GB148895A - Improvements in internal combustion engines for aircraft - Google Patents

Abstract

148,895. Junkers, H. May 27, 1918. [Convention date]. Addition to 147,219. Regulating. -Relates to an aircraft engine, as described in the parent Specification, having enlarged cylinders for developing the required power at a given altitude, but in which the compression space is not reduced. According to this invention, the fuel is supplied in measured quantities for each piston stroke; the quantity of fuel supplied is adapted to ensure complete combustion at the normal flying altitude; at higher altitudes the quantity of fuel is reduced automatically according to the decreasing density of the air; and at lower altitudes the fuel supply is constant and the air supply may be throttled by a regulating device in the air ind'uction pipe, as described in the parent Specification. As shown in the diagram, the automatic control is effected by an aneroid box 6 which expands with increasing altitude so as to move a grooved plate 18 and vary the positions of the levers 13 and 11. The parts are shown in the position corresponding to the normal flying altitude. As the box expands, the lever 13 is moved towards the dotted position, so that the stroke of the pump plunger 25 is shifted towards the left, and the effective portion of the stroke, viz. the distance by which the plunger overruns the suction port 26, is reduced. The position of the lever 11 controlling the air valve 2 is not altered by the expansion of the box 6, but when this box contracts, the lever 13 remains in the position shown and the lever 11 is moved towards the dotted position, compressing the spring 3 of the air valve 2. The fuel may be admitted to the induction pipe, as shown, into the cylinder, or into the pump of a two-stroke engine; and it may be injected by compressed air or admitted under an even pressure through positively-actuated valves. The aneroid device may act on the controls through relays.