FIELD: engines and pumps.
SUBSTANCE: rocket engine combustion chamber cooling system comprises combustion chamber and nozzle. The latter comprises, in its turn, a converging and a diverging sections and nozzle throat there between. Said sections are composed of outer and inner shells with permanent invariable-depth ribs to make a cooling circuit. Besides, they have at least one curtain belt with tangential bores and manifold. Ring part is arranged inside said manifold. In compliance with this invention said ring part is shaped to half-torus with chamber. Inlet tangential bores to swirl coolant flow are made at ring part in plane perpendicular to combustion chamber axis. Outlet bores are made parallel with combustion chamber axis. Flow turbulence promoters are made at ring part outer surface ahead of tangential bores. Curtain belt is made at joint between combustion chamber and nozzle or at nozzle converging part, or two curtain belts are made.
EFFECT: better cooling of nozzle mouth, higher engine specific thrust.
5 cl, 8 dwg
