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이 특허에 인용된 특허 (13)

이 특허를 인용한 특허 피인용횟수: 1

IPC 상위 출원인

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