GB851428A - Fuel supply system for use in aircraft - Google Patents

Abstract

851,428. Fuel supply systems. UNITED AIRCRAFT CORPORATION. June 19, 1958 [Aug. 28, 1957], No. 19622/58. Class 7(3). [Also in Groups XXIX and XXXIII] In an aircraft fuel system described particularly for a helicopter wherein the tank or tanks are located in the lower part of the main freight compartment, a tank 40 is supported by the lower part of the fuselage 10 between bulkheads 50 and 52. The tank is formed with sumps 54 and 56 positioned below the water and sludge level AA and a container 68 is sealed at its base to sump 54, is open at its top and is provided with an aperture 69 above level AA having a one-way valve 73 which permits fuel flow only into the container. An electrically driven booster pump 66 draws fuel from the interior of the container and delivers it through conduit 82, strainer 80 and valve 92 to engine driven pump 88 from whence it is delivered to the engine 25. Sump 56 supports a filter 107 which encloses an ejector pump 98, the outlet 108 connecting by pipe 118 and non-return valve 120 with container 68 and the nozzle 112 being fed with fuel tapped from pipe 96 by pipe 122 either upstream or downstream of pump 88. Drain valves 64, overflow connection 65 and vent 91 are provided. The arrangement ensures that the tank will be completely emptied regardless of the attitude of the aircraft for in a dive with fuel at level B container 68 will be supplied with fuel through valve 73 whereas in a climb with fuel at level C the ejector pump will feed container 68 and pump 66 through pipe 118. In level flight both pumps function. A further embodiment is described of two connected tanks, one as shown in Fig. 2 and the other having an ejector pump only, also feeding into container 68. In this arrangement the ejector pump may be dispensed with in the tank containing pump 66.