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| Number | Title | Issue Date |
| 8443607 | Coaxial fuel and air premixer for a gas turbine combustor An air/fuel premixer comprising a peripheral wall defining a mixing chamber, a nozzle disposed at least partially within the peripheral wall comprising an outer annular wall spaced from the peripheral wall so as to define an outer air passage between the peripheral ... | 05/21/2013 |
| 8438851 | Combustor assembly for use in a turbine engine and methods of assembling same A fuel nozzle assembly for use with a turbine engine is described herein. The fuel nozzle assembly includes a plurality of fuel nozzles positioned within an air plenum defined by a casing. Each of the plurality of fuel nozzles is coupled to a combustion liner defini... | 05/14/2013 |
| 8424311 | Premixed direct injection disk A fuel/air mixing disk for use in a fuel/air mixing combustor assembly is provided. The disk includes a first face, a second face, and at least one fuel plenum disposed therebetween. A plurality of fuel/air mixing tubes extend through the pre-mixing disk, each mixin... | 04/23/2013 |
| 8424310 | Mixing chamber A mixing chamber with a wall and at least one vortex generating element arranged on the wall is provided. The vortex generating element has at least three surfaces, at least one of the surfaces forming a top surface and the other surfaces forming at least first and ... | 04/23/2013 |
| 8413445 | Method and system for porous flame holder for hydrogen and syngas combustion A fuel nozzle assembly for a combustor in a gas turbine including: a gaseous fuel passage and a fuel nozzle at a distal end of the passage; an air tube concentric with the fuel nozzle and defining an air passage between the air tube and the fuel nozzle, wherein the ... | 04/09/2013 |
| 8413446 | Fuel injector arrangement having porous premixing chamber A fuel injector arrangement for a turbine engine is disclosed. The fuel injector arrangement may have a combustion chamber, a plenum, an injector, and a premixing chamber configured to receive the injector. The premixing chamber may be at least partially disposed wi... | 04/09/2013 |
| 8397510 | Combustor for gas turbine A combustor for a gas turbine capable of performing stable combustion even by using high temperature air, comprising a first burner (5) jetting fuel and air into a combustion chamber (2) and a second burner (8) causing the circulating jet of the... | 03/19/2013 |
| 8371123 | Apparatus for conditioning airflow through a nozzle A nozzle includes a center body and a shroud surrounding the center body to define an annular passage. An arcuate annular guide extending from a point radially inward of the shroud to a point radially outward of the shroud defines a first airflow between the arcuate... | 02/12/2013 |
| 8365531 | Fuel injector A fuel injector head for a gas turbine engine the head comprising a pilot injector and a main injector located radially outwardly of the pilot injector. A concentric separates the pilot injector from the main injector and bounding a duct through which in use a fuel ... | 02/05/2013 |
| 8365532 | Apparatus and method for a gas turbine nozzle A nozzle includes an inlet, an outlet, and an axial centerline. A shroud surrounding the axial centerline extends from the inlet to the outlet and defines a circumference. The circumference proximate the inlet is greater than the circumference at a first point downs... | 02/05/2013 |
| 8347630 | Air-blast fuel-injector with shield-cone upstream of fuel orifices An air-blast fuel nozzle assembly includes a housing having an inner surface defining an interior chamber around a central axis. The inner surface terminates in an exit aperture. An air swirler pneumatically communicates with the interior chamber and has vanes opera... | 01/08/2013 |
| 8327642 | Multiple tube premixing device The present application provides a premixer for a combustor. The premixer may include a fuel plenum with a number of fuel tubes and a burner tube with a number of air tubes. The fuel tubes extend about the air tubes. ... | 12/11/2012 |
| 8322143 | System and method for injecting fuel According to various embodiments, a system includes a staggered multi-nozzle assembly. The staggered multi-nozzle assembly includes a first fuel nozzle having a first axis and a first flow path extending to a first downstream end portion, wherein the first fuel nozz... | 12/04/2012 |
| 8322142 | Trapped vortex combustion chamber A combustor for a gas turbine engine is disclosed which is able to operate with high combustion efficiency, and low nitrous oxide emissions during gas turbine operations. The combustor consists of a can-type configuration which combusts fuel premixed with air and de... | 12/04/2012 |
| 8312722 | Flame holding tolerant fuel and air premixer for a gas turbine combustor A fuel nozzle with active cooling is provided. It includes an outer peripheral wall, a nozzle center body concentrically disposed within the outer wall in a fuel and air pre-mixture. The fuel and air pre-mixture includes an air inlet, a fuel inlet and a premixing pa... | 11/20/2012 |
| 8312723 | System for injecting a mixture of air and fuel into a turbomachine combustion chamber A system for injecting a mixture of air and fuel into a turbomachine combustion chamber is disclosed. The system includes a fuel injector and a Venturi with an interior surface delimiting a premixing chamber. The Venturi includes an internal annular airflow cavity w... | 11/20/2012 |
| 8291705 | Ultra low injection angle fuel holes in a combustor fuel nozzle A fuel nozzle for a combustor includes a mixing passage through which fluid is directed toward a combustion area and a plurality of swirler vanes disposed in the mixing passage. Each swirler vane of the plurality of swirler vanes includes at least one fuel hole thro... | 10/23/2012 |
| 8276385 | Staged multi-tube premixing injector A fuel injection nozzle includes a body member having an upstream wall opposing a downstream wall, and an internal wall disposed between the upstream wall and the downstream wall, a first chamber partially defined by the an inner surface of the upstream wall and a s... | 10/02/2012 |
| 8266911 | Premixing device for low emission combustion process A premixing device is provided. The premixing device includes an air inlet configured to introduce compressed air into a mixing chamber of the premixing device and a fuel plenum configured to provide a fuel to the mixing chamber via a circumferential slot and over a... | 09/18/2012 |
| 8240150 | Lean direct injection diffusion tip and related method A nozzle for a gas turbine combustor includes a first radially outer tube defining a first passage having an inlet and an outlet, the inlet adapted to supply air to a reaction zone of the combustor. A center body is located within the first radially outer tube, the ... | 08/14/2012 |
| 8234871 | Method and apparatus for delivery of a fuel and combustion air mixture to a gas turbine engine using fuel distribution grooves in a manifold disk with discrete air passages A nozzle has combustion air passages extending from a first, upstream end to a second, downstream end. A fuel distribution manifold is associated with the first, upstream end of the nozzle. Combustion air passages correspond to, and align with the air passages in th... | 08/07/2012 |
| 8234872 | Turbine air flow conditioner A system includes an air flow conditioner configured to mount in an air chamber separated from a combustion chamber of a turbine combustor. The air flow conditioner comprises a perforated annular wall configured to direct an air flow in both an axial direction and a... | 08/07/2012 |
| 8225611 | System for vaporization of liquid fuels for combustion and method of use A gas stream with a reduced oxygen concentration relative to ambient air is used to vaporize a liquid fuel or liquefied higher hydrocarbon gas, or is mixed with a vaporized gas, and the reduced oxygen vaporized fuel gas is fed to a combustion device such as a premix... | 07/24/2012 |
| 8220269 | Combustor for a gas turbine engine with effusion cooled baffle A combustor (1) for a gas turbine engine, particularly for a gas turbine having sequential combustion, includes a combustor wall (4) defining a mixing region (5) and a combustion region (6). The mixing region (5) has at least one f... | 07/17/2012 |
| 8220270 | Method and apparatus for affecting a recirculation zone in a cross flow Disclosed is a cross flow apparatus including a surface and at least one outlet located at the surface. The cross flow apparatus further includes at least one guide at the surface configured to direct an intersecting flow flowing across the surface and increase a ve... | 07/17/2012 |
| 8209986 | Multi-tube thermal fuse for nozzle protection from a flame holding or flashback event A protection system for a pre-mixing apparatus for a turbine engine, includes: a main body having an inlet portion, an outlet portion and an exterior wall that collectively establish a fuel delivery plenum; and a plurality of fuel mixing tubes that extend through at... | 07/03/2012 |
| 8205452 | Apparatus for fuel injection in a turbine engine In one embodiment, a system includes a fuel nozzle that includes a fuel injector configured to output a fuel flow and a premixer tube disposed about the fuel flow output from the fuel injector. The premixer tube includes a perforated portion and a non-perforated por... | 06/26/2012 |
| 8196409 | Gas turbine engine fuel supply arrangement using plural distinct fuels A fuel supply arrangement for a gas turbine burner is provided. The fuel distribution arrangement includes a rear section external to the burner located between a turbine wall and a fuel distribution system interface directing fuel into fuel supply circuits. The fue... | 06/12/2012 |
| 8186162 | Acoustically tuned combustion for a gas turbine engine A fuel nozzle for a turbine engine has a central body member with a pilot, a surrounding barrel housing, a mixing duct and an air inlet duct. The fuel nozzle additionally has a main fuel injection device located between the air inlet duct and the mixing duct. The ma... | 05/29/2012 |
| 8166763 | Gas turbine fuel injector with a removable pilot assembly A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing having a longitudinal axis. The injector housing includes one or more fuel inlets, one or more fuel galleries annularly disposed about the longitudinal axis, and an... | 05/01/2012 |
| 8161750 | Fuel nozzle for a turbomachine A turbomachine includes a compressor, a turbine, and a combustor operatively connected to the turbine. The turbomachine further includes a cap member mounted to the combustor. The cap member includes a first surface and a second surface. A combustion chamber is defi... | 04/24/2012 |
| 8127549 | Burner and gas turbine combustor A burner is provided that has high flame stability and reduces NOx emissions. In the burner, air holes of an air hole member have a central axis inclined relative to a burner central axis. The leading end portion of a first fuel nozzle is configured to be abl... | 03/06/2012 |
| 8117845 | Systems to facilitate reducing flashback/flame holding in combustion systems A method for assembling a premixing injector is provided. The method includes providing a centerbody including a center axis and a radially outer surface, and providing an inlet flow conditioner. The inlet flow conditioner includes a radially outer wall, a radially ... | 02/21/2012 |
| 8113000 | Flashback resistant pre-mixer assembly A pre-mixer assembly associated with a fuel supply system for mixing of air and fuel upstream from a main combustion zone in a gas turbine engine. The pre-mixer assembly includes a swirler assembly disposed about a fuel injector of the fuel supply system and a pre-m... | 02/14/2012 |
| 8065880 | Premixed combustion burner for gas turbine A premixed combustion burner for a gas turbine can efficiently premix fuel and air to produce fuel gas having a uniform concentration, while reliably achieving prevention of flash back by making the flow rate of fuel gas substantially uniform. The premixed combustio... | 11/29/2011 |
| 8047001 | Media mixing insert for turbine blade in turbine engine The invention relates to a blade for a turbine comprising a blade wall, a first channel for guiding a first medium and a second channel for guiding a second medium that can be supplied to the turbine blade separately from the first medium. In order to combine both m... | 11/01/2011 |
| 8037689 | Turbine fuel delivery apparatus and system A fuel nozzle for a turbine is disclosed. The fuel nozzle includes a housing, a plurality of fuel passages disposed within the housing, and a plurality of air passages disposed within the housing. A total flow area of the plurality of fuel passages is substantially ... | 10/18/2011 |
| 8033112 | Swirler with gas injectors A swirler for premixing a flow of fuel and a flow of air provided to a burner for a gas turbine engine is provided. The burner is provided with a swirler for mixing the air and the fuel and wherein the swirler is provided with swirler wings, wherein a channel formed... | 10/11/2011 |
| 8015813 | Fuel injector for injecting fuel into a turbomachine combustion chamber A fuel injector for injecting fuel into a turbomachine combustion chamber, the injector presenting an injector nose for connection to an injection system fastened to the end wall of said combustion chamber, the injector nose comprising: ... | 09/13/2011 |
| 7975486 | Burner for premix-type combustion The invention relates to a burner for premix-type combustion having a cavity which has at least one tangential air inlet slot for the supply of a combustion air flow, a device for the injection of fuel into the cavity which is provided in the region of a burner axis... | 07/12/2011 |
