GB826861A - Rocket motors - Google Patents

Abstract

826,861. Rocket motors. NAPIER & SON Ltd., D. May 1, 1957 [May 14, 1956], No. 15016/56. Class 110 (3). [Also in Groups XI and XII] In a rocket motor of the kind using a fuel and an oxidant, the fuel being in liquid form and the oxidant being in gaseous form when introduced to the fuel and oxidant distributer, the gaseous oxidant is supplied into the combustion chamber through an annular duct and the liquid fuel is introduced into the duct through an orifice in the inner wall of the annular duct with a substantial component of velocity transverse to the flow of gaseous oxidant so that the liquid fuel impinges on a surface constituted by the outer wall of the annular duct whereby the fuel is atomized and distributed through the gaseous oxidant. The rocket motor shown comprises an outer casing 1 and an inner casing 2 which affords a combustion space 5 leading to a Venturi-shaped propulsion nozzle 6, a catalyst chamber 3 being disposed within the upstream end of the casing. Hydrogen peroxide is supplied to the space 7 between the outer casing 1 and inner casing 2 where it provides a cooling effect on the combustion chamber and propulsion nozzle and then enters the decomposition chamber 3 issuing therefrom in the form of a mixture of steam and oxygen at high temperature and pressure. The mixture then flows through passages 14 in the fuel and oxidant distributer 4 to the annular duct 11 and then discharges through the annular duct formed between the frusto-conical surfaces 12, 13 into the combustion zone. Liquid fuel such as paraffin is supplied through a duct 8 to the chamber 19 and then flows through passages 18 in web members 30 to a manifold 20, the fuel then flowing radially inwardly through a narrow annular space 21 and through openings 23 into a central chamber 24. The fuel then flows through a non-return valve 25 to a space 26 and thence through a narrow annular space 28 and finally through a series of discharge orifices 29 into the flow of steam and oxygen issuing through the annular duct 12, 13. The liquid fuel flowing through the narrow passages 21, 28 provides a cooling effect on the walls 9, 31 of the fuel and oxidant distributer, these walls actually forming the end wall of the combustion chamber. Some steam and oxygen issuing from the decomposition chamber enters the combustion space through the passage 15, being caused to flow radially inwardly by the flanged lip 17. Reference has been directed by the Comptroller to Specification 727,720, [Groups XII and XXXI].