FIELD: rocket equipment.
SUBSTANCE: invention relates to combustion engines of rocket engines. Combustion chamber and rocket engine comprises injection device (11) which injects oxidizing agent and fuel from injection surface (23), flame tube (12), in which a gaseous combustion product is formed by burning an oxidizing agent and fuel injected from injection device (11), resonator (31) connected to fire tube (12) via communication channel (35), and perforated plate (41) made in communication channel (35).
EFFECT: invention provides suppression of combustion oscillations.
8 cl, 9 dwg
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