Patent GB-548898-A (GB)
Title: Improvements in or relating to the propulsion of aircraft and other vehicles
IPC: F02K7/06
Filed: 1941-07-08
Abstract: 548,898. Jet propulsion apparatus. FAIREY AVIATION CO., Ltd., and FORSYTH, A. G. July 8, 1941, Nos. 8620 and 11795. [Classes 4 and 114] [Also in Groups XII and XXVI] Apparatus for generating gases for the jet propulsion of aircraft and other vehicles and for driving auxiliaries such as electric generators, air compressors fuel pumps and the like comprises an air intake chamber separated by a valve from an explosion chamber to which fuel is injected and air admitted by the valve periodically and exploded, the two chambers being shaped conjointly to constitute a Venturi tube with the valve at its throat. As shown in Fig. 1, the air chamber a, the open end of which is directed forwardly of the vehicle, is separated from the explosion chamber c by a valve e, which may be sodium filled, and combusion gases are ejected through the pipe f. The two chambers are provided with water jacket b, d. The valve e is connected by its spindle to a piston q in a cylinder p and is held against its seat by a spring o. The valve is opened by compressed air supplied through ports r, sunder the control of a piston valve k to the cylinder p and the piston is moved against the action of the spring o. As the valve opens, an extension 29 of the valve spindle actuates through levers 26, 22 interconnected by a spring 30 the piston valve k to close the compressed air supply ports r, s and open exhaust ports t, u. The valve e then closes under the action of the spring o and air from the cylinder p exhausts through the ports t, u to a pipe v which is provided with a perforated construction in communication with a fuel supply pipe y to effect a supply of fuel to a nozzle g located in the explosion chamber. Also as the valve e closes the spindle extension 29 closes a switch 31 in the primary circuit of an ignition coil 34 the secondary of which is connected to a sparking plug h. In modifications (not shown) the piston valve k is provided with additional grooves cooperating with ports in the boss n to supply fuel in measured quantities to the nozzle g and water to the explosion chamber c. In the modification shown in Fig. 8, the fuel supply is regulated in accordance with the speed of the aircraft or vehicle. The valve K controls the compressed air and exhaust ports r, s, t, u, exhaust port 38 connected to the port u and fuel supply ports 39, 42. The fuel port 42 is connected through a valve 44 to the compressed air exhaust port 38 and to the nozzle g. A pitot tube 53 in the air chamber a is connected to a chamber 51 enclosing a bellows device 50 which actuates a toggle lever 56, 57 connected to the fuel valve 44 and the throttle lever 58. As shown in Fig. 12, the explosion chamber c is of Venturi shape having a spring pressed sodium cooled valve 60 as its throat. After initial movement of the valve by the explosion gases a piston 62 mounted on the valve spindle is moved to open a port 70 which admits air to open the valve to its full extent. The port 70 is controlled by a piston valve 66 actuated by levers similar to those employed for operating the piston valve k. The air intake chamber a may be associated with a number of explosion chambers each separated from the air chamber by a valve, the valves being mounted on radial arms and actuated simultaneously by the piston q. Alternatively the air chamber may be divided into compartments each provided with a valve, the valves being operated simultaneously to admit air to a common explosion chamber. Multiple air chambers and corresponding multiple explosion chambers may also be employed. Fig. 18, shows the explosion chamber c delivering through an exhaust passage f and between fixed vanes 82 to a turbine 81 for driving an electric generator 79 forming part of auxiliary apparatus. Steam generated in the jacket d may be utilized for driving a turbine 88 connected to an auxiliary such as an air or fuel compressor. Fig. 20 shows a number of units arranged about an axis some of the units being employed as propulsion units and others for driving a sodium cooled turbine 100 driving the rotor 101 of a multistage supercharger delivering to a volute 105 which replaces the several intake chambers of the units. The rotor shaft also drives through gearing a fuel pump 119, air compressor 120 and electric generator 116. The air compressor may deliver to a distributor to supply compressed air successively to the operating mechanism for the main valves e. When the explosion chamber is of Venturi shape, a streamlined centre piece carried by a spider may be arranged to the rear of the throat. The open end of the air chamber a may be provided with a streamlined nose piece adapted to move away from the end of the chamber when the chamber is in operation. The gas generating units when applied to an aircraft may be arranged beneath the body, at the tail or in the wings.