GB896966A - Improvements in or relating to rocket motors - Google Patents

Abstract

896,966. Rocket propulsion. FISCHOFF, E. July 24, 1958 [July 31, 1957], No. 23856/58. Class 110 (3). [Also in Group XXIX] A rocket motor assembly comprises a main combustion chamber to which a plurality of propellant fluids are supplied by turbine-driven propellant pumps, at least one gas generator being provided for supplying working fluid to the turbine or turbines, the gas generator also being supplied with a plurality of fluids, means being provided for stabilizing and equalizing the output pressures of the fluids of each plurality of fluids. The output pressure of each of the fluids feeding the main combustion chamber is made equal to a first pre-set reference pressure, and the output pressure of each of the fluids feeding the gas generator is made equal to a second pre-set reference pressure, the output pressures being varied by varying the reference pressures. In Fig. 4 combustion ingredients are supplied by means of pumps 17, 18, 19 to the gas generator of a gas turbine (not shown) which drives the propellant pumps. Fluids from the pumps 17, 18 flow through lines 23, 24 and through regulators 25, 26, respectively, thence to the gas generator. The regulators 25, 26 are supplied with fluid at a " reference " pressure obtained from the downstream side of a by-pass valve 27 which is supplied from pump 19, the fluid from the pump 19 also flowing to the gas generator. One form of regulator is shown in Fig. 1 and comprises a piston 5 mounted in a bore 2 in a casing 1, the piston being connected by its rod 6 to a diaphragm 7. Fluid is supplied from the pump through inlet 3 and is discharged through outlet 4, the pressure at the outlet being determined by the position of the piston. The lower side of the diaphragm is subjected to the " reference " pressure of the fluid from the by-pass valve 27, while the upper side of the diaphragm is subjected to the pressure of the fluid in the outlet 4. Should the latter pressure rise with respect to the former, the diaphragm will move the piston to restrict the flow passage from inlet 3, and vice versa. The piston 5 is provided with a through bore 12 so as to equalize pressures above and below the piston. In Fig. 2, the piston 5 and rod 6 are disposed coaxially with the inlet 3, this arrangement avoiding side thrust on the piston. In another arrangement the piston 5 is mounted in a sleeve disposed within the bore in the casing, fluid from the inlet passing into a space around the sleeve and thence through radial bores in the sleeve to the space below the piston 5. In Fig. 5, the " reference " pressure is obtained by a separate device which comprises a cylinder and piston arrangement, the position of the piston and so the pressure of the inert fluid contained in the cylinder being varied by means of the lever 41. The pressure of the reference fluid is supplied through ducts 36, 37, 38 to regulators 28, 29, 30, one in each of the fluid supply lines to the gas generator. In Fig. 6 the invention is shown applied to the supply of combustion fluids to both the main combustion chamber 53 of a rocket motor and to the gas generator 57 supplying gases to a turbine 67 driving the combustion fluid pumps 48, 49, 50, the two separate reference pressures being derived from units 61, 64<SP>1</SP> similar to that shown in Fig. 5. Fluids from the three pumps 50, 49, 48 flow through the regulators 58, 59, 60 to the gas generator 57, the reference pressure being applied to the regulators from unit 61 through lines 62, 63, 64. Fluids from the two pumps 48, 49 flow through regulators 62<SP>1</SP>, 63<SP>1</SP> to the rocket combustion chamber 53, the reference pressure being applied to the regulators from unit 64<SP>1</SP> through lines 65, 66. In the arrangement shown in Fig. 9, fluids are supplied by means of three pumps 89, 90, 91 to the combustion chamber 98, the pressure of fluid from the pump 89 being taken as a reference pressure and applied to the regulators 94, 95 in the supply lines from the pumps 91, 90. The pressures of the fluids delivered at 94, 95 are therefore equal and equal to that of fluid delivered by pump 89.