Fuel transmission system
AssigneeTusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi
InventorsBerke Alp Mirza, Mustafa Bahadir Karahan
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Abstract
The present invention relates to a body (2) that is located on the aircraft, at least one external tank (T) that is located on the body (2) and provides fuel accumulation, at least one valve (3) that is located between the body (2) and the external tank (T) and provides fuel transmission, at least one opening (4) that is located on the valve (3) and allows the fuel passage between the body (2) and the external tank (T), a gear region (5) that is located oppositely on the body (2) and on the valve (3) and allows the valve (3) to be mounted on the body (2), and at least one sealing element (6) that is located between the body (2) and the valve (3) in a way surrounding the valve (3) and prevents fuel from leaking into the body (2).
Claims8
A fuel transmission system comprising:
- an aircraft body structure configured for fuel containment;
- at least one external tank mounted on the aircraft body structure, the external tank configured to accumulate fuel;
- at least one valve disposed between the aircraft body structure and the external tank, the valve configured to transmit fuel between the aircraft body structure and the external tank;
- at least one opening on the valve, the opening configured to allow fuel passage between the aircraft body structure and the external tank;
- a threaded region formed on opposing surfaces of the aircraft body structure and the valve, the threaded region configured to mount the valve to the aircraft body structure;
- at least one first sealing element disposed between the aircraft body structure and the valve and surrounding the valve, the first sealing element configured to prevent fuel from leaking into the aircraft body structure;
- at least one second sealing element disposed between the opening and the threaded region, the second sealing element configured to prevent fuel from the opening from reaching the threaded region;
- and
- at least one coating on the threaded region, the coating configured to provide galvanic compatibility between the aircraft body structure and the valve, thereby preventing corrosion.
The fuel transmission system according to 1, wherein the aircraft body structure comprises a slot through which the valve is inserted to mount the valve to the aircraft body structure, and wherein the threaded region is positioned so as to remain outside the external tank when the valve is passed through the slot, such that the threaded region is spaced apart from fuel within the external tank.
Dependencies are inferred from the claim text.