FIELD: aeronautical engineering; combustion chambers of hypersonic ramjet engines. SUBSTANCE: device includes main nozzle, shell, pipe line with additional nozzle for delivery of liquid or gaseous fuel. Nozzle-throat diameter of additional nozzle is equal to 0.1-0.2 of nozzle-throat diameter of main nozzle. Distance between throat diameters of additional nozzle. EFFECT: enhanced efficiency of stabilization of diffusion combustion. 4 dwg
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