Cooling for a combustion chamber for rockets

The combustion chamber has a cooling unit and an inner combustion chamber wall. The wall has recesses, which are formed so that a stable border layer of the gas flow, which is formed near the inner wall when the combustion chamber is operational, is destabilized in the area of the recesses. The depth of the recesses corresponds to half the thickness of the inner combustion chamber wall, and at most to the thickness o the border layer. The recesses are formed by angled grooves.