FIELD: rocket engines of space flying vehicle control systems.
SUBSTANCE: proposed chamber has housing, mixing head with injectors for feeding the oxidizer and fuel at acute angle on inner surface of combustion chamber and nozzle. Axes of oxidizer and fuel injectors lie in radial planes and cross the inner surface of combustion chamber at two levels: oxidizer at one level and fuel at other level. Oxidizer and fuel injectors may lie in pairs in one plane or separately in alternating radial planes. Planes of location of oxidizer and fuel injectors may alternate over circumference at regular pitch.
EFFECT: enhanced efficiency of thermal protection by means of film cooling.
4 cl, 6 dwg
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