Patent GB-537473-A (GB)
Title: Improvements in or relating to gaseous fluid jet reaction devices or like prime movers
IPC: F02K7/00
Filed: 1939-11-22
Abstract: 537,473. Self-propelled missiles. WALTON, G. W. Nov. 22, 1939, No. 30568. [Classes 9 (i) and 9 (ii)] [Also in Groups XXXIII and XXVI] A propelling 'device comprises a rigid structure having a system of helical passages around a common axis about which it rotates, gaseous the passages where it is compressed, heated by combustion of a fuel and then expanded and discharged at the rear to give an axial thrust, a peripheral component of the energy maintaining the rotation of the device to compress the incoming fluid. The device may also be used for compressing in or exhausting air from a closed chamber, or the discharged fluid may drive the rotor of a turbine. Fig. 1 shows a device acting as an aerial torpedo. A central hollow body 3 is connected by helical ribs 2 to an outer shell 1 open at both ends. The device is started by rotating it about its axis whereupon air is drawn in at the front end compressed and consequently raised in temperature to a point where it is mixed with fuel injected by centrifugal force through holes 10 from a reservoir 9 and ignited. The heated combustion products are then expanded and discharged at the rear, reaction against the ribs 2 maintaining the rotation of the device. A forward chamber 8 contains explosive. Should the temperature due to compression be insufficient to ignite the mixture, devices shown in Fig. 10 may be mounted in the passages near the holes 10. These consist of open-ended tubes pressed to form fins 76, the air entering the end 75 being further compressed and raised in temperature before issuing at the rear. ends. At starting or throughout operation these devices may be heated electrically by current from a motorgenerator which may have its rotor driven in the opposite direction to the main body by vanes in the fluid stream. For supporting and propelling aircraft the devices may rotate about fixed spindles through which fuel may be supplied, and leads from the electric motor-generator taken, the supports of the fixed spindle being mounted on trunnions to enable the direcfluid being induced to flow continuously through tion of thrust to be varied. Fig. 5 shows such a device, a part 20 of the generator being mounted on the fixed spindle 22, about which the central body carrying the other part 19 of the generator rotates. In this form the fuel chamber rotates in the opposite direction to the rest of the device and fuel is supplied to the chamber through a bore 21 in the spindle 15. For controlling the supply of fuel at different altitudes of the aircraft the holes 10 are controlled by needle valves 43, Fig. 8, adjusted axially by screws 45 when rotated by pinions 44 engaging a rack connected to a flexible diaphragm 41 of an air capsule subjected to the external atmospheric pressure. The same rack may engage pinions 59 to control rotary valves 58 for shutting off supply of fuel to certain of the helical passages when flying at low altitudes. To prevent disturbance of longitudinal balance as the rack moves, counterweights are moved 'by the opposite sides of the pinions 59, or when valves 58 are not used, by the pinions 44. An aerial propeller having blades 69, Fig. 9A, which need not be thickened at the root is driven by a similar device wherein the central body 3 is expanded to form a rim encircling the blades, helical passages being formed by ribs 2 connecting the rim 3 to an outer rim 1 and fuel being supplied to holes 10 through passages 29 in the blades 69, the whole rotating about a fixed spindle 15. Fig. 9B shows a modification in which the output from a propelling device 70 entrains extra air through cones 73, 74 supported by streamline fins 72. Similar cones may be immersed in water for marine propulsion the water being entrained by the products of combustion from a propelling device mounted within the vessel.