Fuel supply system

Aeronautics and astronautics – Aircraft structure – Fuel supply

Patent

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Details

244135C, 137566, 137572, B64D 3700, B64D 3704, B64D 3730, F17D 102

Patent

active

056603584

ABSTRACT:
Fuel supply system for multijet airplanes using cryogenic fuel with one tank or one tank group for each engine or for all engines on one side of the longitudinal central plane of the airplane, and, if desired, with an additional, common tank or an additional, common tank group for all engines. A transfer line with shut-off valve leads from each tank/tank group associated with a defined engine or with the engines of one side of the airplane to at least one other tank/tank group and/or, if desired, to the tank/tank group common to all engines. If desired, at least one transfer line leads from the common tank/tank group to at least one other tank/tank group.

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W. Steinebach, 1964, Luftfahrtzubehor, Bei Ablage in DIN A 4-Ordner hier abschneiden, No Translation.
Herrn Krabel, Jul. 15, 1969, Design Considerations of the DC-8 Fuel System, Dornier GmbH Druckschrift "The SAE Journal", No Translation.
Hawker Siddeley, Jan. 1970, Powerplant: Fuel System, Aircraft Engineering, Translation.

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