Patent application number | Description | Published |
20100275404 | ON-LINE CLEANING OF TURBINE HOT GAS PATH DEPOSITS VIA PRESSURE PULSATIONS - A method for removing hot gas deposits from a system via pressure pulses is provided. The method includes regulating a flow of a mixture of detonation fluid and oxidizer into an expansion chamber; and generating a detonation within the expansion chamber by igniting the mixture of detonation fluid and oxidizer in the expansion chamber producing a high-pressure wave, the high-pressure wave propagating along a fluid path of the system in a supersonic rate removing hot gas deposits in the fluid path while the system is in fired operation, the expansion chamber directing the high-pressure wave towards the fluid path of the system. | 11-04-2010 |
20110094232 | APPARATUS FOR CONDITIONING AIRFLOW THROUGH A NOZZLE - A nozzle includes a center body and a shroud surrounding the center body to define an annular passage. An arcuate annular guide extending from a point radially inward of the shroud to a point radially outward of the shroud defines a first airflow between the arcuate annular guide and the shroud and a second airflow between the arcuate annular guide and the center body. | 04-28-2011 |
20110179803 | BLED DIFFUSER FED SECONDARY COMBUSTION SYSTEM FOR GAS TURBINES - The present subject matter provides a system for modifying static pressure recoveries and emissions formation within a gas turbine. The system includes a bled diffuser positioned downstream from a compressor section of the gas turbine and a bleed duct extending from the bled diffuser. The bleed duct may be configured to direct bleed air from the pressurized airflow exiting the compressor section to a secondary combustion system located downstream from the main combustion system in a combustor. The bleed air flowing into the secondary combustion system may be mixed with fuel to form an air/fuel mixture. | 07-28-2011 |
20120036861 | METHOD FOR COMPENSATING FOR COMBUSTION EFFICIENCY IN FUEL CONTROL SYSTEM - Compensation is provided for a fuel demand signal of a gas turbine controller during transition between operating modes. The compensation adjusts fuel demand to account for combustion efficiency differences between the starting and ending operating mode that otherwise can lead to severe swings in combustion reference temperature and lean blowout. | 02-16-2012 |
20120055168 | SYSTEM AND METHOD FOR PRODUCING HYDROGEN RICH FUEL - A system for providing hydrogen enriched fuel includes first and second gas turbines. The second gas turbine receives a portion of compressed working fluid from the first gas turbine and produces a reformed fuel, and a fuel skid provides fluid communication between a turbine in the second gas turbine and a combustor in the first gas turbine. A method for providing hydrogen enriched fuel includes diverting a portion of a first compressed working fluid from a first compressor to a second compressor and providing a second compressed working fluid from the second compressor. The method further includes mixing a fuel with the second compressed working fluid in a reformer to produce a reformed fuel, flowing the reformed fuel through a second turbine to cool the reformed fuel, and connecting the second turbine to the second compressor so that the second turbine drives the second compressor. | 03-08-2012 |
20130098053 | SYSTEMS AND METHODS FOR USE IN OPERATING TURBINE ENGINES - A control system for use with a turbine engine that is configured to operate at a rated power output is provided. The control system includes a computing device that includes a processor that is programmed to calculate an amount of fluid to be supplied for combustion in the turbine engine. The processor is also programmed to designate at least one nozzle of a plurality of nozzles to receive the fluid. Moreover, the control system includes at least one control valve coupled to the computing device. The control valve is configured to receive at least one control parameter from the computing device for use in modulating the amount of the fluid to be channeled to the nozzle such that the rated power output is generated while emission levels are maintained below a predefined emissions threshold level. | 04-25-2013 |
20130177858 | COMBUSTOR AND METHOD FOR DISTRIBUTING FUEL IN THE COMBUSTOR - A combustor includes a plurality of tubes arranged in a tube bundle and supported by at least one plate that extends radially within the combustor, wherein each tube includes an upstream end axially separated from a downstream end and provides fluid communication through the tube bundle. A flow conditioner extends upstream from the upstream end of one or more of the plurality of tubes, and a radial passage extends through the flow conditioner. A method for distributing fuel in a combustor including flowing a working fluid through a flow conditioner that extends from a tube that is configured in a tube bundle comprising a plurality of tubes and that is supported by at least one plate. The flow conditioner includes at least one radial passage to impart radial swirl to the working fluid. Flowing a fuel through an annular insert that is at least partially surrounded by the flow conditioner. | 07-11-2013 |
20130192234 | BUNDLED MULTI-TUBE NOZZLE ASSEMBLY - A method for reducing emissions in a turbo machine is disclosed. The method includes providing fuel to a multi-tube nozzle and reducing the differences in the mass flow rate of fuel into each tube. An improved multi-tube nozzle is also disclosed. The nozzle includes an assembly that reduces the difference in the mass flow rate of fuel into each tube. | 08-01-2013 |
20130219899 | ANNULAR PREMIXED PILOT IN FUEL NOZZLE - A combustor for a gas turbine engine has a head end portion that carries at least one fuel/air nozzle. Each fuel/air nozzle includes a premixed pilot nozzle having premix conduits that are configured with concentric axes that direct the fuel/air mixture axially from the premixed pilot nozzle. The premixed pilot nozzle can include an annular channel disposed radially outwardly from the premix and including air jets that direct air radially outwardly from the premix conduits. | 08-29-2013 |
20130219912 | COMBUSTOR AND METHOD FOR PURGING A COMBUSTOR - A combustor includes an end cap. The end cap includes a first surface and a second surface downstream from the first surface, a shroud that circumferentially surrounds at least a portion of the first and second surfaces, a plate that extends radially within the shroud, a plurality of tubes that extend through the plate and the first and second surfaces, and a first purge port that extends through one or more of the plurality of tubes, wherein the purge port is axially aligned with the plate. | 08-29-2013 |
20130269359 | COMBUSTOR FLOW SLEEVE WITH SUPPLEMENTAL AIR SUPPLY - A gas turbine combustor includes a combustor liner enclosing a combustion chamber; at least one fuel nozzle arranged to provide fuel to the combustion chamber; a flow sleeve surrounding the combustor liner forming a passage radially between the combustor liner and the flow sleeve for supplying air to the combustion chamber, the flow sleeve configured to permit air to flow substantially axially into the passage via a substantially annular flow sleeve inlet. A downstream end of the flow sleeve is formed to include an annular manifold provided with plural outlets about a circumference of the downstream end of the flow sleeve and adapted to supply supplemental air from an external variable air source substantially radially into the passage to thereby maintain axial air flow boundary layer attachment at the flow sleeve inlet. | 10-17-2013 |
20130283810 | COMBUSTION NOZZLE AND A RELATED METHOD THEREOF - A combustion nozzle includes at least one passage having a mixing section and an exit section. The mixing section includes an air inlet, and a fuel inlet. The mixing section has a first length and a first diameter. The exit section has a second length different from the first length, and a second diameter different from the first diameter. | 10-31-2013 |
20130298561 | MULTI-TUBE FUEL NOZZLE WITH MIXING FEATURES - A system includes a multi-tube fuel nozzle having an inlet plate and a plurality of tubes adjacent the inlet plate. The inlet plate includes a plurality of apertures, and each aperture includes an inlet feature. Each tube of the plurality of tubes is coupled to an aperture of the plurality of apertures. The multi-tube fuel nozzle includes a differential configuration of inlet features among the plurality of tubes. | 11-14-2013 |
20130299602 | SYSTEM AND METHOD HAVING MULTI-TUBE FUEL NOZZLE WITH DIFFERENTIAL FLOW - A system includes a multi-tube fuel nozzle with a fuel nozzle body and a plurality of tubes. The fuel nozzle body includes a nozzle wall surrounding a chamber. The plurality of tubes extend through the chamber, wherein each tube of the plurality of tubes includes an air intake portion, a fuel intake portion, and an air-fuel mixture outlet portion. The multi-tube fuel nozzle also includes a differential configuration of the air intake portions among the plurality of tubes. | 11-14-2013 |
20130305738 | SYSTEM AND METHOD FOR PRODUCING HYDROGEN RICH FUEL - A system for providing hydrogen enriched fuel includes first and second gas turbines. The second gas turbine receives a fuel from a fuel supply and portion of compressed working fluid from the first gas turbine and produces a reformed fuel, and a fuel skid provides fluid communication between a turbine in the second gas turbine and a combustor in the first gas turbine. A method for providing hydrogen enriched fuel includes diverting a portion of a first compressed working fluid from a first compressor to a second compressor and providing a second compressed working fluid from the second compressor. Mixing a first portion of a compressed fuel with the second compressed working fluid in a reformer to produce a reformed fuel, flowing a second portion of the compressed fuel to a second turbine for cooling, and flowing the reformed fuel through the second turbine to cool the reformed fuel. | 11-21-2013 |
20130327050 | CONTROLLING FLAME STABILITY OF A GAS TURBINE GENERATOR - A method and apparatus for controlling a flame stability at a gas turbine generator is disclosed. The method includes forming combustible mixtures at a plurality of fuel nozzles of a combustor of the gas turbine generator; altering an oxygen concentration of at least one of the combustible mixtures at a selected fuel nozzle of the plurality of fuel nozzles; and burning the combustible mixtures at the plurality of fuel nozzles to control the flame stability at the gas turbine generator. | 12-12-2013 |
20130340404 | HOT EGR DRIVEN BY TURBOMACHINERY - In one embodiment, a system includes a turbine combustor of a turbine system with the turbine combustor at least partially enclosed within a compressor discharge casing. The turbine system also includes an exhaust gas recovery system that includes an exhaust gas recirculation duct. The exhaust gas recirculation duct is configured to recirculate exhaust gas from a downstream end of the turbine combustor to an upstream end of the turbine combustor. This exhaust gas recirculation duct is entirely enclosed within the compressor discharge casing. | 12-26-2013 |
20140000269 | COMBUSTION NOZZLE AND AN ASSOCIATED METHOD THEREOF | 01-02-2014 |
20140061327 | SYSTEM AND METHOD FOR STAGING FUEL TO A COMBUSTOR - A system for staging fuel to a combustor includes a fuel manifold with a plurality of valves. At least one fuel circuit provides fluid communication between the fuel manifold and a first set of fuel nozzles. A flow distribution valve is fluidly connected to one of the at least one fuel circuits between the fuel manifold and the first set of fuel nozzles. The flow distribution valve includes an inlet and at least two outlets. | 03-06-2014 |
20140157779 | SYSTEM FOR REDUCING COMBUSTION DYNAMICS AND NOx IN A COMBUSTOR - A combustor includes an end cap that extends radially across at least a portion of the combustor. The end cap includes an upstream surface axially separated from a downstream surface. A plurality of tubes extend from the upstream surface through the downstream surface of the end cap to provide fluid communication through the end cap. Each tube in a first set of the plurality of tubes has an inlet proximate to the upstream surface and an outlet downstream from the downstream surface. Each outlet has a first portion that extends a different axial distance from the inlet than a second portion. | 06-12-2014 |