Abstract: A method of controlling a combustor of a gas turbine is disclosed. The method includes operatively disposing a combustor can in a combustor of a gas turbine. The combustor can comprising a plurality of combustor fuel nozzles, each having a fuel injector and configured to selectively provide a liquid fuel, a liquid fluid or liquid fuel and liquid fluid to a fuel injector nozzle that is configured to provide, respectively, a plurality of liquid fuel jets, a plurality of liquid fluid jets or a combination thereof, that are in turn configured to provide an atomized liquid fuel stream, an atomized liquid fluid stream, or an atomized and emulsified liquid fuel-liquid fluid stream, respectively. The method also includes selectively providing an amount of fuel, fluid or a combination thereof to the fuel injector nozzle to produce an atomized fuel stream, atomized fluid stream, or an atomized and emulsified fuel-fluid stream, respectively.

Abstract: A fuel injector nozzle is disclosed. The nozzle includes a nozzle body having a fuel conduit that extends from a fuel inlet through a fuel outlet conduit to a fuel outlet and a fluid conduit that extends from a fluid inlet through a fluid outlet conduit to a fluid outlet. The fuel outlet conduit and fuel outlet configured to produce a liquid fuel jet from the fuel outlet upon introduction of a pressurized liquid fuel into the fuel conduit. The fluid outlet conduit and fluid outlet are configured to produce a liquid fluid jet from the fluid outlet upon introduction of a pressurized liquid fluid into the fluid conduit, wherein the liquid fuel jet and the liquid fluid jet are configured to impact one another and produce a flow stream of atomized fuel.

Abstract: A fuel injector nozzle is disclosed. The nozzle includes a nozzle body for fluid communication of a liquid fuel to produce a liquid fuel jet and a fluid to produce a fluid jet. The nozzle body includes an adapter comprising a fuel conduit and a fluid conduit. The nozzle body also includes a nozzle tip disposed on the adapter comprising a plurality of fuel outlet conduits that are in fluid communication with the fuel conduits and a plurality of fluid outlet conduits that are in fluid communication with the fluid conduits.

Abstract: A turbomachine includes a compressor, a turbine operatively connected to the compressor, and a combustion assembly fluidly connected between the compressor and the turbine. The combustion assembly includes an end cover including a plurality of fuel circuits, a fuel distributing flange fluidly connected to at least one of the plurality of fuel circuits, a nozzle assembly fluidly linked to the at least one of the plurality of fuel circuits, and a fuel distribution system configured and disposed to deliver fuel to the fuel distributing flange. The fuel distribution system is selectively activated to stage fuel delivery to the at least one of the plurality of fuel circuits at a pressure sufficient to achieve atomization at the nozzle assembly without requiring a supplemental atomization air flow prior to delivering fuel to others of the plurality of fuel circuits at a pressure to achieve atomization without requiring a supplemental atomization air flow.

Abstract: An insert for pre-mixing a secondary fuel in a pre-mixing annulus of a fuel nozzle assembly is disclosed. The insert includes a cartridge extending through at least a portion of the fuel nozzle assembly and configured to flow the secondary fuel therethrough. The insert further includes an adapter coupled to the cartridge, the adapter defining a fuel plenum and at least one radially extending injection bore. The at least one injection bore is configured to accept at least a portion of the secondary fuel from the cartridge and inject the secondary fuel into the pre-mixing annulus.

Abstract: A fuel injector nozzle is disclosed. The nozzle includes a nozzle body for fluid communication of a liquid fuel to produce a liquid fuel jet and a fluid to produce a fluid jet. The nozzle body includes an adapter comprising a fuel conduit and a fluid conduit. The nozzle body also includes a nozzle tip disposed on the adapter comprising a plurality of fuel outlet conduits that are in fluid communication with the fuel conduits and a plurality of fluid outlet conduits that are in fluid communication with the fluid conduits.

Abstract: A method of controlling a combustor of a gas turbine is disclosed. The method includes operatively disposing a combustor can in a combustor of a gas turbine. The combustor can comprising a plurality of combustor fuel nozzles, each having a fuel injector and configured to selectively provide a liquid fuel, a liquid fluid or liquid fuel and liquid fluid to a fuel injector nozzle that is configured to provide, respectively, a plurality of liquid fuel jets, a plurality of liquid fluid jets or a combination thereof, that are in turn configured to provide an atomized liquid fuel stream, an atomized liquid fluid stream, or an atomized and emulsified liquid fuel-liquid fluid stream, respectively. The method also includes selectively providing an amount of fuel, fluid or a combination thereof to the fuel injector nozzle to produce an atomized fuel stream, atomized fluid stream, or an atomized and emulsified fuel-fluid stream, respectively.

Abstract: A fuel injector nozzle is disclosed. The nozzle includes a nozzle body having a fuel conduit that extends from a fuel inlet through a fuel outlet conduit to a fuel outlet and a fluid conduit that extends from a fluid inlet through a fluid outlet conduit to a fluid outlet. The fuel outlet conduit and fuel outlet configured to produce a liquid fuel jet from the fuel outlet upon introduction of a pressurized liquid fuel into the fuel conduit. The fluid outlet conduit and fluid outlet are configured to produce a liquid fluid jet from the fluid outlet upon introduction of a pressurized liquid fluid into the fluid conduit, wherein the liquid fuel jet and the liquid fluid jet are configured to impact one another and produce a flow stream of atomized fuel.

Abstract: A turbomachine includes a compressor, a turbine operatively connected to the compressor, and a combustion assembly fluidly connected between the compressor and the turbine. The combustion assembly includes an end cover including a plurality of fuel circuits, a fuel distributing flange fluidly connected to at least one of the plurality of fuel circuits, a nozzle assembly fluidly linked to the at least one of the plurality of fuel circuits, and a fuel distribution system configured and disposed to deliver fuel to the fuel distributing flange. The fuel distribution system is selectively activated to stage fuel delivery to the at least one of the plurality of fuel circuits at a pressure sufficient to achieve atomization at the nozzle assembly without requiring a supplemental atomization air flow prior to delivering fuel to others of the plurality of fuel circuits at a pressure to achieve atomization without requiring a supplemental atomization air flow.