Abstract: A gas turbine system includes a fuel nozzle. The fuel nozzle includes a first fluid conduit defining a first fuel passage, a second fluid conduit defining a second fuel passage, and a third fluid conduit defining an oxidant passage. A first plurality of orifices is disposed along the first fluid conduit and is configured to fluidly couple the first fuel passage to the oxidant passage. A second plurality of orifices is disposed on the third fluid conduit and is configured to fluidly couple the second fuel passage to the oxidant passage. A first diameter of the first plurality of orifices is less than a second diameter of the second plurality of orifices.

Abstract: A micromixer of a turbine system is provided and the micromixer includes a plurality of pipes each having an inlet and an outlet for receiving flow and dispersing the flow to a combustor. Also provided is a non-uniform inlet arrangement defined by the inlets of the plurality of pipes, wherein at least one of the inlets extends to an axial location distinct from at least one other inlet.

Abstract: A combustor includes a cap assembly that extends radially across at least a portion of the combustor, wherein the cap assembly includes an upstream surface axially separated from a downstream surface, and a combustion chamber downstream from the cap assembly. A plurality of tubes extend from the upstream surface through the downstream surface of the cap assembly, and each tube provides fluid communication through the cap assembly to the combustion chamber. The downstream surface is sloped at an angle with respect to the upstream surface.

Abstract: An injector includes a surface and an injector hole formed in the surface. The injector also includes a groove formed in the surface, the groove surrounding the injector hole.

Abstract: A system includes a fuel supply system. The fuel supply includes a primary fuel supply, a fuel additive supply, and a common pipeline coupled to the primary fuel and fuel additive supplies. The primary fuel supply includes a primary fuel having a first average molecular weight. The fuel additive includes a fuel additive having a second molecular weight that is greater than the first average molecular weight. The common pipeline is configured to direct a mixture of the primary fuel and the fuel additive into a fuel nozzle.

Abstract: A gas turbine system includes a fuel nozzle. The fuel nozzle has a first wall extending along an axis and defines a first fluid passage. A second wall surrounds the first wall and defines a second fluid passage. A third wall surrounds the second wall and defines a third fluid passage. The first and second fluid passages are configured to collectively direct a flow of air and fuel into a combustion region to produce a flame. The third fluid passage is configured to direct a diluent into the combustion region to adjust a combustion parameter of the flame.

Abstract: A gas turbine system includes a fuel nozzle. The fuel nozzle includes a first fluid conduit defining an oxidant passage, a second fluid conduit defining a first fuel passage, and a third fluid conduit surrounding the second fluid conduit and defining a second fuel passage. A first orifice is disposed on the second fluid conduit and is configured to fluidly couple the first fuel passage to the oxidant passage. A second orifice is disposed on the third fluid conduit and is configured to fluidly couple the second fuel passage to the oxidant passage. A first diameter of the first orifice is less than a second diameter of the second orifice.

Abstract: A system includes a turbine combustor containing a first wall portion disposed about a combustion zone, a second wall portion disposed about the first wall portion, and a plurality of vanes disposed within an annulus between the first and second wall portions. The plurality of vanes is configured to swirl air flowing within the annulus.

Abstract: Circumferential fluid distribution in an annulus can be made more uniform with an annulus coupleable with a feed supply pipe, where the apparatus includes a plurality of inlets arrayed in the annulus and receives fluid from the feed supply pipe, and a plurality of outlets connected to the annulus and delivering fluid radially inward from the annulus. The inlets distribute fluid in the annulus to the outlets. The inlets and the outlets are configured such that a fluid static pressure in the annulus is substantially consistent.

Abstract: A combustor includes a cap assembly that extends radially across at least a portion of the combustor, wherein the cap assembly includes an upstream surface axially separated from a downstream surface, and a combustion chamber downstream from the cap assembly. A plurality of tubes extend from the upstream surface through the downstream surface of the cap assembly, and each tube provides fluid communication through the cap assembly to the combustion chamber. The downstream surface is sloped at an angle with respect to the upstream surface.

Abstract: A nozzle includes a center body and a shroud circumferentially surrounding at least a portion of the center body to define an annular passage between the center body and the shroud. A plurality of apertures pass through the center body to the annular passage, and a plenum extends inside the center body and is in fluid communication with the plurality of apertures. A cooling medium is in fluid communication with the plenum. A method for cooling a nozzle includes flowing a cooling medium through a plenum across a surface of the nozzle.

Abstract: A turbomachine combustor includes a combustor cap having a cap surface and a wall that define, at least in part, a resonator volume. A plurality of injection nozzle members extend from the cap surface. Each of the plurality of injection nozzle members include an inner nozzle member and a plurality of outer nozzle members. An adjustable conduit extends through the wall into the resonator volume. The adjustable conduit includes an internal passage having a dimensional parameter. A combustor dynamics mitigation system is operably connected to the combustor cap. The combustor dynamics mitigation system includes a controller configured and disposed to control one a size of the resonator volume and the dimensional parameter of the adjustable conduit to modify combustor dynamics in the combustor.

Abstract: A nozzle includes a center body that defines an axial centerline and a shroud circumferentially surrounding at least a portion of the center body to define an annular passage between the center body and the shroud. A plurality of vanes between the center body and the shroud comprise a radially outward portion separated from the shroud. A method for enhancing flow through a nozzle includes flowing a fuel through a center body and flowing a fluid stream across a vane located between the center body and a shroud surrounding at least a portion of the center body. The method further includes flowing the fluid stream between a radially outward portion of the vane and the shroud, wherein the radially outward portion of the vane is separated from the shroud.

Abstract: A micromixer of a turbine system is provided and the micromixer includes a plurality of pipes each having an inlet and an outlet for receiving flow and dispersing the flow to a combustor. Also provided is a non-uniform inlet arrangement defined by the inlets of the plurality of pipes, wherein at least one of the inlets extends to an axial location distinct from at least one other inlet.

Abstract: A swirler assembly in a gas turbine combustor includes a hub, a shroud, and a plurality of vanes connected between the hub and the shroud. A vane angle of the plurality of vanes is adjustable.

Abstract: A turbomachine combustor assembly includes a combustor body, a combustor liner arranged within the combustor body and defining a combustion chamber, a fluid passage defined between the combustor body and the combustor liner, and an annular flow conditioning member arranged in the fluid passage and extending about the combustor liner.

Abstract: A turbomachine combustor includes a combustor cap having a cap surface and a wall that extends about the cap surface to define a cap volume, and a plurality of nozzle members that extend from the cap surface. The plurality of nozzle members include a center nozzle member and one ore more outer nozzle members. A combustor dynamics mitigation system is arranged in the combustor cap and includes plurality of divider members that extend from the wall toward the center nozzle member. The plurality of divider members define a plurality of parallel resonator volumes. The combustor dynamics mitigation system also includes a plurality of tubes that extend into corresponding ones of the plurality of parallel resonator volumes.

Abstract: Disclosed is a cross flow apparatus including a surface and at least one outlet located at the surface. The cross flow apparatus further includes at least one guide at the surface configured to direct an intersecting flow flowing across the surface and increase a velocity of a cross flow being expelled from the at least one outlet downstream from the at least one outlet.

Abstract: A nozzle includes a center body that defines an axial centerline and a shroud circumferentially surrounding at least a portion of the center body to define an annular passage between the center body and the shroud. A plurality of vanes between the center body and the shroud comprise a radially outward portion separated from the shroud. A method for enhancing flow through a nozzle includes flowing a fuel through a center body and flowing a fluid stream across a vane located between the center body and a shroud surrounding at least a portion of the center body. The method further includes flowing the fluid stream between a radially outward portion of the vane and the shroud, wherein the radially outward portion of the vane is separated from the shroud.

Abstract: A nozzle includes a center body and a shroud circumferentially surrounding at least a portion of the center body to define an annular passage between the center body and the shroud. The nozzle further includes apertures through at least one of the center body or shroud, a plenum in fluid communication with the apertures, and a louvers proximate to the apertures and connected to at least one of the center body or shroud. A method for cooling a nozzle includes flowing a cooling medium through a plenum inside a center body of the nozzle and flowing the cooling medium through apertures in the center body. The method further includes redirecting the cooling medium with louvers to flow the cooling medium across a surface of the center body.