FIELD: heating systems.
SUBSTANCE: combustion chamber of gas turbine engine, namely gas-turbine jet or turbo-propeller engine of aircraft, includes chamber bottom equipped with fuel injection devices and circular walls connecting the chamber bottom to internal and external attachment flanges to internal and external casings. Flanges include annular parts with holes provided for air passage, which cools components located behind. Holes at least of one of flanges are located in a staggered order and have triangular shape or actually triangular shape.
EFFECT: increasing cooling efficiency of combustion chamber with simultaneous increase in vibration resistance of flanges.
14 cl, 4 dwg
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