Patent ID: 8127550
Filing Date: 2012-03-06
Classification: F23D,F23R

Abstract:
1. A gas turbine combustor comprising: a. a base plate having a body extending perpendicularly to a longitudinal flow-axis of the combustor to define a partial flow barrier and comprising at least one aperture for a main swirler assembly, a centrally disposed aperture for a pilot burner, and a plurality of axially-directed apertures for passage of fluid from an upstream side to a downstream side of the base plate; b. the main swirler assembly having an upstream end and a downstream end, the downstream end disposed in the at least one aperture; c. a structure adjacent the pilot burner aperture comprising a plurality of laterally-directed apertures effective to reduce the occurrence of undesired flashbacks on or near the base plate; and d. the base plate comprising a lip formed about the main swirler assembly aperture, the lip extending to the downstream side from the base plate body.