Class / Patent application number | Description | Number of patent applications / Date published |
060390461 | Using special fuel or oxidizer | 72 |
20090013663 | METHANE ENGINE FOR ROCKET PROPULSION - Disclosed is a methane engine for rocket propulsion. A methane supply pump ( | 01-15-2009 |
20100122519 | ULTRA-LOW SULFUR FUEL AND METHOD FOR REDUCED CONTRAIL FORMATION - A method of managing contrail formation of a gas turbine engine includes delivering an ultra-low sulfur fuel to a combustor of a gas turbine engine to limit an amount of sulfur byproduct produced in an exhaust of the gas turbine engine. | 05-20-2010 |
20100126137 | Combustion Installation - A combustion installation including a combustion device with a combustion space for combustion of a fuel and an oxygen-containing gas to a combustion gas in the combustion space and a membrane device is described. The membrane device is arranged for the flow of air, past a membrane in a second compartment of the membrane device, to be in the same direction as the flow of combustion gases, past the membrane in a first compartment of the membrane device. | 05-27-2010 |
20100281845 | Jet fuel compositions and methods of making and using same - Provided herein are, among other things, jet fuel compositions and methods of making and using the same. In some embodiments, the fuel compositions comprise at least a fuel component readily and efficiently produced, at least in part, from a microorganism. In certain embodiments, the fuel compositions provided herein comprise a high concentration of at least a bioengineered fuel component. In further embodiments, the fuel compositions provided herein comprise a C | 11-11-2010 |
20100281846 | Jet fuel compositions and methods of making and using same - Provided herein are, among other things, jet fuel compositions and methods of making and using the same. In some embodiments, the fuel compositions comprise at least a fuel component readily and efficiently produced, at least in part, from a microorganism. In certain embodiments, the fuel compositions provided herein comprise a high concentration of at least a bioengineered fuel component. In further embodiments, the fuel compositions provided herein comprise limonane. | 11-11-2010 |
20100281847 | Mixed fuel coal burner for gas turbines - As shown schematically in FIG. | 11-11-2010 |
20100300063 | Apparatus and Method for Combusting a Fuel at High Pressure and High Temperature, and Associated System and Device - A combustor apparatus is provided, comprising a mixing arrangement for mixing a carbonaceous fuel with enriched oxygen and a working fluid to form a fuel mixture. A combustion chamber is at least partially defined by a transpiration member. The transpiration member is at least partially surrounded by a pressure containment member. The combustion chamber has opposed inlet and outlet portions. The inlet portion of the combustion chamber is configured to receive the fuel mixture for the fuel mixture to be combusted at a combustion temperature. The combustion chamber is further configured to direct the resulting combustion product toward the outlet portion. The transpiration member directs a transpiration substance therethrough toward the combustion chamber for buffering interaction between the combustion product and the transpiration member. Associated systems, apparatuses, and methods are also provided. | 12-02-2010 |
20110005190 | KEROSENE BASE FUEL - The subject invention relates to a kerosene base fuel having an initial boiling point in the range 130 to 160° C. and a final boiling point in the range 250 to 300° C. as determined according to ASTM method D86, and comprising less than 15% by weight of aromatic compounds, and at least of 80% by weight of aliphatic hydrocarbons, of which at least 20% by volume are n-paraffins and at least 25% by volume are cycloparaffins, as determined by according to ASTM method D2425. It further relates to the use of this base fuel in fuel compositions, as well for he use of the kerosene base fuel in a fuel composition comprising a petroleum based kerosene base fuel having a higher density and a lower energy content than that of the kerosene base fuel, to increase the energy density above that of the petroleum derived kerosene fuel. | 01-13-2011 |
20110107737 | Gasification Power Generation System Provided with Carbon Dioxide Separation and Recovery Device - A gasification power generation system provided with a carbon dioxide separation and recovery device is disclosed. The system includes a carbon dioxide separation and recovery device having a shift reactor to convert carbon monoxide contained in fuel gas into carbon dioxide by mixing steam into the fuel gas containing carbon monoxide and hydrogen to cause a shift reaction; a carbon dioxide absorption tower to produce fuel gas from which carbon dioxide has been removed by allowing an absorption liquid to absorb carbon dioxide from the fuel gas containing carbon dioxide flowing down the shift reactor; an absorption liquid recycling device to recycle an absorption liquid by separating carbon dioxide absorbed by the absorption liquid in the carbon dioxide absorption tower; and a gasification power generation system. | 05-12-2011 |
20110167783 | GAS TURBINE DEVICE - An object of the present invention is to provide a gas turbine device capable of producing a mixed gas in which three or more types of gases are evenly mixed, and of doing the like. To achieve this, in a gas turbine device configured to burn in a combustor ( | 07-14-2011 |
20110185703 | Gas Turbine Combustor - A gas turbine combustor includes plural multi-coaxial-injection-hole burners in which plural fuel nozzles and plural air holes provided in an air plate to correspond to the respective fuel nozzles are coaxially arranged. Each of the multi-coaxial-injection-hole burners includes a first coaxial injection burner disposed on an inner circumferential side, and a second coaxial injection burner disposed on an outer circumferential side, and a diameter of the air holes of the first coaxial injection burner is smaller than a diameter of the air holes of the second coaxial injection burner. Combustion for carrying out flame holding of a gas turbine combustor is performed by the first coaxial injection burner, and low NOx combustion of the gas turbine combustor is performed by the second coaxial injection burner. | 08-04-2011 |
20120073261 | APPARATUS FOR COMBUSTING A FUEL AT HIGH PRESSURE AND HIGH TEMPERATURE, AND ASSOCIATED SYSTEM - A combustor apparatus is provided, comprising a mixing arrangement for mixing a carbonaceous fuel with enriched oxygen and a working fluid to form a fuel mixture. A combustion chamber is at least partially defined by a porous perimetric transpiration member, at least partially surrounded by a pressure containment member. The combustion chamber has longitudinally spaced apart inlet and outlet portions. The fuel mixture is received by the inlet portion for combustion within the combustion chamber at a combustion temperature to form a combustion product. The combustion chamber directs the combustion product longitudinally toward the outlet portion. The transpiration member is configured to substantially uniformly direct a transpiration substance therethrough toward the combustion chamber, such that the transpiration substance is directed to flow helically about the perimeter and longitudinally between the inlet and outlet portions, for buffering interaction between the combustion product and the transpiration member. Associated systems are also provided. | 03-29-2012 |
20130036723 | OXY-COMBUSTION GAS TURBINE HYBRID - An integrated oxy-combustion power generation process is provided. This process includes providing an air separation unit for producing at least an oxygen-enriched stream, providing a carbon dioxide recycle stream, which is combined with the oxygen-enriched stream thereby producing a synthetic air stream, providing a gas turbine comprising a gas inlet , a combustor, and a gas outlet, wherein the synthetic air stream is introduced into the gas inlet, providing a fuel stream to the combustor, thereby producing a power output, and a hot exhaust gas stream, which exits the gas outlet, introducing the exhaust gas stream, along with a boiler feed water stream, into a heat recovery steam generator, thereby producing a steam stream and a cooled exhaust gas stream, and separating the cooled exhaust gas stream into an enriched carbon dioxide product stream and the carbon dioxide recycle stream. | 02-14-2013 |
20130232942 | GRADUAL OXIDATION WITH GRADUAL OXIDIZER WARMER - Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber. | 09-12-2013 |
20140000236 | COMBUSTOR | 01-02-2014 |
20150128559 | Advanced Humid Air Gas Turbine System - One of the objects of the invention is to provide a water-saving type advanced humid air gas turbine system (AHAT) that can decrease the amount of makeup water to be supplied from the outside, by reducing the amount of water consumed when the gas turbine system is starting up, shut down, or subjected to load rejection. | 05-14-2015 |
20150315971 | HIGH-SPEED VEHICLE POWER AND THERMAL MANAGEMENT SYSTEM AND METHODS OF USE THEREFOR - A thermal management and power generation system for a hypersonic vehicle. The thermal management and power generation system comprising a fluid supply having a volatile fluid and a fuel supply having an endothermic fuel. A first heat exchanger, fluidically coupled to the fluid supply, absorbs heat from a first portion of the hypersonic vehicle, which vaporizes the volatile fluid. A mixing apparatus, fluidically coupled to the first heat exchanger and the fuel supply combines the vaporized volatile fuel and endothermic fuel. A second heat exchanger, fluidically coupled to the mixing apparatus, absorbs heat from a second portion of the hypersonic vehicle and decomposes the endothermic fuel by endothermic pyrolysis. A heat engine, fluidically coupled to the first heat exchanger and the mixing apparatus, is configured to generate an electrical power for use by the hypersonic vehicle. The vaporized volatile fluid mixed with the endothermic fuel within the second heat exchanger reduces coking caused by the endothermic pyrolytic decomposition of the endothermic fuel as compared to an endothermic pyrolytic decomposition of an endothermic fuel not having a vaporized volatile fluid mixed therewith. | 11-05-2015 |
20160090911 | GAS TURBINE FACILITY - A gas turbine facility | 03-31-2016 |
20160194573 | PROCESS FOR PRODUCING A SUBSTITUTE NATURAL GAS | 07-07-2016 |
060390463 | Plural distinct fuels | 32 |
20080196385 | GAS TURBINE SYSTEM - A gas turbine uses a first fuel at full load and an improved emission behavior is achieved by operating the gas turbine ( | 08-21-2008 |
20090107105 | METHOD AND APPARATUS FOR COMBUSTING SYNGAS WITHIN A COMBUSTOR - A method for operating a combustor is provided. The method includes supplying a predetermined amount of a first gaseous fuel to the combustor, wherein the first gaseous fuel has a first Modified Wobbe Index (MWI) and a first fuel reactivity, and supplying a predetermined amount of a second gaseous fuel to the combustor, wherein the second gaseous fuel has a second MWI that is lower than the first MWI and a second fuel reactivity that is higher than the first fuel reactivity. The method also includes mixing the first and second gaseous fuels together to form a blended gaseous fuel, and injecting the blended gaseous fuel into the combustor. | 04-30-2009 |
20090165435 | Dual fuel can combustor with automatic liquid fuel purge - A lean, low NOx gas-fired can combustor having liquid fuel operation capability includes a housing, a combustor liner disposed within the housing and defining a combustion zone for combusting fuel with air, and a head assembly for joining the longitudinal housing and liner ends and for supporting swirler vanes that admit about 45-55% of a total combustor air flow to the combustion zone. The head assembly includes multiple gaseous fuel injection ports upstream of the swirler vanes, and a single liquid fuel injector positioned along the liner axis for directing atomized liquid fuel into the combustion zone. The head assembly further includes a heat shield disposed between the injector and the combustion zone, and the head assembly is configured to provide a flow of air for cooling the heat shield during all operations of the can combustor. The can combustor may also include apparatus for automatically purging the liquid fuel injector with compressed air, such as cooled compressed air from a gas turbine engine compressor stage. The apparatus includes a shuttle valve controller including a shuttle member biased by a first pressure towards a first position interconnecting the liquid fuel input to the liquid fuel injector inlet, while blocking compressed purging air flow, and biased by a second pressure towards a second position interconnecting the compressed purging air input to the liquid fuel injector inlet, while blocking liquid fuel flow. | 07-02-2009 |
20090272096 | Single Manifold Dual Gas Turbine Fuel System - The present application provides a dual gas fuel delivery system and a method of delivering two gas fuels to a turbine. The dual gas fuel delivery system may include (a) a low energy gas delivery system comprising a low energy gas inlet and a low energy gas primary manifold outlet; (b) a high energy gas delivery system comprising a high energy gas inlet and a high energy gas primary manifold outlet; and (c) a primary manifold, wherein the low energy gas primary manifold outlet and the high energy gas primary manifold outlet are coupled to the primary manifold. | 11-05-2009 |
20090272097 | Independent Manifold Dual Gas Turbine Fuel System - The present application provides a dual gas fuel delivery system and a method of delivering two gas fuels. The system may include (a) a low energy gas delivery system comprising a low energy gas inlet, a gas split, a low energy gas primary manifold outlet, and a low energy gas secondary manifold outlet; (b) a high energy gas delivery system comprising a high energy gas inlet and a high energy gas primary manifold outlet; (c) a primary manifold; and (d) a secondary manifold, wherein the low energy gas primary manifold outlet and the high energy gas primary manifold outlet are coupled to the primary manifold, wherein the low energy gas secondary manifold outlet is coupled to the secondary manifold, and wherein the low energy gas delivery system further comprises a primary low energy gas stop and pressure control valve between the gas split and the low energy gas primary manifold outlet. | 11-05-2009 |
20090272098 | Primary Manifold Dual Gas Turbine Fuel System - The present application provides a dual gas fuel delivery system and a method of delivering two gas fuels. The dual gas fuel delivery system may include (a) a low energy gas delivery system comprising a low energy gas inlet, a gas split, a low energy gas primary manifold outlet, and a low energy gas secondary manifold outlet; (b) a high energy gas delivery system comprising a high energy gas inlet and a high energy gas primary manifold outlet; (c) a primary manifold; and (d) a secondary manifold, wherein the low energy gas primary manifold outlet and the high energy gas primary manifold outlet are coupled to the primary manifold, and wherein the low energy gas secondary manifold outlet is coupled to the secondary manifold. | 11-05-2009 |
20100083633 | METHOD AND SYSTEM FOR OPERATING A TURBOMACHINE HAVING AN UNCHOKED VALVE - An embodiment of the present invention provides a method of controlling a turbomachine having at least one fuel supply system that uses an unchoked valve. Here, the method may determine the flow characteristics of a fuel in a fuel supply system without using a flow meter. | 04-08-2010 |
20100095649 | STAGED COMBUSTION SYSTEMS AND METHODS - Systems and methods for staged combustion are provided. One staged combustion system includes a first fuel source for supplying a first fuel having a first chemical composition, a first injector for injecting the first fuel, a second fuel source for supplying a second fuel having a second chemical composition such that a relative reactive concentration of one or more of hydrogen, carbon monoxide, a hydrocarbon, or a combination of two or more hydrocarbons, in the first chemical composition is different from that of the second chemical composition, and a second injector situated for injecting the second fuel downstream of the first injector. | 04-22-2010 |
20100139238 | Combustor Housing for Combustion of Low-BTU Fuel Gases and Methods of Making and Using the Same - A combustor housing includes an inlet cover plate having a central inlet configured to receive a supply of one of a high BTU content fuel or air and at least one radially-spaced, peripheral fuel inlet configured to receive a supply of a low BTU content fuel. It also includes an outlet cover plate having at least one radially-spaced, peripheral fuel outlet. The combustor housing also includes a peripheral sidewall joining the inlet cover and the outlet cover and enclosing a plenum, the at least one peripheral fuel inlet opening through the inlet cover plate into the plenum and the at least one fuel outlet opening from the plenum through the outlet cover plate. The central inlet opens into at least one conduit which extends away from the central inlet and opens into at least one high BTU content fuel conduit or air supply conduit that is axially aligned with the at least one fuel outlet. | 06-10-2010 |
20100229524 | LOW HEATING VALUE FUEL GAS BLENDING CONTROL - A method includes blending a first fuel with a second fuel in a ratio to produce a third mixed fuel. The first fuel has a first heating value, the second fuel has a second heating value, and the third mixed fuel has a third heating value. In addition, the first heating value is different than the second heating value. The method also includes feedforward controlling the third heating value of the third mixed fuel via prediction and correction of a fuel flow rate of the first and/or second fuels to adjust the ratio of the first and second fuels based at least in part on a comparison between a measurement and a target for the third heating value. | 09-16-2010 |
20100263348 | Additive injection system for improving thermal stability of jet fuel - A gas turbine engine fuel system includes a fuel tank for storing fuel, a heat exchanger through which the fuel from the fuel tank can pass, a fuel pump located downstream from the heat exchanger for pumping the fuel, a fuel metering unit for metering the fuel pumped by the fuel pump, an additive tank for storing a fuel additive, an additive delivery subsystem for mixing the fuel additive with the fuel at or before the heat exchanger to generate a fuel and fuel additive mixture, and a combustor located downstream of the fuel metering unit where the fuel and fuel additive mixture is delivered for combustion. The fuel additive comprises a fuel stabilizer for reducing fuel coking. | 10-21-2010 |
20110067379 | DUAL FUEL COMBUSTOR NOZZLE FOR A TURBOMACHINE - A dual fuel combustor nozzle includes a body member including a first end portion that extends to a second end portion through an intermediate portion. The intermediate portion includes an outer wall portion and an inner wall portion with the inner wall portion defining a first fuel plenum. The dual fuel nozzle also includes an inner nozzle member arranged within the first fuel plenum. The inner nozzle member includes a first end section that extends to a second end section through an intermediate section. The intermediate section defines a second fuel plenum. The second end section being spaced from the second end portion of the body member so as to define a pre-emergence zone. | 03-24-2011 |
20120110974 | LATE LEAN INJECTION WITH ADJUSTABLE AIR SPLITS - A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors. | 05-10-2012 |
20120192542 | SYSTEM FOR CONTROLLING FUEL SUPPLY FOR A GAS TURBINE ENGINE - A system includes a turbine fuel controller configured to control a first supply of a first fuel to a turbine engine, a second supply of a second fuel to the turbine engine, and a transition between the first fuel and the second fuel. The turbine fuel controller includes a fuel integrity control logic configured to control a volume of the first fuel in a first fuel line to maintain a first fuel integrity while the turbine engine is operating on the second fuel rather than the first fuel. | 08-02-2012 |
20120198812 | APPARATUS FOR MIXING FUEL IN A GAS TURBINE - A combustor nozzle includes an inlet surface and an outlet surface downstream from the inlet surface, wherein the outlet surface has an indented central portion. A plurality of fuel channels are arranged radially outward of the indented central portion, wherein the plurality of fuel channels extend through the outlet surface. | 08-09-2012 |
20120324863 | COOLING SCHEME FOR AN INCREASED GAS TURBINE EFFICIENCY - A burner for a combustion chamber of a turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner is proposed. The injection device has at least one body arranged in the burner with at least two nozzles for introducing the at least one fuel into the burner, the body being configured with a streamlined cross-sectional profile which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The carrier air plenum is provided with holes such that carrier air exiting through the holes impinges an inner side of a leading edge portion of the body. | 12-27-2012 |
20130186057 | NAPHTHA AND PROCESS GAS/SYNGAS MIXTURE FIRING METHOD FOR GAS TURBINE ENGINES - A fuel delivery system for a gas turbine designed to efficiently transfer from one type of fuel to a separate fuel, comprising different and cooperating fuel modules, namely high hydrogen fuel gas, distillate fuel and naphtha fuel modules, each of which feeds a different liquid or gas fuel to the combustors, an atomized air delivery system for either the naphtha or distillate (or combinations thereof), an air extraction system, a plurality of distribution control valves for the high hydrogen fuel gas, distillate fuel and naphtha fuel modules, and a nitrogen purge system to purge the high hydrogen fuel gas lines to the combustors and/or flushing the naphtha lines with distillate. | 07-25-2013 |
20130239543 | GAS TURBINE ENGINE CONTROL SYSTEM WITH GAS MONITOR - A gas turbine engine configured to operate using a liquid fuel and a gaseous fuel may include a combustor system fluidly coupled to a compressor system and a turbine system. The gas turbine engine may also include a control system configured to selectively direct the gaseous fuel and the liquid fuel to the combustor system based on a concentration of a constituent in the gaseous fuel. | 09-19-2013 |
20130263571 | COMBUSTOR AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR - A combustor includes a combustion chamber that defines a longitudinal axis. A primary reaction zone is inside the combustion chamber, and a secondary reaction zone inside the combustion chamber is downstream from the primary reaction zone. A center fuel nozzle extends axially inside the combustion chamber to the secondary reaction zone, and a plurality of fluid injectors circumferentially are arranged inside the center fuel nozzle downstream from the primary reaction zone. Each fluid injector defines an additional longitudinal axis out of the center fuel nozzle that is substantially perpendicular to the longitudinal axis of the combustion chamber. | 10-10-2013 |
20140069079 | GAS TURBINE COMBUSTOR - A gas turbine combustor includes a burner disposed upstream of the combustion chamber for supplying a gas and air to an interior of the combustion chamber to hold a flame provided with a first swirler in which a gas hole and an air hole are alternately formed in a circumferential direction. A first gas is supplied to the gas hole in the first swirler and air is supplied to the air hole. A swiveling flow path is formed in the gas hole and the air hole in the burner to swivel the gas and the air and supply the gas and the air to the interior of the combustion chamber, a second gas hole is formed in the swiveling flow path in at least one of the air hole and the gas hole, and a second gas is supplied through the second gas hole. | 03-13-2014 |
20140083078 | METHOD AND SYSTEM FOR CONTROLLING CO2 EMISSIONS - A system, including a turbine fluid supply system, including a fuel supply assembly, including a first fuel supply configured to supply a first fuel to a gas turbine engine; and a second fuel supply configured to supply a second fuel to the gas turbine engine, wherein the first fuel has a greater carbon content than the second fuel, and a diluent supply assembly comprising at least one diluent supply configured to supply at least one diluent to the gas turbine engine; and a controller having instructions to control the first fuel supply, the second fuel supply, or the at least one diluent supply to adjust a percentage of carbon in a combustor of the gas turbine engine to maintain a ratio of carbonaceous emissions in an exhaust gas per unit of energy produced by the gas turbine engine at or below a threshold ratio. | 03-27-2014 |
20140130477 | TURBOMACHINE AND STAGED COMBUSTION SYSTEM OF A TURBOMACHINE - A turbomachine including a combustor in which fuel is combustible to produce a working fluid, a turbine section, which is receptive of the working fluid for power generation operations, a transition piece in which additional fuel is combustible, the transition piece being disposed to transport the working fluid from the combustor to the turbine section and a staged combustion system coupled to the combustor and the transition piece. The staged combustion system is configured to blend components of the fuel and the additional fuel in multiple modes. | 05-15-2014 |
20150082770 | Dual-Fuel Burning Gas Turbine Combustor - A dual-fuel burning gas turbine combustor having a diffusive combustion burner to burn a liquid fuel and a gaseous fuel placed at the axis of the gas turbine combustor and a plurality of pre-mixing combustion burners to burn a liquid fuel and a gaseous fuel placed on an outer circumferential side of the diffusive combustion burner, each pre-mixing combustion burner having a liquid fuel nozzle, a plurality of gaseous fuel spray holes, a plurality of air holes, and a pre-mixing chamber to mix gaseous fuel and air, wherein each pre-mixing combustion burner has a double pipe sleeve at a connected portion between end cover and the pre-mixing combustion burner, and the double pipe sleeve has an inner sleeve having a gaseous fuel flow path, an outer sleeve positioned on an outer circumferential side of the inner sleeve, and a circular spacing formed between the inner sleeve and the outer sleeve. | 03-26-2015 |
20150323189 | MULTI-FUEL TURBINE COMBUSTOR, MULTI-FUEL TURBINE COMPRISING SUCH A COMBUSTOR AND CORRESPONDING METHOD - Combustor ( | 11-12-2015 |
20150330312 | TURBINE ENGINE ASSEMBLY AND DUAL FUEL AIRCRAFT SYSTEM - A turbine engine assembly including a turbine core and a cryogenic fuel system. The turbine core includes: a compressor section; a combustion section; and a turbine section, which are axially aligned. The a cryogenic fuel system includes: a cryogenic fuel reservoir; a vaporizer heat exchanger; a liquid supply line operably coupling the fuel reservoir to an input of the vaporizer heat exchanger; a gas supply line operably coupling an output of the vaporizer heat exchanger to the combustion section; and a second heat exchanger thermally connecting the liquid supply line and the gas supply line to transfer heat from the gas supply line to the liquid supply line. | 11-19-2015 |
20150345795 | FUEL NOZZLE ASSEMBLY WITH REMOVABLE COMPONENTS - A fuel nozzle assembly ( | 12-03-2015 |
20150362194 | MULTIFUEL GAS TURBINE COMBUSTOR - To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner ( | 12-17-2015 |
20160033131 | MULTIFUEL GAS TURBINE COMBUSTOR - To provide a multifuel gas turbine combustor capable of combusting gases containing hydrogen in a high concentration with a low NOx while maintaining a low emission performance brought about by the pre-mixture combustion in the main burner, the gas turbine combustor includes a main burner ( | 02-04-2016 |
20160033138 | FUEL PLENUM FOR A FUEL NOZZLE AND METHOD OF MAKING SAME - A fuel plenum for a fuel nozzle assembly includes a gaseous fuel conduit, a conduit passage, and a liquid fuel conduit. Said gaseous fuel conduit received at a first end of said fuel plenum. Said fuel plenum is configured to distribute gaseous fuel received from said gaseous fuel conduit. Said conduit passage extends from the first end to a second end of said fuel plenum. Said conduit passage is at least partially defined by at least one interior wall of said fuel plenum. Said liquid fuel conduit defined by an outer wall and a portion of said liquid fuel conduit extending through said conduit passage. Said liquid fuel conduit outer wall is offset from said at least one interior wall. | 02-04-2016 |
20160053681 | LIQUID FUEL COMBUSTOR HAVING AN OXYGEN-DEPLETED GAS (ODG) INJECTION SYSTEM FOR A GAS TURBOMACHINE - A liquid fuel combustor for a gas turbomachine includes a combustor body, a combustor liner arranged in the combustor body defining a combustion chamber extending from a head end to a combustor discharge. The combustor liner is spaced from the combustor body forming a compressor discharge casing (CDC) airflow passage. A nozzle is arranged at the head end of the combustor liner. The nozzle includes a first inlet, a second inlet and an outlet configured and disposed to establish a flame zone. The first inlet is configured to receive a first fluid and the second inlet is configured to receive a second fluid. The second fluid includes a liquid fuel. An oxygen-depleted gas (ODG) injection system is arranged radially outwardly of the nozzle. The ODG injection system is configured and disposed to deliver an oxygen-depleted gas stream into the combustion chamber to vaporize a portion of the second fluid. | 02-25-2016 |
20160195013 | CRYOGENIC FUEL COMPOSITIONS AND DUAL FUEL AIRCRAFT SYSTEM | 07-07-2016 |
20160252254 | GAS TURBINE BURNER HUB WITH PILOT BURNER | 09-01-2016 |
060390464 | Solid, slurry, emulsive, or suspensive type fuel | 2 |
20080245052 | Integrated Biomass Energy System - An indirect-fired biomass-fueled gas turbine system with a combustor for combustion of biomass particles to produce a combustion gas, a heat exchanger providing a heat exchange relationship between combustion gas from the combustor and compressed air, and a gas turbine. The combustor may be a cyclonic combustor with a combustion liner forming a combustion chamber, a biomass feed inlet at one end of the combustion chamber formed through the combustion liner for receiving the biomass particles from a fuel feed system, wherein the biomass feed inlet is formed so that the biomass particles are introduced into the combustion chamber with a tangential component, and a plurality of air tuyeres formed through the combustion liner for receiving air, wherein at least one of the air tuyeres is arranged to introduce the air into the combustion chamber with a tangential component. | 10-09-2008 |
20100218477 | DEWATERING SYSTEM AND PROCESS FOR INCREASING THE COMBINED CYCLE EFFICIENCY OF A COAL POWERPLANT - A process for treating coal includes contacting the coal with a leaching agent configured to remove a mineral from the coal; forming a wastewater stream comprising water and a concentration of a contaminant; and contacting the wastewater stream with a first side of a reverse osmosis membrane under pressure, wherein a permeate stream comprising a reduced concentration of the contaminant permeates the reverse osmosis membrane and flows from a second side of the reverse osmosis membrane, and a concentrate stream comprising an increased concentration of the contaminant is retained on the first side of the reverse osmosis membrane. | 09-02-2010 |
060390465 | Gaseous fuel at standard temperature and pressure | 19 |
20100115913 | GAS TURBINE PLANT - The invention relates to gas turbine plants which can be used for gas turbine locomotives and mobile and stationary power plants and which use cryogenic gas fuel. The oil systems of a gas turbine engine and of actuating units are designed in the form of individual adjustable flow circuits each of which comprises fuel-oil heat exchangers, the cooling medium of which his in the form of a cryogenic gas fuel, a delivery pump and an oil tank. The cooling cavities of the fuel/oil heat exchangers are connected, at the inputs thereof, to a fuel supply and adjusting device and to a fuel heater, which is arranged, at the outputs thereof, in the sleeve of the gas turbine engine. Said invention makes it possible to design a low-consumption gas turbine plant provided with a small-sized oil-cooling and fuel-heating system. The invention makes it possible to recover the heat removed by oil from lubricated friction units of the gas turbine engine and the actuating units driven thereby and to return said heat to the thermodynamic circuit of the gas turbine engine. In addition, the power consumption for needs of the gas turbine plant is reduced, the structural design for the oil cooling system is substantially simplified and the fuel heater can be of small size due to the fact that a cryogenic gas is heated in the fuel/oil heat exchangers. | 05-13-2010 |
20100186367 | GAS TURBINE WITH INTRODUCTION OF NITROGEN - A power plant, including a compressor, in which inlet air is compressed for combustion operations, is provided and includes a separation unit, which receives and removes nitrogen from an air supply, and a system, coupled to the separation unit and an inlet disposed upstream from and in fluid communication with the compressor, which receives the nitrogen from the separation unit and delivers the nitrogen to the inlet. | 07-29-2010 |
20120260622 | REHEAT BURNER INJECTION SYSTEM - A burner, such as for a secondary combustion chamber of a gas turbine with sequential combustion having first and second combustion chambers, includes an injection device for introducing at least one gaseous fuel into the burner. The injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the gaseous fuel into the burner. The body is configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body. The body has two lateral surfaces substantially parallel to the main flow direction. At least one vortex generator is located on at least one lateral surface upstream of the at least one nozzle. | 10-18-2012 |
20130019584 | BURNER, GAS TURBINE COMBUSTOR, BURNER COOLING METHOD, AND BURNER MODIFYING METHOD - In a burner for injecting mixed gas fuel containing at least one of hydrogen and carbon monoxide into a combustion chamber of a gas turbine combustor, the burner includes a fuel nozzle for startup from which liquid fuel is injected into the combustion chamber, and a mixed fuel nozzle disposed around the fuel nozzle for injecting the mixed gas fuel. An air swirler is disposed at a downstream end of the mixed fuel nozzle and has a plurality of flow passages from which compressed air is injected into the combustion chamber, and the mixed fuel nozzle has injection ports disposed in the inner peripheral side of the flow passages of the air swirler. Cooling holes formed in the nozzle surface and positioned to face the combustion chamber introduce a part of the mixed gas fuel injected from the mixed fuel nozzle into the combustion chamber. | 01-24-2013 |
20130104520 | Hydrogen-Rich Gas Combustion Device | 05-02-2013 |
20130232943 | GRADUAL OXIDATION WITH HEAT CONTROL - Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber. | 09-12-2013 |
20130232944 | GRADUAL OXIDATION WITH HEAT CONTROL - Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber. | 09-12-2013 |
20130232945 | GRADUAL OXIDATION WITH HEAT TRANSFER - Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber. | 09-12-2013 |
20130232946 | GRADUAL OXIDATION WITH HEAT CONTROL - Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber. | 09-12-2013 |
20130232947 | STAGED GRADUAL OXIDATION - Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber. | 09-12-2013 |
20140130478 | GAS TURBOMACHINE INCLUDING A FUEL PRE-HEAT SYSTEM - A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, a combustor assembly including at least one combustor fluidically connected to the turbine portion, and an accessory mechanically linked with and driven by the turbine portion. The gas turbomachine also includes a fuel pre-heat system including a fuel pre-heat element having a fuel circuit fluidically connected to the at least one combustor arranged in a heat exchange relationship with a heating medium circuit fluidically connected to at least one of the compressor portion, the turbine portion, and the accessory. | 05-15-2014 |
20140190146 | CARBON DIOXIDE MEMBRANE SEPARATION SYSTEM IN COAL GASIFICATION PROCESS, AND INTEGRATED COAL GASIFICATION COMBINED CYCLE POWER GENERATION FACILITY USING SAME - The carbon dioxide membrane separation system in a coal gasification process contains introduction of a mixed gas of hydrogen (H | 07-10-2014 |
20140366504 | GASIFICATION FURNACE, GASIFICATION POWER PLANT, AND METHOD OF PREVENTING BLOCKAGE OF SLAG HOLE IN GASIFICATION FURNANCE - An object is to prevent blockage of a slag hole with char and slag, enabling stable operation of a gasification furnace. In a configuration in which a heat exchanger ( | 12-18-2014 |
20150337730 | TURBINE ENGINE ASSEMBLIES - Turbine engine assemblies including a turbine engine assembly having a turbine core comprising a compressor section, a combustion section, a turbine section, and a nozzle section, which are axially aligned, wherein the combustion section comprises a generally annular case having inner and outer walls, a heat exchanger comprising multiple passages in proximity to at least one of the inner and outer walls, with the passages arranged about at least a portion of the case and in fluid communication with each other such that fluid may flow through the passages and a cryogenic fuel system having a cryogenic fuel tank with a supply line coupled to one of the passages, wherein cryogenic fuel may be supplied from the cryogenic fuel tank, through the supply line, to the passages of the heat exchanger, where the fuel in the passages may be heated by the combustion section. The heat exchanger may be a single or multistage vaporizer. | 11-26-2015 |
20150375832 | Offshore Facility - The present invention relates broadly to a offshore facility. The offshore facility comprise a floating platform; a metal processing apparatus disposed on the floating platform; and a power management module adapted to manage and provide a stable power supply to the metal processing apparatus. | 12-31-2015 |
20160061108 | DIFFUSION FLAME BURNER FOR A GAS TURBINE ENGINE - A diffusion flame burner ( | 03-03-2016 |
20160114876 | SYSTEM AND METHOD FOR TREATING BOIL-OFF GAS IN SHIP - In a BOG treatment system, boil-off gas (BOG) discharged from a storage tank is compressed, most of the BOG is used as the fuel of vessel engines, and a remaining part of the BOG is liquefied by cold energy of BOG newly discharged from the storage tank and is returned to the storage tank, thereby efficiently utilizing the BOG. The BOG treatment system for a vessel includes a compressor compressing the BOG discharged from the storage tank; a medium pressure gas engine receiving at least a part of the BOG compressed by the compressor, as fuel; a heat exchanger exchanging heat between the remaining part of the BOG, which is not supplied to the medium pressure gas engine as fuel, and the BOG, which is discharged from the storage tank and is not compressed; and an expander decompressing the remaining part of the BOG cooled by the heat exchanger. | 04-28-2016 |
20160146461 | DEVICE AND SYSTEM FOR PLASMA TREATMENT OF SOLID WASTE - A device for plasma treatment of solid waste includes:
| 05-26-2016 |
20170234219 | SYNGAS BURNER SYSTEM FOR A GAS TURBINE ENGINE | 08-17-2017 |