Class / Patent application number | Description | Number of patent applications / Date published |
060390530 | With addition of steam and/or water | 24 |
20080216461 | Micro Gas Turbine System - A micro gas turbine system is provided which increases power generation efficiency and output of power generation by means of water spray and which can exercise effective water spray control with simple control. The micro gas turbine system, according to the present invention, including a compressor, a combustor, a regenerative heat exchanger, a generator and a power transducer is provided with a plurality of spray water supply lines which include spray water nozzles and shutoff valves and which supply a prescribed amount of spray water by opening and closing the shutoff valves. | 09-11-2008 |
20090038287 | HIGH HUMIDITY GAS TURBINE EQUIPMENT - A high humidity gas turbine equipment includes a turbine; a compressor; a humidifier, which brings the air compressed by the compressor into contact with feed water to humidify the air; a regenerative heat exchanger, which causes the air humidified by the humidifier to be heated by exhaust gas from the turbine; a combustor, which burns the air heated by the regenerative heat exchanger and fuel to generate the combustion gas; a deaerating equipment including a deaerating section, a water storage tank, and a steam generating section, which causes feed water and makeup water in the water storage tank to be heated by exhaust gas from the turbine to evaporate and supplies the steam to the deaerating section; and a feed water supply pipe, through which the feed water and the makeup water in the water storage tank are supplied to the humidifier. | 02-12-2009 |
20090056303 | COOLING APPARATUS, GAS TURBINE SYSTEM USING COOLING APPARATUS, HEAT PUMP SYSTEM USING COOLING SYSTEM, COOLING METHOD, AND METHOD FOR OPERATING COOLING APPARATUS - The amount of water to be injected in an intercooler is controlled to cool the compressed gas to the saturation temperature. It is difficult to adjust the amount of the water to be injected, however, since the temperature of the compressed gas at an intercooler outlet is actually higher than the saturation temperature. An intercooling system is configured so as to cool a gas to the saturation temperature without controlling the amount of water injection and thereby maintain the reliability of the compressor while improving the cooling efficiency. | 03-05-2009 |
20090145100 | RADIAL STAGING METHOD AND CONFIGURATION OF A LIQUID INJECTION SYSTEM FOR POWER PLANTS - A turbine power plant employs a radial staging of a liquid injection system to provide a uniform fluid distribution, for use in wet compression. The liquid injection system includes a hub to be coupled to an air intake case of a turbine power plant. An annular ring assembly is spaced radially outwardly from the hub. Spray bars are spoked about the hub and the annular ring. The spray bars each include a body portion having an inner end coupled to the hub and an outer end coupled to the ring assembly. The spray bars each have at least two nozzle assemblies along the body portion. The spray bars each define at least two liquid supply manifolds each having an inlet at the annular ring assembly and an outlet at an associated nozzle assembly. The liquid supply manifolds each supply liquid to one or more associated nozzle assemblies. | 06-11-2009 |
20090320440 | WET COMPRESSION SYSTEMS IN TURBINE ENGINES - A wet compression system for a gas turbine compressor having a bellmouth that includes a plurality of nozzles for spraying a fine spray of liquid disposed within an aft section of the bellmouth. The aft section of the bellmouth may include a downstream half of the bellmouth, and the nozzles may be connected to a plurality of struts, each of the struts comprising a structural member that connects an inner diameter casing of the bellmouth to an outer diameter casing of the bellmouth. In some embodiments, the nozzles may be positioned on a leading edge of at least one of the struts and a minimum clearance of at least approximately 0.2 m may be maintained between the nozzles and the inner diameter casing of the bellmouth. In other embodiments, the nozzles may be positioned on a trailing edge of at least one of the struts and a minimum clearance of at least approximately 0.05 m may be maintained between the nozzles and the inner diameter casing of the bellmouth. | 12-31-2009 |
20100077720 | METHODS OF REDUCING EMISSIONS FOR A SEQUENTIAL COMBUSTION GAS TURBINE AND COMBUSTOR FOR A GAS TURBINE - In an SEV combustor and a method for reducing emissions in an SEV combustor of a sequential combustion gas turbine, an air/fuel mixture is combusted in a first burner and the hot gases are subsequently introduced into the SEV combustor ( | 04-01-2010 |
20100089020 | METERING OF DILUENT FLOW IN COMBUSTOR - Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A circumferentially adjustable collar is located at the at least one baffle hole between the baffle plate and the at least one fuel nozzle. A plurality of openings at the collar are configured to meter a flow of diluent between the baffle hole and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings disposed at a circumferentially adjustable collar between a baffle plate and at least one fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow hole in the at least one fuel nozzle. | 04-15-2010 |
20100089021 | METHOD AND APPARATUS OF INTRODUCING DILUENT FLOW INTO A COMBUSTOR - Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A plurality of injection holes extend through the at least one fuel nozzle and are configured to meter a flow of diluent into the combustor. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings located at at least one fuel nozzle extending through a through hole in a baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow opening in the at least one fuel nozzle. | 04-15-2010 |
20100089022 | METHOD AND APPARATUS OF FUEL NOZZLE DILUENT INTRODUCTION - Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A shroud is disposed between the baffle plate and the at least one fuel nozzle and is affixed to the baffle plate. A plurality of openings in the shroud are configured to meter a flow of diluent between the baffle hole and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings disposed in a shroud affixed to a baffle plate and disposed between the baffle plate and at least one fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow opening in the at least one fuel nozzle. | 04-15-2010 |
20100101204 | DILUENT SHROUD FOR COMBUSTOR - Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one through baffle hole. At least one diluent shroud is affixed to the at least one baffle plate and is configured to guide a diluent flow toward a mixing chamber of the at least one fuel nozzle. Further disclosed is a method for introducing a diluent flow into a mixing chamber of a fuel nozzle including urging the diluent flow from a plenum through a baffle plate gap between a baffle plate and an outer surface of the fuel nozzle. The diluent flow is directed via at least one diluent shroud extending from the baffle plate toward a plurality of air swirler holes extending through a fuel nozzle tip. The diluent flow is flowed through the plurality of air swirler holes into the mixing chamber. | 04-29-2010 |
20100186366 | System and Method for Water Injection in a Turbine Engine - In one embodiment, a system includes a water injection system configured to supply water from a pressure regulating valve to a water manifold of a turbine engine. The system also includes a drain valve configured to drain at least a portion of the water from the pressure regulating valve during a start-up period of the water injection system at least until a stable water pressure is achieved downstream of the pressure regulating valve. | 07-29-2010 |
20100269482 | GAS TURBINE SYSTEM USING HIGH-HUMIDITY AIR - A gas turbine system using high-humidity air, comprises a compressor for compressing air, a humidifying tower for humidifying the compressed air supplied from the compressor, and a gas turbine driven by a combustion using the compressed air humidified by the humidifying tower, wherein | 10-28-2010 |
20120167545 | PURGE SYSTEM, SYSTEM INCLUDING A PURGE SYSTEM, AND PURGE METHOD - A purge system and liquid fuel atomizing system, a system including a purge system and liquid fuel atomizing system, and a method of purging and atomizing are disclosed. The purging involves a first nozzle, a second nozzle, a third nozzle, and a staged compression system having a first stage and a second stage. The first stage is configured to selectively direct a first pressurized fluid stream to the first nozzle and the second nozzle. The second stage is configured to selectively direct a second pressurized fluid stream to the third nozzle. | 07-05-2012 |
20160010509 | VARIABLE FUEL GAS MOISTURE CONTROL FOR GAS TURBINE COMBUSTOR | 01-14-2016 |
20160084160 | SYSTEM FOR TURBINE COMBUSTOR FUEL MIXING - A system includes a plurality of interconnected mixing assemblies configured to mix a first fuel and water to generate a first mixture, and mix a second fuel and the water to generate a second mixture. The first and second fuel mixtures are configured to combust in a plurality of combustors of a gas turbine. The interconnected mixing assemblies include first and second fuel passages, a water passage, first and second mixers, first and second fuel valves, and first and second water valves disposed in an integrated housing. The first fuel valve has a first fuel flow coefficient between approximately 1.0 to 1.5, the second fuel valve has a second fuel flow coefficient between approximately 3.0 to 5.0, the first water valve has a first water flow coefficient between approximately 0.4 to 0.55, and the second water valve has a second water flow coefficient between approximately 3.5 to 5.0. | 03-24-2016 |
060390540 | Added in prime mover | 2 |
20140069076 | GAS TURBINE INLET FOGGING SYSTEM USING ELECTROHYDRODYNAMIC (EHD) ATOMIZATION - A gas turbine inlet fogging system using electrohydrodynamic (EHD) atomization is disclosed. In one embodiment, the inlet fogging 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, an inlet fogging 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. | 03-13-2014 |
20150377133 | INTAKE-AIR COOLING DEVICE - An object of the present invention is to spray water uniformly to intake air even during partial operation. An intake-air cooling device is disposed on a rear-stage side of a pre-filter disposed on an intake-air inlet side of an intake-air duct for guiding intake air taken in from an intake-air inlet to a compressor, for cooling the intake air by spraying water to the intake air. The intake-air cooling device includes a plurality of nozzles configured to spray the water to the intake air, a plurality of water conduit pipes including the plurality of nozzles arranged in an axial direction of the water conduit pipes, and a plurality of supply pumps configured to supply the water to corresponding one of the plurality of water conduit pipes. Each of the plurality of water conduit pipes is an endless member which has a different perimeter. | 12-31-2015 |
060390550 | Added in combustion products generator | 4 |
20110185699 | GAS TURBINE ENGINE STEAM INJECTION MANIFOLD - A gas turbine engine steam injector includes an annular steam injection manifold aftwardly bounded by an aft manifold wall having steam injection holes disposed therethrough and located axially aft and radially inwardly of a diffuser outlet. An outer baffle wall around manifold has a curved convex surface which may generally conform to a streamline emanating from outlet. Holes may be circumferentially evenly distributed and non-uniformally sized around the aft manifold wall. Hollow struts extend between radially outer and inner bands of a diffuser and a steam supply header in steam supply communication with a fluid passage of at least one of the struts having a passage outlet open to steam cavity within cavity casing located inwardly of inner band. Openings are disposed in an aft cavity wall between cavity and the injector. Passages may be in only a non-uniformally distributed portion of the struts that may be adjacent to each other. | 08-04-2011 |
20120272635 | Gas Turbine Thrust Fuel Efficiency Enhancement System Water (Volatile) Introduction Arrangement Method and Means - Additional thrust fuel efficiency is provided for a gas turbine system that includes a first member(s) (e.g., a support for a rotating main shaft) that is attached to a stationary casing. The rotating main shaft is attached to the first member through a bearing. A second member is associated with a rotating member, such as a motor or other rotating part of the main or other shaft. The first member has a flow path in it for the liquid (e.g. water and/or other volatile liquid) and has an opening (nozzle) for discharging the liquid. The second member has a liquid impinging member for generating a liquid spray, droplet, mist optimally, which vaporizes with hot combustion gases that flow exteriorly along the main shaft. In this form vaporization is quick and is less erosive. The volume of thrust gases is increased advantageously and likewise engine boost increases. | 11-01-2012 |
20130055698 | STEAM INJECTED GAS TURBINE ENGINE - A gas turbine engine has in flow series: a compressor section, a combustion chamber, and a turbine section. The engine further has a steam generator. The combustion chamber has a steam reservoir located at the upstream end thereof. The steam reservoir receives steam from the steam generator, and delivers the received steam into a combustion zone of the combustion chamber. | 03-07-2013 |
20130192192 | OPEN BRAYTON BOTTOMING CYCLE AND METHOD OF USING THE SAME - According to one embodiment, an open brayton bottoming cycle includes a heat exchanger configured between a compressor and an expander. The heat exchanger is configured to receive heat from a heat source and supply at least a portion of the exhaust heat to an expander using a fluid. The compressor configured to supply compressed fluid to the heat exchanger. The expander has a shaft connected to the compressor and configured to supply energy to the compressor. At least one of the compressor or the expander has an efficiency greater than 80 percent. | 08-01-2013 |
060390580 | Added in mixing nozzle or in turbine nozzle | 1 |
20130227928 | FUEL NOZZLE ASSEMBLY FOR USE IN TURBINE ENGINES AND METHOD OF ASSEMBLING SAME - A fuel nozzle for use with a turbine engine is provided. The fuel nozzle includes a housing coupled to a combustor liner defining a combustion chamber. The housing is at least partially positioned within an air plenum and comprises an endwall that at least partially defines the air plenum. The fuel nozzle includes a plurality of mixing tubes extending through the housing for channeling a fuel to the combustion chamber, a cooling fluid plenum at least partially defined within the housing by the housing endwall, and a plurality of apertures defined within the housing endwall for channeling a cooling fluid from the cooling fluid plenum to the air plenum. | 09-05-2013 |
060390590 | Added in separate mixing chamber | 2 |
20130097991 | SYSTEM FOR TURBINE COMBUSTOR FUEL MIXING - A system includes a mixing assembly configured to mix a liquid fuel and a water to generate a fuel mixture. The fuel mixture is configured to combust in a combustor of a gas turbine. The mixing assembly includes a liquid fuel passage disposed in an integrated housing. The liquid fuel passage is configured to flow the liquid fuel and to exclude liquid traps. The mixing assembly also includes a water passage disposed in the integrated housing. The water passage is configured to flow the water and to exclude liquid traps. The mixing assembly also includes a mixer disposed in the integrated housing and coupled to the liquid fuel passage and the water passage. The mixer is configured to mix the liquid fuel and the water to form the fuel mixture. | 04-25-2013 |
20140096502 | BURNER FOR A GAS TURBINE - A burner for a gas turbine is provided. The burner has a pilot combustor, a supply module providing pilot fuel and air into a pilot combustion room enclosed by a pilot burner housing having a tapered exit throat discharging radicals and heat generated in a pilot combustion zone into a main combustion room. An equalizer has holes for main flow air entering a cavity in a radial direction with regard to a burner axis defined by centers of pilot combustion zone and main combustion zone. A fuel injector is downstream the equalizer to supply flow fuel into flow air. A swirler is downstream the injector to give flow distribution to the flow fuel and air entering the main combustion room. A channel leads from the equalizer to the swirler arranged circumferentially around the pilot burner housing to direct the main air flow from the equalizer in axial and circumferential direction. | 04-10-2014 |