Patent GB-1211841-A (GB)
Title: Fluid propulsion mechanisms for rockets
IPC: F02K9/48
Filed: 1964-11-13
Abstract: 1,211,841. Rocket propulsion. BÍLKOW G.m.b.H. Nov.13, 1964[Dec.21, 1963], No.46415/64. Heading F1J. In a fluid rocket propulsion mechanism, preliminary combustion takes place in two chambers, in the one with a surplus of oxidant and in the other with a surplus of fuel, the gases from which after combustion drive a turbine or turbines, which in turn drive pumps for the propellant components, before being fed into a main combustion chamber or chambers. In the embodiment shown in Fig.1, there are two preliminary combustion chambers 1, 2 coaxial with a main combustion chamber 3. Chamber 1 is fed with fuel, e.g. liquid hydrogen, through conduits 4 and with a surplus of oxidant, e.g. liquid oxygen, through conduits 5, the mixture formed being ignited by an ignition device 6. The resultant gases, which have a high oxidant content, flow through a guide ring 7 and a turbine 8, the latter driving a pump 10 through a shaft 9. The pump 10 draws in oxidant through an inlet 11 and this is forced through pipes 11a, a distributer 12 and conduits 5, 13 into both of the preliminary combustion chambers 1, 2. Chamber 2 is fed with a surplus of fuel through conduits 14 and the mixture formed in this chamber is ignited by an ignition device 15. The resultant gases, which have a high fuel content, flow through a guide ring 16 and a turbine 17, the latter driving a pump 19 through a hollow shaft 18 mounted concentrically of the shaft 9. The pump 19 draws in fuel through an inlet 20 and this is forced through conduits 20a to the cooling system 24 of the main combustion chamber 3, then through a distributer 22 to conduits 4, 14 and into both of the preliminary combustion chambers 1, 2. To enable the proportions of fuel and oxidant mixture in the preliminary combustion chambers 1, 2 to be controlled as desired, regulators 23 are provided for controlling the amount of oxidant fed to the chamber 2, and regulators 24 for controlling the amount of fuel fed to the chamber 1. The gases from the chambers 1, 2 pass through conduits 25, 26 into the main combustion chamber 3 where they burn up while acting as hypergoles. The pipe 27 which separates the conduits 25, 26 is hollow and is cooled by causing a small proportion of the oxidant taken from tapping points 29 of the conduits 5 to pass through it and to emerge at the end 28 to enter the chamber 3. Alternatively, the desired cooling could be obtained if the propellant component not required for the cooling of the chamber 3, in this case the oxidant, is conveyed either wholly or in part through a "forward flow system" provided in the wall of the pipe 27 to the end of the pipe and then, without entering the chamber 3, through a "reverse flow system", likewise provided in the wall of the pipe, to one or both of the preliminary combustion chambers 1, 2. In two further embodiments, the gases from two coaxial preliminary combustion chambers are fed separately to drive a single turbine which in turn drives pumps for both fuel and oxidant Figs. 2 and 3 (not shown) while in another embodiment, two preliminary combustion chambers are mounted side by side with two main combustion chambers following them Fig. 4 (not shown).