FIELD: gas-turbine engine combustion chambers.
SUBSTANCE: proposed combustion chamber includes flame tubes located in air cavity between outer and inner casings; cooling cavities of flame tubes are diverging from inlet to outlet at ratio of cavity height at inlet H to cavity height at outlet h H/h=1.4-2.0. Radial fin on side of inlet to cooling cavity has thickened portion T relative to thickness t of flame tube wall between cooling cavities T/t=1.3-2.1. Angle between peripheral surface of cooling cavity and inner surface of flame tube wall between cooling cavities is α=8-12°. Ratio of diameter d of holes supplying air to cooling cavity to thickness t of flame tube wall is equal to d/t=0.7-1.4.
EFFECT: enhanced reliability; improved construction of combustion chamber.
2 dwg
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