Method for mixing a dilution air in a sequential combustion system of a gas turbine

Abstract

The invention concerns a method for mixing a dilution air with a hot main flow in sequential combustion system of a gas turbine, wherein the gas turbine essentially comprises at least one compressor, a first combustor which is connected downstream to the compressor, and the hot gases of the first combustor are admitted to at least one intermediate turbine or directly or indirectly to at least one second combustor. The hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor runs under a caloric combustion path having a can-architecture. At least one dilution air injection is introduced into the first combustor, and wherein the direction of the dilution air injection is directed against or in the direction of the original swirl flow inside of the first combustor.

1 . A method for mixing a dilution air with a hot main flow in a sequential combustion system of a gas turbine, wherein the gas turbine essentially comprises at least one compressor, a first combustor which is connected downstream to the compressor, and the hot gases of the first combustor are admitted to at least one intermediate turbine or directly or indirectly to at least one second combustor, wherein the hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor runs under a caloric combustion path having a can architecture, and wherein at least one dilution air injection is introduced into the first combustor, and wherein the resulting swirl flow through the dilution air injection is directed against or in the direction of the original swirl flow inside of the first combustor. 
     
     
         2 . The method as claimed in  claim 1 , wherein the first and second combustor run under a caloric combustion path having a can-architecture. 
     
     
         3 . The method as claimed in  claim 1 , wherein the first combustor runs under a caloric combustion path having an annular architecture, and the second combustor runs under a caloric combustion path having a can-architecture. 
     
     
         4 . The method as claimed in  claim 1 , wherein the first combustor runs under a caloric combustion path having a can-architecture, and the second combustor runs under a caloric combustion path having an annular architecture. 
     
     
         5 . The method as claimed in  claim 1 , wherein that at least one combustor runs under a caloric combustion path having an annular architecture. 
     
     
         6 . A dilution air injector for implementing a method for mixing a dilution air with a hot main flow in a sequential combustion system of a gas turbine, wherein the gas turbine essentially comprises at least one compressor, a first combustor which is connected downstream to the compressor, and the hot gases of the first combustor are admitted to at least one intermediate turbine or directly or indirectly to at least one second combustor, wherein the hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor runs under a caloric combustion path having a can architecture, and wherein the first combustor comprising tangential air inlet slots forming a swirl flow directed against or in direction of the original main swirl flow inside of the first combustor. 
     
     
         7 . The dilution air injector as claimed in  claim 6 , wherein the first combustor runs under a caloric combustion path having an annular architecture, and the second combustor runs under a caloric combustion path having a can-architecture. 
     
     
         8 . The dilution air injector as claimed in  claim 6 , wherein the first combustor runs under a caloric combustion path having a can-architecture, and the second combustor runs under a caloric combustion path having an annular architecture. 
     
     
         9 . The dilution air injector as claimed in  claim 6 , wherein that at least one combustor runs under a caloric combustion path having an annular architecture. 
     
     
         10 . The dilution air injector as claimed  claim 6  wherein the first combustor comprising at least one injector, wherein the direction and/or intensity of the injected air along the first combustion chamber are subject to regulation. 
     
     
         11 . The dilution air injector as claimed in  claim 6  wherein that the injector comprising means for regulating the intensity of the selected dilution air injection or for an additional supporting dilution air. 
     
     
         12 . A combustor as claimed in  claim 6  wherein at least one combustor comprising a burner consisting of hollow part-cone bodies making up a complete body, having tangential air inlet slots and feed channels for gaseous and liquid fuels, wherein in that the centre axes of the hollow part-cone bodies have a cone angle increasing in the direction of flow and run in the longitudinal direction at a mutual offset, wherein a fuel nozzle, which fuel injection is located in the middle of the connecting line of the mutually offset centre axes of the part-cone bodies, is placed at the burner head in the conical interior formed by the part-cone bodies. 
     
     
         13 . A combustor as claimed in one of  claims 6  to  11 , characterized in that at least one combustor comprising a burner for a combustion air flow and means for injection of fuel, substantially consisting of a swirl generator, which substantially consisting of hollow part-cone bodies making up a complete body, having tangential air inlet slots and feed channels for gaseous and liquid fuels, wherein in that the centre axes of the hollow part-cone bodies have a cone angle increasing in the direction of flow and run in the longitudinal direction at a mutual offset, wherein a fuel nozzle, which fuel injection is located in the middle of the connecting line of the mutually offset centre axes of the part-cone bodies, is placed at the burner head in the conical interior formed by the part-cone bodies, and as well of a mixing path provided downstream of said swirl generator, wherein said mixing path comprises transaction ducts extending within a first part of the path in the flow direction for transfer of a flow formed in said swirl generator into the cross-section of flow of said mixing path, that joins downstream of said transition ducts.