GB592758A - Liquid fluid combustion device - Google Patents

Abstract

592,758. Air and gas heating stoves. SOLAR AIRCRAFT CO. Jan. 9, 1945, No. 737. Convention date, June 2, 1944. [Class 64 (i)] [Also in Groups XI and XXXIII] A combustion device which produces a stream of warmed air, e.g., for heating aircraft cabins, comprises a combustion chamber 17 into which is introduced a mixture of air and liquid fuel from the apertures 29 in a pipe 28, to be ignited electrically by a wire 78. In order to obtain complete combustion, auxiliary air from an intake manifold 25 is led into the chamber 17 by longitudinally spaced ducts 30 and 31. The correct air and fuel pressure rates are maintained for any fuel pump speed or any ambient air pressure, by a butterfly valve 44 in the air intake duct, the position of the valve being controlled by the pressure on a diaphragm 46 which is responsive to the fuel pressure in the syphon bellows 52 on its top-side and to the pressure of the incoming air on its lower side. The combustion gases leave the chamber 17 at its right hand end by the discharge orifice 39 to be mixed with a flow of cold air, the whole lot passing between the chamber 17 and the casing 10 to be introduced into the cabin. A thermostat 56 in series with an electrically driven pump 20 decreases the pump speed and hence the amount of fuel supplied when the valve 44 carrying a contact arm 58 is near its fully open position. The electric circuit includes thermal and pressure responsive switches to ensure that no fuel is supplied to the burner until a certain air pressure has been attained and until the wire 78 is heated up. The air may be supplied to the combustion chamber by a blower 72 in such a heater used on the ground, or from a scoop on the exterior of the machine in the case of an aircraft.