RU95104119A - Flying vehicle fuel system - Google Patents

Flying vehicle fuel system

Info

Publication number
RU95104119A
RU95104119A RU95104119/11A RU95104119A RU95104119A RU 95104119 A RU95104119 A RU 95104119A RU 95104119/11 A RU95104119/11 A RU 95104119/11A RU 95104119 A RU95104119 A RU 95104119A RU 95104119 A RU95104119 A RU 95104119A
Authority
RU
Russia
Prior art keywords
compartment
fuel
pipe line
pipe
point
Prior art date
Application number
RU95104119/11A
Other languages
Russian (ru)
Other versions
RU2082653C1 (en
Inventor
Д.Г. Борисов
Original Assignee
Акционерное общество открытого типа "Авиационный комплекс им.С.В.Ильюшина"
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Акционерное общество открытого типа "Авиационный комплекс им.С.В.Ильюшина" filed Critical Акционерное общество открытого типа "Авиационный комплекс им.С.В.Ильюшина"
Priority to RU95104119A priority Critical patent/RU2082653C1/en
Publication of RU95104119A publication Critical patent/RU95104119A/en
Application granted granted Critical
Publication of RU2082653C1 publication Critical patent/RU2082653C1/en

Links

Landscapes

  • Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

FIELD: aircraft manufacture. SUBSTANCE: fuel system has fuel tank 1, service compartment 2, booster pumps 3; one booster pump is located in negative load factor compartment 4. Pumps 3 are connected to fuel feed pipe line 5 connected with active fuel supply pipe line 8 which is fitted with sediment drain valve 10 mounted at lower point of bend 9 provided in pipe line 8. Valve 10 is connected with service compartment by means of pipe line 15. Jet pumps are connected to pipe line 8 at point 11 by means of active fuel mains 12 and 13; they are connected with service compartment 2 by means of anti-siphon pipe line 14. Point 11 and points of entry of pipe lines in service compartment 2 are located above level of negative load factor compartment. EFFECT: enhanced reliability of system operation due to guaranteed amount of fuel in service compartment for starting auxiliary power plant and engines and due to avoidance of air inleakage into fuel feed system.

Claims (1)

Топливная система состоит из топливного бака 1, расходного отсека 2, насосов подкачки 3, один из которых расположен в отсеке отрицательных перегрузок 4. Насосы 3 подключены к трубопроводу подкачки 5, связанному с трубопроводом 8 подачи активного топлива, снабженному клапаном 10 слива отстоя, установленным в нижнем точке изгиба 9, выполненного в трубопроводе 8. Клапан 10 соединен трубопроводом 15 с расходным отсеком 2. К трубопроводу 8 в точке 11 подключаются магистралями 12 и 13 активного топлива струйные насосы, соединенные противосифонным трубопроводом 14 с расходным отсеком 2. Точка 11 и место входа в трубопровода 14 в расходный отсек 2 расположены выше уровня отсека отрицательных перегрузок. Предлагаемое выполнение топливной системы обеспечивает повышение надежности ее работы за счет обеспечения гарантированного запаса топлива в расходном отсеке для запуска вспомогательной силовой установки и двигателей, а также за счет исключения попадания воздуха в систему подкачки топлива.The fuel system consists of a fuel tank 1, a supply compartment 2, and booster pumps 3, one of which is located in the negative overload compartment 4. Pumps 3 are connected to a booster pipe 5 connected to the active fuel supply pipe 8, equipped with a sludge drain valve 10 installed in the lower point of the bend 9 made in the pipe 8. The valve 10 is connected by a pipe 15 to the flow compartment 2. To the pipe 8 at the point 11 are connected jet lines 12 and 13 of the active fuel connected by an anti-siphon pipe Odom 14 with feed compartment 2. The point 11 and the entry in the pipeline 14 into the feed compartment 2 are disposed above the level of negative accelerations compartment. The proposed implementation of the fuel system provides an increase in the reliability of its operation by ensuring a guaranteed fuel supply in the consumable compartment for starting the auxiliary power unit and engines, as well as by eliminating air from entering the fuel pumping system.
RU95104119A 1995-03-23 1995-03-23 Flying vehicle fuel system RU2082653C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU95104119A RU2082653C1 (en) 1995-03-23 1995-03-23 Flying vehicle fuel system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU95104119A RU2082653C1 (en) 1995-03-23 1995-03-23 Flying vehicle fuel system

Publications (2)

Publication Number Publication Date
RU95104119A true RU95104119A (en) 1996-12-20
RU2082653C1 RU2082653C1 (en) 1997-06-27

Family

ID=20165877

Family Applications (1)

Application Number Title Priority Date Filing Date
RU95104119A RU2082653C1 (en) 1995-03-23 1995-03-23 Flying vehicle fuel system

Country Status (1)

Country Link
RU (1) RU2082653C1 (en)

Also Published As

Publication number Publication date
RU2082653C1 (en) 1997-06-27

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