FIELD: heating systems.
SUBSTANCE: gas-turbine engine combustion liner consists of at least two shells the ends of which are located coaxially relative to each other thus forming a convergent annular duct. The end of the shell restricting the duct on external side is equipped with forges uniformly located in a circumferential direction thus forming the openings. Forges come into contact with the end of the other shell, and each of the forges has an inclined end wall with a hole mostly of an oval shape. Total area of openings and holes is at least 1, 2 times larger than the duct exit area. Ratio of duct height to its length is 1/3-1/6.
EFFECT: intensifying the cooling process of shells of combustion liner, and eliminating their distortion in all operating modes of combustion chamber.
3 dwg
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