| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a can-type combustor configured for late fuel injection for management of the combustor exit temperature profile. <P>SOLUTION: A gas turbine combustor includes a combustion chamber defined by a combustor liner, the 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 20 is connected between an aft end of the combustion chamber liner and first stage turbine nozzles 50, 52, 54, the transition duct supplying gaseous products of combustion to the first stage turbine nozzle. One or more additional fuel injection nozzles 56, 58 are arranged at an aft end of the transition duct 20 for introducing additional fuel to be combusted into the transition duct 20 in an upstream end of the first stage turbine nozzle. <P>COPYRIGHT: (C)2012,JPO&INPIT |
