LOW-THRUST LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER Russian patent published in 2016 - IPC F02K9/52 F02K9/62 

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry, particularly, to mixing and combusting processes in liquid-propellant rocket engine of low and super low thrust. Claimed combustion chamber consists of the chamber, mixing head casing with fuel components feed channels and fuel first component manifold with atomisers for chamber walls cooling directed to circular conical deflector and second component manifold communicated with the central mixer atomisers. In compliance with this invention, the first fuel component manifold is composed of female circular cavity around the second fuel component axial manifold. The first row of the first fuel component is directed radially to the circular deflector. The central mixer is composed of the jet atomisers directed to the second deflector shaped to two conjugating conical surfaces. The circular manifold jet atomisers of the first component are directed perpendicular to one of the latter. The axial manifold jet atomisers of the first component are directed perpendicular to the other said surface. The second deflector can have the surface shaped to torus sector while the atomisers are directed to said surface.

EFFECT: higher engine efficiency, perfected dynamic characteristics.

2 cl, 2 dwg