FIELD: combustion chambers of turbo- jet engines; aircraft stationary gas-turbine plants. SUBSTANCE: proposed combustion chamber of gas-jet engine includes circular diffuser, casing, envelopes, flame tube and injectors. Outer wall of diffuser has closed circular cavity formed by load- bearing and perforated walls which are communicated with cavity of flow section of diffuser by various perforations. Perforated wall is made flush with diffuser profile and load-bearing wall is located at distance from it. EFFECT: enhanced operational stability. 3 cl, 4 dwg
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