Abstract: An injection assembly for a gas turbine combustor having a liner defining a combustion zone and a secondary combustion zone and a forward casing circumferentially surrounding at least a portion of the liner is provided. The injection assembly includes a thimble assembly and an injector unit. The thimble assembly, which is mounted to the liner, includes a thimble that extends through a thimble aperture in the liner. The injector unit, which is mounted to and extends through the forward casing, includes an injector blade that extends into the thimble. The injection assembly introduces a flow of fuel into a flow of air flowing through the thimble, such that fuel and air are injected into the secondary combustion zone in a direction transverse to a flow of combustion products from the primary combustion zone.

Abstract: A thimble assembly, which directs fluid flow through a combustor liner, includes a thimble boss and a thimble. The thimble boss is mounted an outer surface of the liner and surrounds a liner opening, thus defining a thimble boss passage. The thimble is disposed through the passage and the liner opening. The thimble wall extends from an inlet portion to an outlet of the thimble. The inlet portion has a greater diameter than the outlet and defines an inlet plane and a parallel intermediate plane. A terminal plane, parallel to the intermediate plane, includes an array of points most distant from a corresponding array of points defining the intermediate plane. The thimble wall has a non-uniform length, such that the outlet of the thimble is oriented at an oblique angle relative to the terminal plane. The thimble wall may have an arcuate shape defined as one-fourth of an ellipse.

Abstract: A fuel injector is provided for the radial introduction of a liquid fuel/air mixture to a combustor. The fuel injector includes a body having a frame that defines an inlet portion and an outlet member that defines an outlet portion. A fuel plenum is defined within the outlet member, and a fuel injection port, which communicates with the fuel plenum, is defined through the outlet member. A fuel supply conduit, fixed to the body, communicates between a source of liquid fuel and the fuel injection port, via the fuel plenum. Alternately, the fuel injector may include a swirl-inducing device mounted to the outlet member in communication with the fuel injection port, and a fuel supply conduit fixed to the swirl-inducing device. In this embodiment, the fuel supply conduit communicates between the fuel injection port and a source of a liquid fuel and water mixture, via the swirl-inducing device.

Abstract: An injection assembly for a gas turbine combustor having a liner defining a combustion zone and a secondary combustion zone and a forward casing circumferentially surrounding at least a portion of the liner is provided. The injection assembly includes a thimble assembly and an injector unit. The thimble assembly, which is mounted to the liner, includes a thimble that extends through a thimble aperture in the liner. The injector unit, which is mounted to and extends through the forward casing, includes an injector blade that extends into the thimble. The injection assembly introduces a flow of fuel into a flow of air flowing through the thimble, such that fuel and air are injected into the secondary combustion zone in a direction transverse to a flow of combustion products from the primary combustion zone.

Abstract: A thimble assembly, which directs fluid flow through a combustor liner, includes a thimble boss and a thimble. The thimble boss is mounted an outer surface of the liner and surrounds a liner opening, thus defining a thimble boss passage. The thimble is disposed through the passage and the liner opening. The thimble wall extends from an inlet portion to an outlet of the thimble. The inlet portion has a greater diameter than the outlet and defines an inlet plane and a parallel intermediate plane. A terminal plane, parallel to the intermediate plane, includes an array of points most distant from a corresponding array of points defining the intermediate plane. The thimble wall has a non-uniform length, such that the outlet of the thimble is oriented at an oblique angle relative to the terminal plane. The thimble wall may have an arcuate shape defined as one-fourth of an ellipse.

Abstract: A fuel injector is provided for the radial introduction of a liquid fuel/air mixture to a combustor. The fuel injector includes a body having a frame that defines an inlet portion and an outlet member that defines an outlet portion. A fuel plenum is defined within the outlet member, and a fuel injection port, which communicates with the fuel plenum, is defined through the outlet member. A fuel supply conduit, fixed to the body, communicates between a source of liquid fuel and the fuel injection port, via the fuel plenum. Alternately, the fuel injector may include a swirl-inducing device mounted to the outlet member in communication with the fuel injection port, and a fuel supply conduit fixed to the swirl-inducing device. In this embodiment, the fuel supply conduit communicates between the fuel injection port and a source of a liquid fuel and water mixture, via the swirl-inducing device.

Abstract: A gas turbine wet compression system using electrohydrodynamic (EHD) atomization is disclosed. In one embodiment, the wet compression system includes: a gas turbine system including an air inlet duct, and a plurality of electrohydrodynamic (EHD) nozzles coupled to a water supply, the plurality of EHD nozzles configured to provide a water-spray for reducing a temperature of inlet air drawn into the air inlet duct. In another embodiment, a wet compression system for a gas turbine system includes: a plurality of electrohydrodynamic (EHD) nozzles, and a water supply in fluid communication with the plurality of EHD nozzles.

Abstract: An on-line wash system for a compressor including: a nozzle including a flow passage for wash liquid, wherein the flow passage is configured to be coupled to a source of a wash liquid and includes a discharge outlet arranged to project the wash liquid into a stream of working fluid for the turbomachine; an electrode proximate to the flow passage of the nozzle, wherein the electrode is configured to form an electrical field sufficient to charge the wash liquid flowing through the passage and the charge applied to the wash liquid is of a first polarity, and a surface of the compressor charged with the first polarity, wherein the surface is exposed to the stream of working fluid and downstream of the nozzle.

Abstract: A turbomachine system according to an embodiment includes: a gas turbine system including a compressor component, a combustor component, and a turbine component; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; a fluid injection system for injecting a fluid into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

Abstract: A system for injecting a liquid fuel into a combustion gas flow field includes an annular liner that defines a combustion gas flow path. The annular liner includes an inner wall, an outer wall and a fuel injector opening that extends through the inner wall and the outer wall. The system further includes a gas fuel injector that is coaxially aligned with the fuel injector opening. The gas fuel injector includes an upstream end and a downstream end. The downstream end terminates substantially adjacent to the inner wall. A dilution air passage is at least partially defined by the gas fuel injector. A liquid fuel injector extends partially through the dilution air passage. The liquid fuel injector includes an injection end that terminates upstream from the inner wall.

Abstract: A turbomachine system according to an embodiment includes: a gas turbine system including a compressor component, a combustor component, and a turbine component; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; a fluid injection system for injecting a fluid into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

Abstract: A fuel nozzle and a method for operating a combustor are disclosed. The method includes flowing a fuel and an oxidizer through a fuel nozzle, the fuel nozzle comprising an inner tube, an intermediate tube, and an outer tube each configured for flowing one of the fuel or the oxidizer therethrough. At least one of the inner tube, the intermediate tube, or the outer tube includes a plurality of swirler vanes. The method further includes imparting a swirl to the fuel and the oxidizer in the fuel nozzle, and exhausting the fuel and the oxidizer from the fuel nozzle into a combustion zone.

Abstract: A system for reducing emissions includes a gas production source that produces nitrogen oxides, sulfur oxides, hydrogen sulfide, sulfuric acid, nitric acid, formaldehyde, benzene, metal oxides, or volatile organic compound emissions. An exhaust plenum is downstream from the gas production source, and structure for dispersing a solvent is in the exhaust plenum. A collection tank is in fluid communication with the exhaust plenum to receive the solvent from the exhaust plenum, and a heat source is in the exhaust plenum downstream from the structure for dispersing the solvent. A method for reducing emissions from a gas production source includes flowing exhaust gases through an exhaust plenum, dispersing a solvent through a nozzle in the exhaust plenum, collecting the dispersed solvent in a collection tank, and heating the exhaust gases flowing through the exhaust plenum downstream from the nozzle.

Abstract: A heat recovery steam generator (HRSG) is coupled to a gas turbine engine that discharges a flow of exhaust gases including oxides of nitrogen (NOx). The HRSG includes a steam-based heating element for heating the exhaust gases, and at least one NOx reduction element coupled downstream from the at least one steam-based heating element and configured to facilitate reducing an amount of NOx in the exhaust gases that are channeled into the at least one NOx reduction element.

Abstract: A system for pre-heating a working fluid within a combustor includes a compressor for providing the working fluid to the combustor. An outer casing is disposed downstream from the compressor. The outer casing at least partially defines a high pressure plenum that at least partially surrounds the combustor. A combustion chamber is defined within the combustor downstream from the high pressure plenum. A catalytic combustor is disposed within the high pressure plenum upstream from the combustion chamber so as to provide thermal energy to the working fluid upstream from the combustion chamber.

Abstract: A flame detector in photonic communication with a no-flame region of a combustor of a gas turbine may emit a signal when a photon is detected. A controller may be arranged to receive a signal from the flame detector and may determine whether a flame presence in the no-flame region is indicated responsive to the signal.

Abstract: Methods and systems are provided for reducing NOx emissions from a gas stream produced by a production source. The method may comprise oxidizing a substantial portion of NO gas present in the gas stream by contacting the gas stream with an oxidation catalyst to yield higher order NxOy molecules; and thereafter removing higher order NxOy molecules from the gas stream by solvent absorption or reaction. The system may comprise a gas production source configured to produce a gas stream comprising NOx; an oxidation catalyst positioned downstream of the gas production source, wherein the oxidation catalyst is configured to oxidize NO gas molecules in the gas stream to yield higher order NxOy molecules; and a removal device positioned downstream of the oxidation catalyst configured to remove higher order NxOy molecules from the gas stream by solvent absorption or reaction.

Abstract: A combustor for a gas turbine includes a fuel nozzle having a central swirler that circumferentially surrounds a downstream end of the fuel nozzle. A primary combustion zone is defined within the central swirler. The combustor further includes an outer swirler that circumferentially surrounds at least a portion of the central swirler and a venturi that is disposed downstream from the primary combustion zone. The venturi includes an inner surface. The central swirler imparts angular swirl to a compressed working fluid so as to rapidly mix and react the fuel rich primary zone products with the working fluid. The outer swirler imparts angular swirl to a compressed working fluid so as to provide a cooling boundary layer along the inner surface of the venturi.

Abstract: A system includes a catalytic reactor configured to mount to a combustor. The catalytic reactor includes a catalyst configured to reduce emissions associated with combustion in the combustor. The catalytic reactor also includes a first and a second sacrificial coating disposed over the catalyst prior to mounting of the catalytic reactor into the combustor, wherein the first and second sacrificial coatings are removable while the catalytic reactor is mounted to the combustor without damaging the catalyst.

Abstract: First and second combustors are provided, and each combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. Each fuel nozzle includes an axially extending center body, a shroud that circumferentially surrounds at least a portion of the center body, and vanes that extend radially between the center body and the shroud. A first fuel port through at least one of the vanes is located at a first axial distance from the combustion chamber, a second fuel port through the center body is located at a second axial distance from the combustion chamber, and the vanes are located at a third axial distance from the combustion chamber. The system varies one or more of the first, second, and third axial distances from combustor-to-combustor to produce a combustion instability frequency in the first combustor that is different from the combustion instability frequency in the second combustor.