Patent ID: 9562690
Date: 2017-02-07
CPC Classifications: F23R

Claim:
1. A combustor for a gas turbine engine comprising: a circumferentially extending inner liner; a circumferentially extending outer liner spaced radially outward from and circumscribing the inner liner; a radially and axially stepped annular bulkhead extending between an upstream end of the inner liner and an upstream end of the outer liner, the stepped bulkhead having a radially inwardmost first bulkhead segment, a radially intermediate second bulkhead segment disposed axially downstream of the first bulkhead segment, and a third radially outermost bulkhead segment disposed axially downstream of the second bulkhead segment; a plurality of first fuel and air admission assemblies disposed in the first bulkhead segment; a plurality of second fuel and air admission assemblies disposed in the second bulkhead segment; and a plurality of third fuel and air admission assemblies disposed in the third bulkhead segment, at least one of the plurality of first, second and third fuel and air admission assemblies including a swirler body defining a unitary fuel and air mixing chamber extending from an upstream end, defined by a forward member, to a downstream end having an opening and with first and second inner air passages in fluid communication with each other in a single interior passage without any partition therebetween, the first and second air passages in communication with first and second air inlets opening radially into the single interior passage, the single interior passage opening into the upstream end of the mixing chamber.