METHODS AND APPARATUS FOR COOLING TURBINE ENGINE COMBUSTOR EXIT TEMPERATURES

摘要

A combustor (16) for a gas turbine engine (10) includes an inner Liner {44), an outer liner (40) which defines a combustion chamber (54) therebetween, an outer support (42) radially outward from the outer liner such that an outer passageway (58) is defined between the outer support and the outer liner, and an inner support (46) radially inward from the inner liner such that an inner passageway (60) is defined between the inner support and the inner liner. At least one of the inner and outer supports includes at least two rows of impingement openings (140) arranged in an array (144) for channeling impingement cooling air toward at least one of the inner liner and the outer liner. At least one of the inner and outer liners includes at least one row of dilution openings (120) extending therethrough for channeling dilution cooling air into the combustion chamber.