FIELD: rocket engine combustion chambers.
SUBSTANCE: the combustion chamber for a rocket engine used for production of the jet thrust due to the efflux of hot gas flow, has a cooling system, as well as an inner wall that adjoins the cooling system from the inner side of the combustion chamber. According to the invention, the inner wall of the combustion chamber has recesses that are made so as to aerodynamically destabilize in the area of these recesses the stable boundary layer of gas flow formed at operation of the combustion chamber at its inner wall.
EFFECT: enhanced heat absorption by the cooling system.
10 cl, 7 dwg
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