Fuel system for flight vehicle

Details Fuel system for flight vehicle Fuel system for flight vehicle

1985-09-30

1987-05-12

Nilson, Robert G.

Fluid handling

Processes

Involving pressure control

55159, 60 3948, 137 38, 137177, 137571, 244135B, F02C 722

Patent

active

046641343

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.

REFERENCES:
patent: 2621719 (1952-12-01), Eaton
patent: 2860648 (1958-11-01), Harrison
patent: 3136507 (1964-06-01), Erlanger et al.
patent: 3176882 (1965-04-01), Meermans
patent: 3286463 (1966-11-01), McGroarty
patent: 3409714 (1968-11-01), Strugar, Jr.
patent: 3486302 (1969-12-01), Paynter
patent: 3854905 (1974-12-01), Balzer et al.
patent: 3933448 (1976-01-01), Di Peri
patent: 4033115 (1977-07-01), Baits
patent: 4093428 (1978-06-01), Swogger
patent: 4168718 (1979-09-01), Hess et al.

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