Patent GB-1167948-A (GB)
Title: Rocket Engine.
Inventor: ANDREWS EDWARD GEORGE DAVID
IPC: F02K9/48
Filed: 1967-06-03
Abstract: 1,167,948. Liquid propellant rocket engines. ROLLS-ROYCE Ltd. June 4, 1968 [June 3, 1967], No. 25754/67. Headings F1J and F1L. A rocket engine comprises a combustion chamber, at least one propellant supply line to the combustion chamber, a combustion gas generator connected to the propellant supply line or lines, through which part of the propellant flowing therethrough will be diverted through a pump to the gas generator, gas from the gas generator being passed to the propellant container to pressurize propellant therein, the propellant being discharged to the combustion chamber. In Fig. 1 the rocket engine comprises a combustion chamber 1, propellant containers 2 and 3, the propellants being for example hydrazine and chlorine trifluoride, and a gas generator 16. The containers 2 and 3 are connected by lines 4 and 5 to the combustion chamber 1, throttle valves 6, 7 being provided in the lines. Propellant is tapped from the lines 4, 5 through lines 8, 9 and passed through pumps 10, 11 and lines 14, 15 all respectively, to the gas generator 16. Combustion gas from the gas generator 16 passes through lines 19, 20, 21 and serves to pressurize the propellants in the containers 2, 3. Further gas from the gas generator passes through lines 25 and 22, that through line 25 passing to a turbine 12 which is connected to drive the propellant pumps 10, 11, the exhaust gases from the turbine passing through line 24 into the combustion chamber 1 where it is used to cool the wall thereof; the gas passing through line 22 passes to the combustion chamber 1 where it is utilized to provide blast atomization of the propellants. The combustion chamber is shown in Fig. 2 and comprises an end wall 29 formed with orifices 32, 33 for propellant injection. The propellant passing through line 4 passes through inlet 40 and thence through inclined passages 39 to swirl chambers 38 from which it discharges through the orifices 32. The propellant flowing through line 5 passes through inlet 37 to annular chamber 36 and thence through inclined passages 35 to swirl chambers 34 from which it discharges through the orifices 33. Combustion gas from the gas generator 16 flowing through the line 22 passes to annular chamber 42 from which it discharges through ducts 41 which are aligned with the injection orifices 32, 33 thus serving to atomize the propellants as they discharge into the combustion chamber. The exhaust gas from the turbine 12 passing through line 24 enters annular chamber 44, the gas discharging therefrom through passages 43 to provide a layer of relatively cool gas along the wall of the combustion chamber. A gas generator suitable for use with a mono-propellant is shown in Fig. 3, the gas generator being of cylindrical form and containing a suitable catalyst 53. Mono-propellant enters the gas generator through inlet 49 and the reaction gases discharge through outlet 50. Perforated screens 51, 52 are provided adjacent the inlet and outlet. A propellant container is shown in Fig. 4, the propellant storage space being indicated at 55 and being intially sealed by seals 60, 66. When pressurizing gas is supplied through inlet 65 to space 64, the seal 60 bursts and the propellant thus pressurized bursts the seal 66 and discharges through outlet 54. The supply of propellants through lines 14, 15 to the gas generator 16 Fig. 1 is controlled by means of spill valves 17, 18.