FIELD: rocket equipment.
SUBSTANCE: invention relates to rocketry. Combustion chamber consists of a chamber forming a combustion chamber cavity with a hermetically sealed mixing head body with fuel components supply channels, central jet nozzle of the first fuel component (fuel) and peripheral jet nozzles of the second component (oxidant), directed to the axis of a central injector. Fuel supply channel is made in the form of a capillary tube with a jet nozzle at the outlet; capillary tube extends into the combustion chamber. Oxidizer feed channel is also made in the form of a capillary tube protruding into the combustion chamber cavity; the capillary tube passes into an annular element, wherein the axis of symmetry of the annular element coincides with the axis of the central jet nozzle. Injection nozzles made in the annular element tube walls are directed towards the central axis of the jet nozzle. Capillary tube of the oxidant can pass into a spiral with number of turns of not less than one. Besides, the capillary tube of the oxidant can pass into the toroid.
EFFECT: invention improves dynamic nature of low-thrust liquid-propellant engine (LTLPE), improves thermal condition of the injector head and increases efficiency of the LTLPE.
3 cl, 2 dwg
