| 摘要 |
1,178,723. Combustion gas generators; rocket engines. NORTH AMERICAN ROCKWELL CORP. Jan.25, 1967 [Jan.25, 1966 (2)], No.3787/67. Heading F1J and F1L. In a gas generating device comprising a combustion chamber having an associated throat, such as a rocket engine, the walls of the combustion chamber and throat are formed of a material having a high thermal conductivity to density ratio, and the injector apparatus adapted to inject fuel into the combustion chamber has means for injecting a film of coolant along the wall of the combustion chamber and throat. A high thermal conductivity to density ratio is defined as a ratio of at least 0À4 where thermal conductivity is expressed in BTU/ft<SP>2</SP> /‹ F/ft and density in 1b/ft<SP>3</SP>. The rocket engine shown comprises a wall 4 which defines a combustion chamber 8 and propulsion nozzle having a throat 6. At the inlet end of the chamber a spacer 12, an insulator 20 and an injector member 14 are secured to the wall 4 by means of bolts 18. A manifold ring 22 and injector member 16 are also provided. Fuel supplied through line 26 passes through duct 28 to the manifold 24 and is discharged into the combustion chamber through passages 30, 32, the fuel discharging through passages 32 forming a film cooling layer along the walls of the combustion chamber and nozzle. Oxidiser supplied through line 36 passes through duct 38 to the space 40 and then discharges through passages 42 into the combustion chamber. The wall 4 is formed by beryllium. In a further embodiment the wall is formed of copper the inner surface of which is plated with a layer of nickel; another material is aluminium in conjunction with a layer of nickel or stainless steel. Beryllium has a thermal conductivity to density ratio of 1À16, copper about 0À4 and aluminium about 0À68. It is stated that the high rate of heat conductivity enables the heat developed at the nozzl e throat to be conducted to the forward part of the rocket engine wall and then into the combustion chamber. |
