Patent ID: 11920543
Assignee: RADIAN AEROSPACE INC.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B | IPC B  F

Claim 0:
1. A rocket propulsion system, comprising:
a combustion chamber having a curved, inwardly-facing chamber wall enclosing a combustion zone, the combustion chamber having a generally spherical shape with the curved, inwardly-facing chamber wall exposed to the combustion zone; and
a propellant injector coupled to the combustion chamber and having at least one fuel injector nozzle positioned to direct a flow of cooling fuel tangentially relative to the curved, inwardly-facing chamber wall;
wherein the at least one fuel injector nozzle includes a spray ring having a plurality of orifices;
wherein the propellant injector includes:
a movable fuel piston; and
a movable oxidizer piston;
wherein the oxidizer piston includes an oxidizer piston wall around an oxidizer passageway, the oxidizer piston wall comprises a fuel piston channel extending within the oxidizer piston wall, and the fuel piston is movable within the fuel piston channel.