GB1200271A - Device for feeding an igniting agent for combustion chambers of liquid fuel rocket propulsion units - Google Patents

Abstract

1,200,271. 200, 271. Rocket engines - ignition arrangements. BÍLKOWG. m.b.H. Jan.24, 1968 [Feb.23, 1967], No.3796/68. Headings. F1J and F1L. The invention relates to a method of supplying an ignition agent into the combustion chamber of a liquid propellant rocket, the ignition agent reacting hyper golically with one of the liquid propellants. The invention also provides for the continuous flow of a purging agent through the ignition agent conduits during operation of the combustion chamber. A piston and cylinder assembly 1 is provided, the cylinder 2 being divided by the piston 3 into an ignition agent storage compartment 5 and a pressurizing compartment 4, the pressurizing fluid being the propellant fuel which is supplied under pressure from the tank 11 through line 10. An outlet 13 is provided through the end wall 12 of the ignition agent compartment 5, the outlet being controlled by a solenoid-operated twoway valve member 17. The valve member 17 is normally urged to the right by means of a spring 27 thus closing off the ignition agent outlet 13. In this position of the valve member a flow path is provided from the fuel tank 11 through line 25a, duct 29 in the closure member 26, chamber 28 and radial bores 30 to the annular space 31 thence through outlet 38 and line 25b to the inlet duct 32 in the head 33 of the combustion chamber 34. This circuit constitutes a purging circuit through which a small proportion of fuel flows when the combustion chamber is in normal operation. To start the operation, the switch 41 is closed thus energizing the solenoid 19 and causing the valve member 17 to move to the left to the position shown against the action of the spring 27 and thus opening the outlet 13. A quantity of ignition agent is forced from the compartment 5 by the pressure of fuel acting on the piston 3, the ignition agent flowing through line 25b and inlet 32 into the combustion chamber 34 where it reacts spontaneously with the other propellant, oxygen, already supplied to the chamber. Upon ignition, the electric circuit is broken and the valve member 17 moves to the right to close the outlet 13 of the ignition agent, at the same time opening the circuit 25 of the purging fluid so that a small portion of fuel flows continuously through the circuit 25 and into the inlet 32 into the combustion chamber, thus preventing the ignition agent circuit from becoming blocked. The main flow of fuel is through the line 10 to the combustion chamber head 33. The ignition agent may be aluminium triethyl which reacts spontaneously with oxygen.