A turbomachine combustor assembly includes a combustor body (20), and a combustor liner (24) arranged within the combustor body (20). The combustor liner (24) defines a combustion chamber (30) having a head end (32) and a discharge end (37). A plurality of combustor nozzles (44-49) are arranged in an annular array at the head end (32) of the combustion chamber (30), and a fluid delivery nozzle (90) is arranged substantially centrally within the annular array at the head end (32) of the combustion chamber (30). The fluid delivery nozzle (90) includes a first end portion (98) that extends to a second end portion (99) through a wall portion (100). The wall portion (100) includes at least one combustion chamber outlet (113). The fluid delivery nozzle (90) is configured to deliver a non-combustible fluid into the at least one of the plurality of combustor nozzles (44-49) and the combustion chamber (30).
申请公布号
WO2013147633(A1)
申请公布日期
2013.10.03
申请号
WO2012RU00232
申请日期
2012.03.29
申请人
GENERAL ELECTRIC COMPANY;SOKOLOV, ALEXANDER NIKOLAY;TRETYAKOV, DMITRY VLADIMIROVICH;SLOBODYANSKIY, ILYA ALEKSANDROVICH
发明人
SOKOLOV, ALEXANDER NIKOLAY;TRETYAKOV, DMITRY VLADIMIROVICH;SLOBODYANSKIY, ILYA ALEKSANDROVICH