| 摘要 |
809,844. Rocket motors. ARMSTRONG SIDDELEY MOTORS Ltd. June 21, 1957 [July 5, 1956], No. 20824/56. Class 110 (3). [Also in Group XII] In a rocket motor operating with liquid fuel and concentrated hydrogen peroxide, a catalyst unit is provided at the upstream side of the combustion chamber for decomposing a relatively small proportion of the total delivered supply of concentrated hydrogen peroxide, the remainder of the supply being directed in a spray towards a spray of the liquid fuel in the region where the decomposition products of the relatively small proportion of the concentrated hydrogen peroxide are delivered to the upstream end of the combustion chamber. The upstream end of the rocket motor shown comprises a ring member 18 having formed in the wall thereof a series of through bores 20 which alternate with blind bores 21, the ends of tubes 15, which are shaped to provide the wall of the combustion chamber, throat and propulsion nozzle, being secured in the bores 20, 21. The tubes 15 at their downstream ends enter an annular header so that hydrogen peroxide supplied to the inlet manifold 37 can flow in a downstream direction through the tubes 15 secured in the blind bores 21 to the header 17, then in an upstream direction through the tubes 15 secured in the through bores 20, the hydrogen peroxide thereby cooling the wall of the combustion chamber and propulsion nozzle before being delivered into the space between the end plate 19 and the perforated frusto-conical plate 33. A small proportion of the hydrogen peroxide passes through the perforations 34 into the catalyst chamber 36 which contains silver or silver-plated nickel gauzes and is there decomposed, the decomposition products issuing through the spaces between the radial spokes 29 into the combustion chamber. The remainder of the hydrogen peroxide enters the annular space between the walls 25, 27 and then passes through ducts 40 in the spokes 29 to the annular chamber 31 issuing therefrom into the combustion chamber through spray nozzles 41. Liquid fuel supplied at 26 passes through the central duct 25 and issues into the combustion chamber through spray nozzles 39. In Fig. 3 a valve member 32a is supported within the central duct 25, the valve being loaded by means of a spring 47. The valve is opened against the force of the spring by the pressure of the fuel supplied to the duct 25, the fuel discharging into the combustion chamber through the annular opening 39a. The tubes 15 forming the wall of the combustion chamber and nozzle are covered by wire wound under tension. |
