Patent GB-572876-A (GB)
Title: Improvements in or relating to fluid reaction apparatus for propelling purposes
IPC: F02K7/02
Filed: 1943-09-01
Abstract: 572,876. Jet propulsion of aircraft &c. STARK, F. H. Sept. 1, 1943, No. 14282. [Class 51 (i)] [Also in Group XXXIII] The jet propulsion of vehicles, ships and aircraft is effected by causing a column of fluid to be driven from the open end of a discharge tube at a velocity sufficient for it to set up a reactive effect for driving the vehicle &c. and in addition to set up a depression below atmospheric pressure in a combustion chamber at the other end of the tube so that after discharge of such column from the tube the ambient fluid is able to enter and set up a column of fluid moving through the tube in the reverse' direction and by its momentum exerting sufficient pressure for compressing a charge of air and fuel admitted for combustion into the combustion chamber. In the apparatus shown in Figs. 1 and 1a, fuel is sprayed into a combustion chamber 2 and ignited by a sparking plug 8. The explosion causes a column of gases to pass along the tube 1 to the open end la and also to cause a depression in the combustion chamber, whereupon a valve 3 opens against the action of a spring 5 and admits a mixture of fuel and air from a carburetter 6, 7 to the combustion chamber 2. The amount of mixture admitted to the combustion chamber is insufficient to restore atmospheric pressure so that a column of air from the atmosphere returns through the tube and compresses the charge and also closes the valve 3. The charge is ignited by the electric contacts 12 being closed by the motion of the rocker arm 4 of the valve 3. The exterior of the tube 1 may be cooled by an air or water jacket and where, as shown, an air jacket is employed, the tube 1 may be provided with fins 21. The interior of the tube may also be provided with partitions 20. Gases may be withdrawn from the tube 1 through a valve 23 and pipe 22 and used for auxiliary purposes. The combustion chamber 2 may be provided with an auxiliary air inlet 11. The valve 3 may be operated by a cam and instead of lift valve 3, sliding piston or reed valves may be used for the admission of air, fuel being injected into the combustion chamber under pressure. Two or more combustion chambers may discharge into a single tube 1 or a number of tubes 1 may receive the gases from a single combustion chamber. In the modification shown in Fig. 6, one or more annular ducts 50 are disposed along the tube 1 and supplied with fuel and air.from a carburetter 60, the inlet port 51 being controlled by a sleeve valve 52. Correction for atmospheric pressure and temperature may be provided by providing a duct 71 in communication with the air jacket 15 and a thermometer 70 arranged in the air jacket and connected to capsules 73, 72 adapted to influence the disc 74 of a governor 75 connected to the throttle lever 79. A number of propulsion units for aircraft may be grouped in a circle or arranged in a row ; in the latter case, the units may be mounted on the wing of an aeroplane. When the propulsion units are applied to marine vessels, the open ends of the tubes may be situated beneath the surface of the water in which the vessel is floated, in which case the water would be the ambient medium. Reference has been directed by the Comptroller to Specification 176,838, [Class 51 (i)].