FIELD: heating.
SUBSTANCE: annular combustion chamber of gas turbine engine consists of bottom wall passing transversely relative to lengthwise axis of combustion chamber and of side walls passing in lengthwise direction from said bottom wall arranged in forward in flow part of combustion chamber and up to outlet opening of combustion products exhaust flow; outlet opening is located in backward in flow part of combustion chamber. The side walls contain at least one row of openings of air supply for diluting the flow of gaseous combustion products. At least one opening of dilution has a forward in flow edge projecting inward the combustion chamber and backward in flow edge projecting outward the combustion chamber and non-central with the forward in flow edge relative to a plane transverse to the wall. The opening has an axis oriented along a certain direction inclined towards the wall at a certain angle and passing into the side of the internal cavity and in the direction of backward in flow part of the combustion chamber.
EFFECT: facilitating optimisation of air flow supply to combustion chamber.
22 cl, 20 dwg
