Patent ID: 7513098

Claim:
A gas turbine can-annular combustor comprising: a main swirler assembly comprising: i. an inner body comprising a front end and an exhaust end defining an axis of axial flow therebetween for passage of a fuel/air mixture during operation of the gas turbine; ii. swirler flow conditioning members disposed about the axis of axial flow of the inner body: iii. a sleeve, comprising an upstream end and a downstream end, disposed peripherally about the inner body and wherein the exhaust end of the inner body extends into the sleeve through its upstream end, therebetween defining a first peripheral air entry, and the sleeve additionally comprising a plurality of spaced apart tabs projecting substantially axially from the downstream end, each of said tabs adapted to engage a respective portion along an opening of a base plate, the sleeve further comprising a second peripheral air entry defined by gaps between the spaced apart tabs, and b. a base plate extending transversely across the combustor to form a barrier comprising a lateral edge defining an opening for the main swirler assembly, the lateral edge receiving the downstream end of the sleeve, wherein combined air flows from the first and said second peripheral air entries are effective during operation to reduce or eliminate flashback.