APPARATUS AND METHOD FOR COOLING GAS TURBINE ENGINE COMBUSTORS

摘要

An apparatus and method fabricating a deflector-flare cone for a combustor is provided. The combustor includes an air swirler annular about a centerline axis of the combustor wherein the swirler includes an annular exit downstream of the swirler. The deflector-flare cone includes a single annular body including an engagement end configured to support the deflector-flare cone, an annular divergent portion extending downstream from the engagement end. The annular divergent portion includes a radially outer annular deflector portion and a radially inner annular flare cone portion that are separated by an annular gap extending between the deflector portion and the flare cone portion. The deflector-flare cone includes a plurality of cooling passages extending through the single annular body of the deflector-flare cone. The plurality of cooling passages are spaced circumferentially about the centerline axis and are configured to be coupled in flow communication with a cooling fluid source.