FIELD: engines and pumps.
SUBSTANCE: proposed low-thrust rocket engine comprises engine chamber with mixing head, fire bottom, igniter with ignition chamber arranged along its axis, oxidiser swirl-type nozzle with tangential channels and swirling chamber. It comprises also fuel jet nozzles directed towards the axis that have axial and peripheral channels to communicate said swirling chamber with ignition chamber. In compliance with this invention, ignition chamber represents a semi-sphere, while axial channel has converging and diverging parts with minimum section there between. Fuel jet nozzles are directed at an angle to mixing head axis towards combustion chamber. Outlets of jet nozzles alternate with peripheral channel inlets and are located at the end of diverging part of axial channel, behind tangential channel outlets, right after skewed edge of said channels. Fire bottom represents a semi-sphere. Said fire bottom has tangential channels of curtain oxidizer, while jet nozzle axes are directed towards their outlets. Swirl-type nozzle tangential channels are arranged at an angle to swirling chamber axis and directed towards ignition. Split chamber housing consists of adapter, heatproof combustion chamber and nozzle, their joint being accommodated in oxidiser manifold.
EFFECT: higher reliability, increased specific thrust.
4 cl, 3 dwg
