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: 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.

Abstract: An improved method of powering an engine using water as a fuel by separating the hydrogen and oxygen atoms and igniting the hydrogen with high voltage high amperage dc electricity in the compression/combustion chamber of the engine and recycling the exhaust water for reuse.

Abstract: A chemical-looping combustion system is provided in which an oxygen carrier, for example a metallic oxide or peroxide, is used for fuel combustion and produces carbon dioxide and water as by-products. The system delivers steam and CO2 at for direct utilization by steam cycle power generation equipment and heat exchangers. After fuel combustion, the oxygen-poor carrier is regenerated by exposure to air in a second, sequestered reactor. Choice of oxygen-carrier material and conditions allows for the fuel oxidizer reactor to run at temperatures greater than the running temperature of the regenerator reactor.

Abstract: The present invention is a method and system for vertically producing a steam and combustion gas mixture, typically used in enhanced oil recovery processes. The system is a fluid bed up-flow combustor system, including a vertical vessel with fours sections. In a first section, fuel, oxidizer, and possibly water are supplied to the high pressure combustor at a combustion section of a vertical vessel. The combustion gas from the first section flows to a second section for steam generation, where low quality water is injected and turned into steam. Next, the third section is a homogenizer vessel, where any remaining water drops are converted to steam and solid particles and discharged from the vessel. The fourth section located at the bottom of the vessel is a fluid bed, receiving and processing the falling solids from the combustion and the steam generation sections.

Abstract: A power generation system (11) and method of operating such a system (11) including a steam turbine (14). In one embodiment a HRSG (20) includes an evaporator (127) coupled to receive condensate from the steam turbine (14), and a superheater (132) coupled to receive output from the evaporator (127). The HRSG (20) generates steam with thermal energy received from a combustion turbine (28). A flash tank (9) receives water heated in the HRSG (20), outputs a first portion of the water as steam, and outputs a second portion of the water as liquid. A flow line (134) passes steam (51) from the flash tank (9) to a combustion chamber (26) in the combustion turbine (28) to provide power augmentation.

Abstract: A method is disclosed for removing deposits from rotating parts of a gas turbine engine while under full fire or idle speed utilizing a particulate coke composition. The coke composition may be introduced directly into the combustion chamber (combustor) of the gas turbine or, alternatively, anywhere in the fuel stream, water washing system, or the combustion air system. By kinetic impact with the deposits on blades and vanes, the deposits will be dislodged and will thereby restore the gas turbine to rated power output. If introduced into the compressor section, the coke particles impinge on those metal surfaces, cleaning them prior to entering the hot gas section where the process is repeated.

Abstract: A method of operating a combustor having a central nozzle and a plurality of outer nozzles surrounding the central nozzle is provided. The method includes providing a liquid fuel to only the plurality of outer nozzles at a specified total energy input. The method includes decreasing the liquid fuel to the plurality of outer nozzles while simultaneously increasing a gas fuel to the central nozzle and the plurality of outer nozzles to substantially maintain the specified total energy input. The method includes supplying a fuel-air ratio of the gas fuel to the central nozzle that exceeds a threshold value such that a central nozzle flame is anchored. An air-fuel ratio of the gas fuel to the plurality of outer nozzles is less than the threshold value such that a plurality of outer nozzle flames are lifted until a purge flow is supplied to the outer nozzles.

Abstract: A system for reducing combustion dynamics in a combustor includes an end cap having an upstream surface axially separated from a downstream surface, and tube bundles extend through the end cap. A diluent supply in fluid communication with the end cap provides diluent flow to the end cap. Diluent distributors circumferentially arranged inside at least one tube bundle extend downstream from the downstream surface and provide fluid communication for the diluent flow through the end cap. A method for reducing combustion dynamics in a combustor includes flowing fuel through tube bundles that extend axially through an end cap, flowing a diluent through diluent distributors into a combustion chamber, wherein the diluent distributors are circumferentially arranged inside at least one tube bundle and each diluent distributor extends downstream from the end cap, and forming a diluent barrier in the combustion chamber between at least one pair of adjacent tube bundles.

Abstract: The invention relates to a method for operating a combined-cycle power plant with cogeneration, in which method combustion air is inducted in at least one gas turbine, is compressed and is fed to at least one combustion chamber for combustion of a fuel, and the resultant exhaust gas is expanded in at least one turbine producing work, and in which method the exhaust gas which emerges from the at least one turbine is fed through a heat recovery steam generator in order to generate steam, which heat recovery steam generator is part of a water-steam circuit with at least one steam turbine, a condenser, a feedwater tank and a feedwater pump, wherein heat is produced by extraction of steam from the at least one steam turbine.

Abstract: The invention relates to a method for operation of a combined-cycle power plant with cogeneration, in which method combustion air is inducted in at least one gas turbine, is compressed and is supplied to at least one combustion chamber for combustion of a fuel, and the resultant exhaust gas is expanded in at least one turbine, producing work, and in which method the exhaust gas emerging from the at least one turbine is passed through a heat recovery steam generator in order to generate steam, which generator is part of a water-steam circuit with at least one steam turbine, a condenser, a feedwater tank and a feedwater pump, wherein heat is provided by extracting steam from the at least one steam turbine.

Abstract: A fuel purging system for a turbine assembly includes a fuel delivery system. The fuel delivery system includes a fuel source for providing a fuel to the turbine assembly, a control valve for regulating a fuel flow of the fuel, a flow divider for selectively distributing the fuel to at least one combustor, and a combustor valve located upstream of the at least one combustor. The fuel purging system also includes a steam source for distributing a steam to the fuel delivery system at a location upstream of the combustor valve.

Abstract: A combustor includes an end cap having upstream and downstream surfaces and a cap shield surrounding the upstream and downstream surfaces. First and second sets of premixer tubes extend from the upstream surface through the downstream surface. A first fuel conduit supplies fuel to the first set of premixer tubes. A casing circumferentially surrounds the cap shield to define an annular passage, and a second fuel conduit supplies fuel through the annular passage to the second set of premixer tubes. A method for supplying fuel to a combustor includes flowing a working fluid through first and second sets of premixer tubes, flowing a first fuel into the first set of premixer tubes, and flowing a second fuel through an annular passage surrounding the end cap and into the second set of premixer tubes.

Abstract: Systems and methods for improving the efficiency of a power generation facility utilize heat energy to preheat inlet-air that is supplied to the compressor of a turbine or to preheat fuel that is burned in the turbine. The heat energy used to preheat the inlet-air can be drawn from a heat recovery steam generator (HRSG) that produces steam using at least part of the exhaust gas of the turbine. The heat energy can be obtained from one or more predetermined points within the HRSG, such as a feed water line exiting a drum of the HRSG or a feed line connecting an economizer of the HRSG to a drum of the HRSG. The fluid drawn from the predetermined point passes through a heat exchanger or a preheater to remove the heat energy used for preheating. The fluid is then returned to the HRSG immediately downstream from the point from which it was drawn.

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 heating and cooling system for inlet air of a turbine compressor. The heating and cooling system may include a fluid coil positioned about the turbine compressor and a thermal energy storage tank. The fluid coil and the thermal energy storage tank are in fluid communication such that fluid is both provided to the fluid coil from the thermal energy storage tank for exchanging heat with the inlet air and returned to the thermal energy storage tank without further heat exchange.

Abstract: Disclosed is a method for operating a burner for fluid fuels. According to said method, the fluid fuel is mixed with an oxidizer before the fluid fuel is burned. The inventive method is characterized in that a liquid fuel that is used as a fluid fuel is mixed with a gaseous or vaporous carrier flow before being mixed with the oxidizer while the carrier flow containing the liquid fuel is mixed with the oxidizer in order to mix the liquid fuel with the oxidizer.

Abstract: A method is provided for operating a combined cycle power plant. Flue gas of a gas turbine is used for producing steam for a steam turbine. A reliable and flexible black start network restoration is achieved by: a) in island mode, supplying internal consumers by the gas turbine, the operating point of which is selected so that a minimum steam temperature is achieved; b) in island mode, the steam turbine is synchronized and ramped up to an operating point where a maximum power increase is achieved, the resulting steam turbine load change is compensated by the gas turbine; c) consumer loads are connected blockwise; d) the increase in the demanded load being provided by the steam turbine; e) the load of the steam turbine is gradually reduced increasing its load-increasing capacity; and steps c)-e) are repeated until the power plant's base load is achieved.

Abstract: A method is provided for supplying a liquid fuel to a gas-turbine engine, e.g. aviation engine. It includes selective fuel delivery through several fuel delivery lines for different engine operating modes based on a required engine power, providing, e.g. feeding the engine operating at minimal power with base or traditional for this type of engine fuel through a base fuel delivery line; in other operating modes the fuel is fed to the engine either through conditioned fuel delivery line with preliminary conditioning of base fuel or through both said fuel delivery lines simultaneously with mixing both fuel flows directly before entering an engine combustion chamber, e.g., in a line connecting intake manifold for the base fuel and each individual fuel injector.

Abstract: A gas turbine engine, especially a turbojet or turbofan for an aircraft, includes a combustion section and an exhaust section produces an exhaust gas. The emission products can be reduced by using a gas treatment device with a reactor and an injection device. The reactor produces a nitrogeneous substance such as ammonia. This reducing agent is injected in the gas phase in the exhaust section of the gas turbine engine. By selective non catalytic reaction the Nitrogen oxides of the exhaust gas can be reduced. Furthermore the injection device is arranged such that the temperature window of this reduction process is ranging from 850° C. to 1100° C. The reactor for producing gaseous ammonia can either be a thermal reactor or a high pressure plasma device.

Abstract: A system includes a turbine fuel supply system. The turbine fuel supply system includes a first turbine fuel mixer configured to mix a first liquid fuel and a first deaerated water to generate a first fuel mixture. The first fuel mixture is configured to combust in a combustor of a gas turbine engine. The turbine fuel supply system also includes a deaerated water flow path configured to route the first deaerated water to the first turbine fuel mixer and a liquid fuel flow path configured to route the first liquid fuel to the first turbine fuel mixer.

Abstract: This invention discloses systems and methods for conversion of high moisture waste materials to dry or low moisture products for recycle or reuse. The equipment systems comprise a gas turbine generator unit (preferred heat source), a dryer vessel and a processing unit, wherein the connection between the gas turbine and the dryer vessel directs substantially all the gas turbine exhaust into the dryer vessel and substantially precludes the introduction of air into the dryer vessel and wherein the processing unit forms the dried material from the dryer vessel into granules, pellets or other desired form for the final product. Optionally, the systems and methods further provide for processing ventilation air from manufacturing facilities to reduce emissions therefrom.

Abstract: A method for extracting energy from hydrocarbons located in a geologic reservoir is presented, including the steps of: oxidizing the hydrocarbons; extracting heat generated from oxidizing the hydrocarbons, relocating oxidized gases away from the oxidizing hydrocarbons; and replenishing oxygen towards the oxidizing hydrocarbons. The extraction of heat further includes: evaporating a liquid; transferring the evaporated liquid to the surface; and recovering low-NaCl, low-precipitate water from the evaporated liquid. The replenishing of oxygen towards the oxidizing hydrocarbons further includes: generating oxygen from water; and transferring the generated oxygen toward the oxidizing hydrocarbons; and combining hydrogen derived from the generating step with surface oxygen, whereby heat and low-precipitate, pure water is produced.

Abstract: The present application provides an inlet air fogging system for a gas turbine engine. The inlet air fogging system may include a fogging nozzle array and a fogging control system in communication with the fogging nozzle array. The fogging control system may include a droplet size measurement system and a humidity level measurement system.

Abstract: A method of operating a multi-fuel combustion system is provided. The method includes a first phase and a second phase, wherein the first phase includes providing ignition to a combustor basket to ignite a first type of fuel, where the first type of fuel is supplied to the combustor basket through a first conduit. Also in first phase steam is also supplied to the first conduit in addition to the first type of fuel and steam is supplied to the second conduit after the ignition. In the second phase a second type of fuel is supplied to the combustor basket through the second conduit after ignition of the first fuel through the first conduit, while stopping the supply of the first fuel, and continuing to supply steam through both the first and second conduits.

Abstract: A system for conditioning an airstream entering an air-breathing machine includes an air conditioning system (ACS) configured for adjusting a physical property of the airstream, wherein the ACS comprises a module. The module includes a non-media conditioning system configured for adjusting a physical property of the airstream if an ambient condition is within a range, wherein the non-media conditioning system comprises nozzles adapted for spraying a fluid onto the airstream. The module also includes a media conditioning system configured for adjusting a physical property of the airstream to provide additional output of the air-breathing machine, wherein the media conditioning system comprises a direct exchange medium and a fluid distribution manifold. The ACS operates in a direct evaporative mode if the fluid is approximately greater than a dew point temperature and operates in a direct chilling mode if the fluid is approximately less than a dew point temperature.

Abstract: A flame-holding control method in a gas turbine having a combustor can and a fuel nozzle disposed in the combustor can. The method can include performing a first scheduled injection of a diluent stream into the nozzle, checking to see if a time period has exceeded a time threshold and in response to the time period being greater than that the time threshold, performing a second scheduled injection of the diluent stream into the nozzle.

Abstract: A heating and cooling system for inlet air of a gas turbine engine in a combined cycle power plant having a steam turbine. The heating and cooling system may include a fluid coil positioned about the gas turbine engine, a heat exchanger in communication with the fluid coil, and a condenser in communication with the steam turbine and the heat exchanger such that waste heat from the steam turbine is forwarded to the fluid coil.

Abstract: 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 can be actuated to inject liquid to various radial regions of an air intake case of the turbine power plant. During a stage one actuation, liquid is directed to a first radial region of the air intake case. During a stage two actuation, liquid is directed to the first radial region and also to a second radial region of the air intake case.

Abstract: A gas turbine engine including a compressor, a combustion chamber and a turbine arranged in flow series, wherein the gas turbine engine further includes: one or more combustion zones; a source of steam configured to deliver steam to the combustion chamber; and a liquid water delivery system configured to selectively provide liquid water to one or more of the combustion zones after a start up period of the gas turbine engine. A method of generating power with a gas turbine engine, the gas turbine engine including a compressor, a combustion chamber and a turbine arranged in flow series, wherein the method includes: selectively delivering steam from a source of steam to the combustion chamber; and providing liquid water to one or more combustion zones after a start up period of the gas turbine engine.

Abstract: Hydrogen-containing fuel/oxidizer combinations, such as aqueous ammonia and aqueous hydrogen peroxide, are disclosed. Systems and methods using such fuel for generation of energy are also disclosed. The reaction products of the fuels are environmentally benign chemicals such as nitrogen gas and water.

Abstract: 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.

Abstract: A steam generation system comprises: an oxygenated water treatment (OWT) sub-system configured to generate water having oxidizing chemistry; a steam generation sub-system configured to convert the water having oxidizing chemistry into steam having oxidizing chemistry; an attemperator or other injection device or devices configured to add an oxygen scavenger to the steam having oxidizing chemistry to generate steam having less oxidizing or reducing chemistry; and a condenser configured to condense the steam having less oxidizing or reducing chemistry into condensed water.

Abstract: A method of operating a multi-fuel combustion system is provided. The method includes a first phase and a second phase, wherein the first phase includes providing ignition to a combustor basket to ignite a first type of fuel, where the first type of fuel is supplied to the combustor basket through a first conduit. Also in first phase steam is also supplied to the first conduit in addition to the first type of fuel and steam is supplied to the second conduit after the ignition. In the second phase a second type of fuel is supplied to the combustor basket after ignition of the first fuel through the second conduit, while stopping the supply of the first fuel.

Abstract: A method and apparatus are disclosed for mixing H2-rich fuels with air in a gas turbine combustion system, wherein a first stream of burner air and a second stream of a H2-rich fuel are provided. All of the fuel is premixed with a portion of the burner air to produce a pre-premixed fuel/air mixture. This pre-premixed fuel/air mixture is injected into the main burner air stream.

Abstract: A device capable of collecting a condensate from a working fluid is disclosed. The condensate can take the form of a liquid and can be injected into a flow path of an engine. In one form the engine is a gas turbine engine and the liquid is injected upstream of a combustor. The liquid can be produced using a component that cools the working fluid to condense a vapor within it. In one non-limiting form the component is part of a refrigeration system. In addition to producing condensate, the refrigeration system can cool the working fluid to be used as cooled cooling air to a turbine of a gas turbine engine. In another non-limiting embodiment a liquid derived from a blackwater containing waste from an organism can be delivered in whole or in part to a flow path of the engine.

Abstract: A gas turbine engine has in flow series: a compressor section, a combustor, and a turbine section. The engine further has a steam generator, and a water and steam delivery system. During an engine start-up period, the delivery system delivers liquid water to the combustor and mixes the delivered water in its liquid state with working gas in the combustor. After the start-up period, the delivery system accepts steam from the steam generator, delivers the steam to the combustor and mixes the delivered steam in its gaseous state with the working gas in the combustor.

Abstract: Contemplated plants integrate regeneration of a freeze point depressant with LNG regasification and a power cycle. Most preferably, the plant is a combined cycle plant in which heat for reboiling the regenerator is provided by the steam cycle, and in which LNG refrigeration content is used to condense steam from the regenerator and to further subcool intake air for a combustion turbine.

Abstract: This invention presents improved combustion methods, systems, engines and apparatus utilizing H2, O2 and H2O as fuel, thereby providing environmentally friendly combustion products, as well as improved fuel and energy management methods, systems, engines and apparatus. The Water Combustion Technology; WCT, is based upon water (H2O) chemistry, more specifically H2O combustion chemistry and thermodynamics. WCT does not use any hydrocarbon fuel source, rather the WCT uses H2 preferably with O2 and secondarily with air. The WCT significantly improves the thermodynamics of combustion, thereby significantly improving the efficacy of combustion, utilizing the first and second laws of thermodynamics. The WCT preferably controls combustion temperature with H2O and secondarily with air in the combustion chamber. The WCT preferably recycles exhaust gases as fuel converted from water.

Abstract: The invention relates to a method of regulation of the temperature of a hot gas of a gas turbine, particularly of a stationary gas turbine used for generating electricity, which comprises injecting a liquid into an airflow, which can be drawn into a compressor and with the aid of which a fuel inside a combustion chamber, which is situated downstream, combusts while producing the hot gas that is subsequently expanded when flowing through the turbine part located downstream. A temperature measuring device is provided that measures the temperature of the airflow before the compressor, whereby the temperature of the hot gas is regulated by the quantity of fuel. The aim of the invention is to provide a regulation with which, during wet compression operation, the serviceable life of the components subjected to the action of hot gas is lengthened.

Abstract: An intake air temperature control device including a heat exchanger is provided. The heat exchanger is connected at one side into an intake air line and is connected at the other side into a circuit of an intake air preheating system, wherein a store for a fluid for heat transfer may be thermally connected to the circuit. A method for operating an intake air temperature control device is also provided.

Abstract: An integrated system for blast furnace iron making and power production based upon higher levels of oxygen enrichment in the blast gas is disclosed. The integrated system leads to; 1) enhanced productivity in the blast furnace, 2) more efficient power production, and 3) the potential to more economically capture and sequester carbon dioxide. Oxygen enhances the ability of coal to function as a source of carbon and to be gasified within the blast furnace thereby generating an improved fuel-containing top gas.

Abstract: A combustion chamber and method for operating a combustion chamber are disclosed. The combustion chamber having at least a mixing device connected to a combustion device. The mixing device has a first fuel feeding stage, to inject fuel into the mixing device and mix the fuel with an oxidizer to then burn the fuel in the combustion device. The combustion device has a second fuel feeding stage to inject fuel into the combustion device. The fuel of the second stage is mixed with only an inert fluid to form a mixture that is then injected into the combustion chamber.

Abstract: A method for assembling an additive injection system for use with a turbine engine includes coupling a liquid fuel connection in flow communication with a water supply manifold and coupling an additive source in flow communication with the water supply manifold.

Abstract: A method for assembling an additive injection system for use with a turbine engine includes coupling an atomizing air connection to a fuel nozzle assembly and coupling an additive source to the atomizing air connection.

Abstract: A gas turbine case is provided including an outer case surface, and a channel portion formed as a recessed area extending radially inwardly into the outer case surface. The channel portion extends about a circumference of the case. An outer flow jacket is attached to the outer case surface and extends over the channel portion to define an enclosed cooling passage along the outer case surface. At least one inlet passage and at least one outlet passage are provided in fluid communication with the enclosed cooling passage to convey air to and from the cooling passage.

Abstract: A method and system for gas turbine emissions management through delivery of a diluent fluid stream (steam, CO2, N2 etc) into a gas turbine combustion system while the gas turbine is operating on a conventional fuel such as light distillate oil or natural gas. The diluent injection system delivers required diluent-to-fuel ratios over the emissions compliance operating range of the gas turbine. The method for diluent injection is coupling the injection system to a gas turbine compressor discharge purge system, such that the diluent fluid is mixed with compressor discharge air. The mixed compressor discharge purge air and diluent stream are injected into the gas turbine combustor through a non-fueled combustion fuel nozzle passage to achieve emissions guarantee compliance.

Abstract: A water injection system positioned about a combustor of a gas turbine engine. The water injection system may include a water manifold and a pressure relief system in communication with the water manifold. The pressure relief system may include a relief vent positioned on a pressure relief line.

Abstract: A method and system for modulating the Modified Wobbe Index (MWI) of a fuel is provided. A variety of industrial components, which may require a gas fuel, such as but not limiting of, a heavy-duty gas turbine; an aero-derivative gas turbine; or a boiler may utilize the method and system. The method and system may provide an industrial component comprising at least one steam injection system, wherein the at least one steam injection system injects steam into at least one fuel supply line upstream of a combustion system to modulate the MWI of at least one fuel. The method and system may also determine whether the MWI of the at least one fuel is outside of a predetermined range; and utilize the at least one steam injection system to automatically inject the steam at a flowrate for adjusting the MWI of the at least one fuel.

Abstract: A power generating system is described which operates at high pressure and utilizes a working fluid consisting of a mixture of compressed non-flammable air components, fuel combustion products and steam. The working fluid exiting the power generating system is substantially free of NOx and CO. Working fluid is provided at constant pressure and temperature. Combustion air is supplied by one or more stages of compression. Fuel is injected at pressure as needed. At least about 40% of the oxygen in the compressed air is consumed when the fuel is burned. Inert liquid is injected at high pressure to produce working an inert mass of high specific heat diluent vapor for use for internal cooling of the combustion chamber. The use of non-flammable liquid injection inhibits the formation of pollutants, increases the efficiency and available horsepower from the system, and reduces specific fuel consumption.