Abstract: The present disclosure is directed to a combustor including an annularly shaped liner that at least partially defines a hot gas path of the combustor and a flow sleeve that circumferentially surrounds at least a portion of the liner. The flow sleeve is radially spaced from the liner to form a cooling flow annulus therebetween. A plurality of fuel injector assemblies circumferentially spaced about the flow sleeve and each fuel injector assembly extends radially through the flow sleeve, the cooling flow annulus and the liner. A first portion of the flow sleeve defined between a first pair of circumferentially adjacent fuel injector assemblies of the plurality of fuel injector assemblies bulges radially outwardly with respect to an outer surface of the liner so as to enlarge a flow volume of the cooling flow annulus.

Abstract: A sleeve assembly for a combustion system is provided. The sleeve assembly includes a liner defining a combustion chamber having a flow axis and a primary combustion zone. The liner has a forward end and an aft end such that the liner circumscribes the flow axis. The sleeve assembly also includes a shell circumscribing the liner such that a cooling duct is defined between the liner and the shell. The shell includes a unisleeve having a forward end and an aft end. The aft end of the unisleeve is positioned axially upstream of the aft end of the liner, defining a gap between the aft end of the liner and the aft end of the unisleeve. The unisleeve is mounted to the liner at circumferentially spaced locations along an axial plane between the forward end and the aft end of the unisleeve.

Abstract: A combustor cap assembly includes an impingement plate coupled to an annular shroud and a cap plate which is coupled to the impingement plate to form an impingement air plenum therebetween. The combustor cap assembly further includes a flow conditioning plate coupled to a forward end portion of the shroud. The flow conditioning plate includes an inner band portion, an outer band portion and an annular portion. The annular portion defines a plurality of flow conditioning passages. The inner band portion at least partially defines a cooling air plenum within the combustor cap assembly. The inner band portion defines an exhaust channel which is in fluid communication with the impingement air plenum and an exhaust outlet. The flow conditioning plate further defines a cooling air passage which provides for cooling air flow into the cooling air plenum.

Abstract: A combustor cap assembly includes an impingement plate coupled to an annular shroud and a cap plate which is coupled to the impingement plate and forms an impingement air plenum therebetween. The cap assembly further includes a flow conditioning plate which is coupled to a forward end portion of the shroud. The flow conditioning plate includes an inner band portion, an outer band portion and an annular portion which extends radially therebetween. The annular portion includes upstream side, a downstream side and a plurality of flow conditioning passages which provide for fluid communication through the upstream and downstream sides. The inner band portion of the flow conditioning plate at least partially defines an exhaust channel. The exhaust channel is in fluid communication with the impingement air plenum and an exhaust outlet. The exhaust outlet is positioned to route cooling air from the impingement air plenum into an annular flow passage defined within a combustor.

Abstract: The present disclosure is directed a combustor. The combustor includes an annularly shaped liner having a downstream end that is rigidly connected to an aft frame. A flow sleeve circumferentially surrounds at least a portion of the liner and is radially spaced from the liner to form a cooling flow annulus therebetween. A plurality of fuel injector assemblies is circumferentially spaced about the flow sleeve. Each fuel injector assembly extends radially through the flow sleeve and the liner. Each fuel injector assembly is rigidly connected to the flow sleeve and to the liner. An aft portion of the flow sleeve terminates axially short of the aft frame to form an axial gap between the aft end and the aft frame to allow for unrestrained axial expansion and contraction of the aft end.

Abstract: The present disclosure is directed to a combustor including an annularly shaped liner that at least partially defines a hot gas path of the combustor and a flow sleeve that circumferentially surrounds at least a portion of the liner. The flow sleeve is radially spaced from the liner to form a cooling flow annulus therebetween. A plurality of fuel injector assemblies circumferentially spaced about the flow sleeve and each fuel injector assembly extends radially through the flow sleeve, the cooling flow annulus and the liner. A first portion of the flow sleeve defined between a first pair of circumferentially adjacent fuel injector assemblies of the plurality of fuel injector assemblies bulges radially outwardly with respect to an outer surface of the liner so as to enlarge a flow volume of the cooling flow annulus.

Abstract: The present disclosure is directed to a system for mounting an axially staged fuel injector assembly. The system includes an annularly shaped liner that at least partially defines a hot gas path of a combustor. The liner defines an injector opening that extends radially through the liner. A flow sleeve circumferentially surrounds at least a portion of the liner and is radially spaced from the liner to form a cooling flow annulus therebetween. An annular injector boss extends radially from the liner through the flow sleeve. The injector boss includes a first end portion that extends circumferentially about the injector opening and a second end portion that is disposed radially outwardly from an outer surface of the flow sleeve. The injector boss is formed to receive a fuel injector. The present disclosure is also directed to a method for mounting an axially staged fuel injector.

Abstract: A sleeve assembly for a combustion system is provided. The sleeve assembly includes a liner defining a combustion chamber having a flow axis and a primary combustion zone. The liner has a forward end and an aft end such that the liner circumscribes the flow axis. The sleeve assembly also includes a shell circumscribing the liner such that a cooling duct is defined between the liner and the shell. The shell includes a unisleeve having a forward end and an aft end. The aft end of the unisleeve is positioned axially upstream of the aft end of the liner, defining a gap between the aft end of the liner and the aft end of the unisleeve. The unisleeve is mounted to the liner at circumferentially spaced locations along an axial plane between the forward end and the aft end of the unisleeve.

Abstract: A combustor cap assembly includes an impingement plate coupled to an annular shroud and a cap plate which is coupled to the impingement plate and forms an impingement air plenum therebetween. The cap assembly further includes a flow conditioning plate which is coupled to a forward end portion of the shroud. The flow conditioning plate includes an inner band portion, an outer band portion and an annular portion which extends radially therebetween. The annular portion includes upstream side, a downstream side and a plurality of flow conditioning passages which provide for fluid communication through the upstream and downstream sides. The inner band portion of the flow conditioning plate at least partially defines an exhaust channel. The exhaust channel is in fluid communication with the impingement air plenum and an exhaust outlet. The exhaust outlet is positioned to route cooling air from the impingement air plenum into an annular flow passage defined within a combustor.

Abstract: A combustor cap assembly includes an impingement plate coupled to an annular shroud and a cap plate which is coupled to the impingement plate to form an impingement air plenum therebetween. The combustor cap assembly further includes a flow conditioning plate coupled to a forward end portion of the shroud. The flow conditioning plate includes an inner band portion, an outer band portion and an annular portion. The annular portion defines a plurality of flow conditioning passages. The inner band portion at least partially defines a cooling air plenum within the combustor cap assembly. The inner band portion defines an exhaust channel which is in fluid communication with the impingement air plenum and an exhaust outlet. The flow conditioning plate further defines a cooling air passage which provides for cooling air flow into the cooling air plenum.

Abstract: Embodiments of the present disclosure are directed towards a turbine combustor probe having a combustion dynamics monitoring probe configured to monitor combustion dynamics within a turbine combustor. The turbine combustor probe also has a gas sampling sleeve configured to collect a gas sample from an airflow path between a liner and a flow sleeve of the turbine combustor.

Abstract: A liner stop for retaining a flow sleeve relative to a combustion liner in a combustor is disclosed. The liner stop includes a female component defining a recess and a male component comprising a protrusion, the protrusion insertable in the female component. The liner stop further includes an insert disposable between the female component and the male component, the insert comprising a surface protrusion configured to interfere with one of the female component or the male component.

Abstract: A late lean injection (LLI) manifold is provided and includes a central nozzle and first and second side nozzles positioned at circumferential locations defined around a vessel, a connector, a first leg, to which the connector is connected, formed to define a tube extending from the central nozzle to the first side nozzle such that fuel is communicable between the connector, the central nozzle and the first side nozzle and a second leg. The second leg is formed to define a tube extending from the central nozzle to the second side nozzle such that the fuel is communicable between the central nozzle and the second side nozzle.

Abstract: A liner stop for retaining a flow sleeve relative to a combustion liner in a combustor is disclosed. The liner stop includes a female component defining a recess and a male component comprising a protrusion, the protrusion insertable in the female component. The liner stop further includes an insert disposable between the female component and the male component, the insert comprising a surface protrusion configured to interfere with one of the female component or the male component.

Abstract: Embodiments of the present disclosure are directed towards a turbine combustor probe having a combustion dynamics monitoring probe configured to monitor combustion dynamics within a turbine combustor. The turbine combustor probe also has a gas sampling sleeve configured to collect a gas sample from an airflow path between a liner and a flow sleeve of the turbine combustor.

Abstract: A late lean injection (LLI) manifold is provided and includes a central nozzle and first and second side nozzles positioned at circumferential locations defined around a vessel, a connector, a first leg, to which the connector is connected, formed to define a tube extending from the central nozzle to the first side nozzle such that fuel is communicable between the connector, the central nozzle and the first side nozzle and a second leg. The second leg is formed to define a tube extending from the central nozzle to the second side nozzle such that the fuel is communicable between the central nozzle and the second side nozzle.