US 4,664,134 AGranted

Fuel system for flight vehicle

AssigneeThe Boeing Company

InventorRonald J. Pera

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Abstract

A main storage tank (2) is pressurized by engine bleed air. A supply tank (12) communicates with tank (2) and with an engine feed line (50). A fluid impermeable expandable wall (34) separates tank (12) into isolator chamber (38) and pressure chamber (40). A surface tension screen (44) covers inlet (42) into isolator chamber (38) to allow liquid fuel to enter chamber (38) and prevent gas from entering chamber (38). During operation of the flight vehicle, a fuel pump withdraws fuel from chamber (38). Pressure chamber (40) is vented to ambient air when the flight vehicle is under no power or is operating under g forces greater than zero, to allow wall (34) to expand and contract to compensate for changes in temperature and pressure. Chamber (40) is pressurized by engine bleed air when the vehicle is operating under zero or negative g forces.

Claims12

Dependent claims

In a flight vehicle fuel system of the type having a storage tank for storing fuel and means for pressurizing the tank, apparatus for compensating for temperature and pressure changes and negative g conditions, and for isolating the fuel from contamination, said apparatus comprising:

a fuel supply tank having an inlet communicating with the storage tank, and an outlet communicating with an engine feed line;
a fluid impermeable movable wall separating the supply tank into a variable volume fuel isolator chamber and a varible volume pressure chamber, said inlet and said outlet communicating with the isolating chamber;
a surface tension screen covering the inlet for allowing liquid fuel to enter the isolator chamber and preventing gas from entering the isolator chamber;
and
venting and pressurizing means for venting the pressure chamber to ambient air when the vehicle is under no power or is operating under positive g forces, to allow the movable wall to expand and contract to compensate for changes in temperature and pressure, and for pressurizing the pressure chamber when the vehicle is operating under negative g forces, to equalize the pressure on both sides of said wall so that said wall will contract as fuel is drawn out of the isolator chamber into the engine feed line.

2 more elements

For use in a flight vehicle fuel system of the type having a storage tank for storing fuel and means for pressurizing the tank, a method of compensating for temperature and pressure changes and negative g conditions and of isolating the fuel from contamination, said method comprising:

providing a fuel supply tank;
dividing the supply tank into a variable volume fuel isolator chamber and a variable volume pressure chamber separated by a fluid permeable movable wall;
communicating the isolator chamber with the storage tank through an inlet in the isolator chamber with an engine feed line through an outlet in the isolator chamber;
and
covering the inlet with a surface tension screen to allow liquid fuel to enter the isolator chamber and prevent gas from entering the isolator chamber;
venting the pressure chamber to ambient air when the vehicle is under no power or is operating under positive g forces, to allow the movable wall to expand and contract to compensate for changes in temperature and pressure;
and
pressurizing the pressure chamber when the vehicle is operating under negative g forces, to equalize the pressure on both sides of said wall so that said wall will contract as fuel is drawn out of the isolator chamber into the engine feed line.

5 more elements

Dependencies are inferred from the claim text.