| CPC F02K 9/52 (2013.01) | 8 Claims |
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1. A chemical rocket propulsion system comprising:
a pressurized supply of a fuel propellant and a pressurized supply of an oxidizer propellant;
a combustion chamber comprising a wall defining a combustion chamber volume and a central axis extending through the combustion chamber volume;
at least one first injection nozzle for the fuel propellant mounted to the wall at a first azimuthal position about the central axis;
at least one second injection nozzle for the oxidizer propellant mounted to the wall of the combustion chamber at the first azimuthal position about the central axis such that the at least one first injection nozzle and the at least one second injection nozzle are aligned, and spaced apart, along the central axis in a direction parallel to the central axis and are oriented substantially transverse to the central axis;
wherein the wall lacks injection nozzles at all azimuthal positions about the central axis except the first azimuthal position;
wherein, during operation of the chemical rocket propulsion system, the at least one first injection nozzle and the at least one second injection nozzle are configured to inject the fuel propellant and the oxidizer propellant, respectively, to generate a pair of counter-rotating vortices within the combustion chamber which rotate about respective axis substantially parallel to the central axis; and
a downstream exhaust nozzle connected to the wall to receive exhaust gases from the combustion chamber.
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