Patent ID: 8082739
Filing Date: 2011-12-27
Classification: F23R

Abstract:
1. A gas turbine combustor comprising: a combustion chamber defined by a combustor liner, said combustor liner having an upstream end cover supporting one or more nozzles arranged to supply fuel to the combustion chamber where the fuel mixes with air supplied from a compressor; a transition duct connected between a downstream end of said combustor liner and a first stage turbine nozzle, said transition duct supplying gaseous products of combustion to said first stage turbine nozzle; and a plurality of fuel injection nozzles arranged at an aft end of said transition duct for introducing additional fuel and air for combustion into said transition duct upstream of said first stage turbine nozzle, said plurality of fuel injection nozzles located proximate to and circumferentially between vanes of said first stage turbine nozzle, wherein each of said plurality of fuel injection nozzles is formed with an open end to draw air from surrounding compressor discharge air, and a swirler for mixing the compressor discharge air with fuel supplied to said plurality of fuel injection nozzles.