Abstract: A turbine to detect a flame holding event includes a combustion section to receive a fluid from a compressor, to heat the fluid by combusting a fuel to generate heat, and to output the heated fluid to a turbine section. The combustion section includes a combustor having a combustion chamber in which the fuel is combusted, and the combustion section having a sensor to sense a static pressure within the combustion chamber. A combustion control device detects a flame holding event in the combustion chamber based only on the sensed static pressure.

Abstract: The present application provides a premixer for a combustor. The premixer may include a fuel plenum with a number of fuel tubes and a burner tube with a number of air tubes. The fuel tubes extend about the air tubes.

Abstract: The present application provides a liquid fuel heating system for heating a flow of fuel for a gas turbine engine. The liquid fuel system may include a flow of steam, an ejector/eductor in communication with the flow of fuel and the flow of steam for mixing therewith, and a high pressure pump downstream of the ejector/eductor.

Abstract: A system may detect a flame about a fuel nozzle of a gas turbine. The gas turbine may have a compressor and a combustor. The system may include a first pressure sensor, a second pressure sensor, and a transducer. The first pressure sensor may detect a first pressure upstream of the fuel nozzle. The second pressure sensor may detect a second pressure downstream of the fuel nozzle. The transducer may be operable to detect a pressure difference between the first pressure sensor and the second pressure sensor.

Abstract: A system including a primary manifold adapted to receive an ammonia feed and a distribution array coupled to the primary manifold to receive the ammonia feed from the primary manifold is provided. The distribution array includes a first supply tube extending approximately perpendicular to the primary manifold and a first plurality of injection tubes extending perpendicularly from the first supply tube. Each injection tube of the first plurality of injection tubes includes a plurality of apertures configured to expel the ammonia feed from the distribution array along a length of the first supply tube.

Abstract: A system includes a gas production source configured to produce a gas stream comprising nitrogen oxides (NOx) and a hydrocarbon injector disposed downstream of the gas production source and configured to inject a hydrocarbon into the gas stream. The hydrocarbon is configured to oxidize molecules of the NOx in the gas stream to produce a higher order compound of nitrogen and oxygen (NyOz). The system also includes a removal device disposed downstream of the hydrocarbon injector. The removal device is configured to remove the NyOz from the gas stream via absorption or reaction.

Abstract: A method for reducing the amount of carbon monoxide and oxygen emissions in a hydrocarbon combustor in a gas turbine engine by feeding hydrocarbon fuel and an oxidizer component into the head end of the combustor while also injecting substantially inert gas into the combustor with the fuel and oxidizer; forming a combustor exhaust stream that mixes with the recycle; cooling the combustor exhaust; detecting the amount of carbon monoxide and oxygen in the exhaust and adjusting the amount of fuel, oxidizer and inert gas feeds based on the detected amounts.

Abstract: The present application provides a premixer for a combustor. The premixer may include a fuel plenum with a number of fuel tubes and a burner tube with a number of air tubes. The fuel tubes extend about the air tubes.

Abstract: A power generation system capable of eliminating NOx components in the exhaust gas by using a 3-way catalyst, comprising a gas compressor to increase the pressure of ambient air fed to the system; a combustor capable of oxidizing a mixture of fuel and compressed air to generate an expanded, high temperature exhaust gas; a gas turbine engine that uses the force of the high temperature gas; an exhaust gas recycle (EGR) stream back to the combustor; a 3-way catalytic reactor downstream of the gas turbine engine outlet which treats the exhaust gas stream to remove substantially all of the NOx components; a heat recovery steam generator (HRSG); an EGR compressor; and an electrical generator.

Abstract: A system for operating a combustor includes a sensor that measures an operating parameter associated with the combustor and generates a signal reflective of the operating parameter. The operating parameter is reflective of an ash deposition rate or an accumulated ash buildup. A controller receives the signal, compares the signal to a predetermined limit, and generates a control signal. A method for operating a combustor includes operating the combustor at a first power level that produces a first temperature that is less than or equal to a first predetermined temperature and creating a layer of ash. The method further includes measuring an operating parameter reflective of an ash deposition rate or an accumulated ash buildup, comparing the operating parameter to a limit, and operating the combustor at a second power level that produces a second temperature that is greater than or equal to the first predetermined temperature.

Abstract: A combustor includes an end cover having a nozzle. The nozzle has a front end face and a central axis. The nozzle includes a plurality of fuel passages and a plurality of oxidizer passages. The fuel passages are configured for fuel exiting the fuel passage. The fuel passages are positioned to direct fuel in a first direction, where the first direction is angled inwardly towards the center axis. The oxidizer passages are configured for having oxidizer exit the oxidizer passages. The oxidizer passages are positioned to direct oxidizer in a second direction, where the second direction is angled outwardly away from the center axis. The plurality of fuel passages and the plurality of oxidizer passages are positioned in relation to one another such that fuel is in a cross-flow arrangement with oxidizer to create a burning zone in the combustor.

Abstract: In a gas turbine engine that includes a compressor and a combustor, wherein the combustor includes a primary fuel injector within a fuel nozzle and a secondary fuel injector that is upstream of the fuel nozzle and configured to inject fuel into a flow annulus of the combustor, a method for detecting a flame holding condition about a fuel injector. The method may include the steps of: detecting an upstream pressure upstream of the secondary fuel injector; detecting a downstream pressure downstream of the secondary fuel injector; determining a measured pressure difference between the upstream pressure and the downstream pressure; and comparing the measured pressure difference to an expected pressure difference.

Abstract: A method for regenerating oxide coatings on selected gas turbine engine components in situ, comprising the steps of defining an exhaust gas recirculation (EGR) loop for the gas turbine engine, identifying one or more target locations within the EGR loop for purposes of monitoring the level of metal oxide degradation occurring in key gas turbine engine components over time, collecting and analyzing data corresponding to the level of metal oxide degradation with a fixed time period at each of the target locations, determining which ones of the target locations within the EGR loop require oxide regeneration using injected oxygen, and controlling the amount of oxygen injection at the target locations sufficient to regenerate the metal oxide coatings to desired levels.

Abstract: The present application provides a premixer for a combustor. The premixer may include a fuel plenum with a number of fuel tubes and a burner tube with a number of air tubes. The fuel tubes extend about the air tubes.

Abstract: Methods and apparatuses are provided for protecting a catalyst within a combustor. In one embodiment, a catalytic reactor includes a protective coating that may be chemically removed or mechanically removed while the catalytic reactor is disposed in a combustor.

Abstract: A combustor nozzle includes a fuel supply in fluid communication with a fuel passage that terminates at a fuel outlet. An oxidant supply is in fluid communication with an oxidant passage radially displaced from the fuel passage and that terminates at an oxidant outlet radially displaced from the fuel outlet. A diluent passage radially displaced from the fuel passage and the oxidant passage terminates at a diluent outlet disposed between the fuel outlet and the oxidant outlet. A method for supplying fuel to a combustor includes flowing the fuel through a fuel outlet and flowing an oxidant through an oxidant outlet radially displaced from the fuel outlet. The method further includes flowing a diluent through a diluent outlet radially disposed between the fuel outlet and the oxidant outlet.

Abstract: A turbomachine includes a compressor, a combustor operatively connected to the compressor, and an injection nozzle operatively connected to the combustor. The injection nozzle includes a main body having a first end section that extends to a second end section to define an inner flow path. The injection nozzle further includes an outlet arranged at the second end section of the main body, at least one passage that extends within the main body and is fluidly connected to the outlet, and at least one conduit extending between the inner flow path and the at least one passage.

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: The present application provides a stoichiometric exhaust gas recovery turbine system. The stoichiometric exhaust gas recovery turbine system may include a main compressor for compressing a flow of ambient air, a turbine, and a stoichiometric exhaust gas recovery combustor. The stoichiometric exhaust gas recovery combustor may include a combustion liner, an extended flow sleeve in communication with the main compressor, and an extraction port in communication with the turbine. The extended flow sleeve receives the flow of ambient air from the main compressor so as to cool the combustion liner and then the flow of ambient air splits into an extraction flow to the turbine via the extraction port and a combustion flow within the combustion liner.

Abstract: A combustor includes an end cover having a nozzle. The nozzle has a front end face and a central axis. The nozzle includes a plurality of fuel passages and a plurality of oxidizer passages. The fuel passages are configured for fuel exiting the fuel passage. The fuel passages are positioned to direct fuel in a first direction, where the first direction is angled inwardly towards the center axis. The oxidizer passages are configured for having oxidizer exit the oxidizer passages. The oxidizer passages are positioned to direct oxidizer in a second direction, where the second direction is angled outwardly away from the center axis. The plurality of fuel passages and the plurality of oxidizer passages are positioned in relation to one another such that fuel is in a cross-flow arrangement with oxidizer to create a burning zone in the combustor.