Patent ID: 8850819

Claim:
An air swirler assembly for a gas turbine combustor comprising: a swirler body defining a unitary fuel and air mixing chamber defined at an upstream end by a forward member, having an open downstream end, and extending along a central longitudinal axis, said swirler body having a first inner air passage opening radially into an upstream end of the mixing chamber proximate the forward member, a second inner air passage opening radially into the mixing chamber downstream of the first inner air passage, and an outer air passage opening externally of the mixing chamber and coaxially about the downstream open end of the mixing chamber; wherein an air flow passing through the second inner air passage has a swirl imparted thereto that is counter-directional to a swirl imparted to an air flow passing through the first inner air passage, and wherein the first inner air passage and the second inner air passage are both embodied within a single interior passage opening into the upstream end of the mixing chamber proximate the forward member.