| 摘要 |
<p>A gas turbine combustor (10) includes a combustion chamber (39) defined by a combustor liner (38), the combustor liner having an upstream end cover (30) supporting one or more nozzles (32) arranged to supply fuel to the combustion chamber where the fuel mixes with air supplied from a compressor. A transition duct (20) is connected between a downstream end of the combustion chamber liner and a first stage turbine nozzle (50, 52, 54) the transition duct supplying gaseous products of combustion to said first stage turbine nozzle. One or more additional fuel injection nozzles (56, 58) is arranged at an aft end of the transition duct (20) for introducing additional fuel and air for combustion into the transition duct (20) upstream of the first stage turbine nozzle.
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