Patent GB-953820-A (GB)
Title: Improvements relating to rocket engines and methods of operating the same
IPC: F02K9/56
Filed: 1962-03-02
Abstract: 953,820. Rocket engines. UNITED AIRCRAFT CORPORATION. March 2, 1962 [March 2, 1961], No. 8252/62. Heading F1J. A liquid fuel rocket engine comprises a combustion chamber 12, a fuel supply line 16 and a liquid oxidizer supply line 26, each line having a relief valve 22, 32 respectively and a supply valve 24, 34 respectively, an igniter fluid supply to the combustion chamber 10 including a supply valve 40, an ignition circuit including an igniter 42 and a normally closed switch 46 and a thrust control device 48 responsive to combustion chamber pressure. To start the rocket engine, a programming device 80 is set into operation and energizes a pre-start solenoid 89, which causes a pilot valve 90 to close a discharge port 94 and open a pressure port 92. Pressure fluid, such as helium is led to pressure chambers 74, 64 in relief valves 32, 22 respectively to open the valves and allow fuel and oxidizer to escape. After a very short time pumps 20, 30 are sufficiently cool to prevent vaporization therein The solenoid 89 is then de-energized and a solenoid 84 is energized to open a pressure port 106 and close a discharge port 108. Pressure fluid flows through a branch 122 to load the relief valve 22 to prevent it opening under normal fuel pressure, and through a branch 118 to an actuator 120 which opens a trap valve 52 to allow trapped pressure gases into the combustion chamber. Movement of the actuator link 128 actuates a pilot valve 136 to open a pressure port 142 and close a discharge port 144. The pressure fluid passes to an actuator 150 via a conduit 148 to open the igniter fluid supply valve 40 and simultaneously actuate pilot valves 160, 218 to open ports 164, 224 respectively. Pressure fluid. then flows through conduits 112, 114, 170 to a chamber 175 of an actuator 172 and as chamber 239 is vented via conduits 238, 226 the actuator link 176 moves to open ports 196, 198. A pressure differential is set up across an actuator 206 which opens the oxidizer supply valve 34. The successive opening of the fuel and oxidizer valves 24, 34 allows the fuel to be heated by the igniter flame and, as the pressure rises in the combustion chamber 12 when the mixture is ignited, the fuel and oxidizer supplies are controlled by the device 48. The pressure inside the combustion chamber expand a bellows 244 to open the switch 46 thereby de-energizing the igniter 42. Simultaneously the pressure acting on a bellows 248 maintains the rod 132 in its raised position. To shut down the rocket engine, the programming device 80 de-energizes the start solenoid 84, the pressure chamber 127 of the actuator 120 is vented to atmosphere and the link 128 closes the valve 52, but the rod 132 remains raised owing to the pressure in the combustion chamber. The fuel relief valve 22 is also unloaded and some of the fuel escapes through the vent 66. In the actuator 172 the chamber 175 is vented and the chamber 239 pressurised to return the link 176 and close the fuel supply valve 24. Movement of the link 176 also actuates the actuator 206 via valves 182, 184 and pressure conduits 204, 212 to close the oxidizer supply valve 34. The pressure drop in the combustion chamber 12 is transmitted to the chamber 247 and the rod 132 is lowered. Pressure fluid leaves the chamber 153 via the conduit 148 and the actuator 150 closes the igniter fluid supply valve 40.