Patent ID: 9310082
Filing Date: 2016-04-12
CPC Classification: F23R

Claim Text:
1. A combustor for a gas turbine, comprising: a. fuel nozzle having a downstream end; b. a central swirler, wherein the central swirler is at least partially defined by an inner liner that surrounds the downstream end of the fuel nozzle, an intermediate linter that surrounds the inner liner and a plurality of turning vanes that extends between the inner liner and the intermediate liner, wherein a downstream trailing end of the inner liner and a downstream trailing end of the intermediate liner converge radially inwardly towards an axial centerline of the combustor; c. a primary combustion zone defined by the inner liner of the central swirler; d. an outer swirler, outside of the intermediate liner, that circumferentially surrounds at least a portion of the central swirler; e. a venturi downstream from the primary combustion zone, the venturi haying an inner surface; and f. wherein the plurality of turning vanes of the central swirler imparts angular swirl to a compressed working fluid to react with a fuel rich mixture from the primary combustion zone and the outer swirler imparts angular swirl to a compressed working fluid to provide a cooling boundary layer along the inner surface of the venturi.