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| Application No. | Application Title | Issue Date |
| 20120102958 | LATE LEAN INJECTION MANIFOLD A late lean injection (LLI) manifold is provided and includes a central nozzle and first and second side nozzles positioned at circumferential locations defined around a vessel, a connector, a first leg, to which the connector is connected, formed to define a tube exten... | 05/03/2012 |
| 20120079828 | Gas Turbine Combustor A gas turbine combustor comprising a fuel nozzle for injecting mixed gas of fuel and air, a cylindrical liner for burning and reacting the mixed gas of fuel and air in a combustion chamber, a transition piece which is a flow path for leading combustion gas generated in ... | 04/05/2012 |
| 20120067051 | GAS TURBINE ENGINE AND COMBUSTOR The present invention provides in one embodiment a unique gas turbine engine. Another embodiment is a unique gas turbine engine combustion system. Still another embodiment is a unique gas turbine engine combustor. Other embodiments include apparatuses, systems, devices,... | 03/22/2012 |
| 20120047902 | FUEL DELIVERY SYSTEM FOR A TURBINE ENGINE A fuel delivery system for a turbine engine has at least one fuel injector having an upstream orifice arrangement that produces a first pressure drop of flowing fuel and a downstream orifice arrangement that produces a second pressure drop of the flowing fuel. The upstr... | 03/01/2012 |
| 20120047901 | REHEAT BURNER A reheat burner includes a channel with a lance projecting thereinto to inject a fuel over an injection plane perpendicular to a channel longitudinal axis. The channel and lance define a vortex generation zone upstream of the injection plane and a mixing zone downstream... | 03/01/2012 |
| 20120031098 | FUEL NOZZLE WITH CENTRAL BODY COOLING SYSTEM A fuel nozzle for turbine engine includes a cooling shroud located at the downstream end of the fuel nozzle to help cool the downstream end of the fuel nozzle. The cooling shroud surrounds the exterior circumference of the downstream end of the fuel nozzle. A flow of ai... | 02/09/2012 |
| 20120023964 | LIQUID-FUELED PREMIXED REVERSE-FLOW ANNULAR COMBUSTOR FOR A GAS TURBINE ENGINE A reverse flow annular combustor for a gas turbine includes a pre-vaporizer/pre-mixing region within a dome section, a liquid fuel injection system feeding the pre-mixing region, a combustion region downstream of the pre-vaporizer/pre-mixing region, a means for guarante... | 02/02/2012 |
| 20110314826 | Burner Assembly A burner assembly for a firing system for firing fluidic fuels is provided. The burner assembly has a burner hub, an air inlet channel and a fuel inlet channel, wherein the fuel inlet channel is at least partially designed in the burner hub. A screening wall is arranged... | 12/29/2011 |
| 20110308254 | Turbine Engine Fuel Injector A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapo... | 12/22/2011 |
| 20110289928 | AIR/FUEL SUPPLY SYSTEM FOR USE IN A GAS TURBINE ENGINE A fuel injector for use in a gas turbine engine combustor assembly. The fuel injector includes a main body and a fuel supply structure. The main body has an inlet end and an outlet end and defines a longitudinal axis extending between the outlet and inlet ends. The main... | 12/01/2011 |
| 20110289929 | TURBOMACHINE FUEL NOZZLE A turbomachine includes a compressor, a turbine operatively coupled to the compressor, and a combustor fluidly linking the compressor and the turbine. The combustor includes at least one fuel nozzle. The at least one fuel nozzle includes a flow passage including a body ... | 12/01/2011 |
| 20110265482 | POCKETED AIR AND FUEL MIXING TUBE An improved mixing tube design and fuel nozzle that allows for a more uniform and thorough mixing of fuel and air being fed to the combustor of a gas turbine engine, wherein each of a plurality of mixing tubes comprises a pair of concentric hollow cylinders that define ... | 11/03/2011 |
| 20110265485 | FLUID COOLED INJECTION NOZZLE ASSEMBLY FOR A GAS TURBOMACHINE A turbomachine includes a fluid cooled injection nozzle assembly. The fluid cooled injection nozzle assembly includes an inner conduit portion that includes a body portion having first end portion to a tip end portion. The body portion includes an outer surface and an i... | 11/03/2011 |
| 20110247342 | SYSTEM AND METHOD FOR A COMBUSTOR NOZZLE A nozzle includes a center body and a shroud circumferentially surrounding at least a portion of the center body to define an annular passage between the center body and the shroud. The nozzle further includes a bimetallic guide between the center body and the shroud. A... | 10/13/2011 |
| 20110247338 | FUEL LANCE FOR A BURNER Disclosed is a fuel lance for a burner, in particular a gas turbine burner, including a tip that has a nozzle surface including at least two fuel nozzles. The nozzle surface is provided with slots between the fuel nozzles. As a rule, the lance is provided for operation ... | 10/13/2011 |
| 20110247314 | COMBUSTOR EXIT TEMPERATURE PROFILE CONTROL VIA FUEL STAGING AND RELATED METHOD A gas turbine combustor includes a combustion chamber defined by a combustor liner, the combustor liner having an upstream end cover supporting one or more nozzles arranged to supply fuel to the combustion chamber where the fuel mixes with air supplied from a compressor... | 10/13/2011 |
| 20110239621 | Fiber optic microphones for active combustion control Disclosed is a fuel injector for a gas turbine engine combustor that includes a fuel nozzle for injecting fuel into the gas turbine engine combustor and a fiber optic microphone operatively associated with the fuel nozzle for measuring acoustic pressure differentials wi... | 10/06/2011 |
| 20110239653 | ANNULAR RING-MANIFOLD QUATERNARY FUEL DISTRIBUTOR A combustor section is provided and includes one or more annular quaternary fuel manifolds mounted within an annular passage defined between a casing and a cap assembly of a combustor through which air and/or a fuel/air mixture flows upstream from a fuel nozzle support,... | 10/06/2011 |
| 20110219779 | LOW EMISSION COMBUSTION SYSTEMS AND METHODS FOR GAS TURBINE ENGINES A combustion system for a gas turbine engine is provided. The system includes a forward liner; an aft liner; a combustion chamber formed by the forward liner and the aft liner, the combustion chamber defining a lean combustion zone and a pilot combustion zone; a premixi... | 09/15/2011 |
| 20110219776 | AERODYNAMIC FLAME STABILIZER A flame stabilizer is in fluid communication with a combustor of a gas turbine engine. The flame stabilizer has a body with an aerodynamic shape that creates a flow recirculation zone by injection of fluid through a plurality of holes in the body of the flame stabilizer... | 09/15/2011 |
| 20110203294 | FUEL INJECTION SYSTEM FOR A COMBUSTION CHAMBER OF A TURBOMACHINE A fuel injection system for an annular combustion chamber of a turbomachine, the system comprising support means for supporting and centering a fuel injector head, and a bowl arranged downstream from the support means and including at its downstream end an annular colla... | 08/25/2011 |
| 20110197587 | MULTI-TUBE PREMIXING INJECTOR A fuel injection nozzle includes at least one tube disposed in the nozzle having a venturi shaped profile defining a gas flow path including an inlet operative to receive a first gas, at least one port operative to emit a second gas into the gas flow path, and an outlet... | 08/18/2011 |
| 20110185741 | INJECTION NOZZLE AND METHOD FOR OPERATING AN INJECTION NOZZLE An injection nozzle (10), especially for injecting liquid fuel, preferably crude oil, into the combustion chamber of a gas turbine, includes an inner chamber (16) which extends along a nozzle axis (19), conically tapers to a concentric nozzle orific... | 08/04/2011 |
| 20110173982 | GAS TURBINE ENGINE FUEL CONVEYING MEMBER A fuel conveying member for a gas turbine engine, the fuel conveying member including a fuel manifold having a plurality of fuel nozzles extending therefrom. The fuel manifold is mounted within the engine by a support system, including integral attachment lugs on the fu... | 07/21/2011 |
| 20110167828 | COMBUSTOR ASSEMBLY FOR A TURBINE ENGINE THAT MIXES COMBUSTION PRODUCTS WITH PURGE AIR A combustor assembly for a turbine engine includes a fuel nozzle located at an upstream end of the combustor assembly. The fuel nozzle includes both a fuel delivery passageway and a purge air passageway. The purge air passageway conveys a flow of purge air to cool the f... | 07/14/2011 |
| 20110167829 | FUEL CONTROL ARRANGEMENTS Fuel injection apparatus 54, for a gas turbine engine, includes pilot fuel injection circuits 42 which supply pilot injectors 44 with fuel from a manifold 60, through a pilot control valve 46. The state of the control valve 46 i... | 07/14/2011 |
| 20110167830 | VIBRATION DAMPER Fuel injector assemblies with frictionally damped fuel supply members, including fuel feed strips. More particularly, the invention provides friction dampers and/or assemblies that frictionally damp movement of fuel supply members in at least one direction. Some of the ... | 07/14/2011 |
| 20110162371 | Fuel Nozzle with Integrated Passages and Method of Operation Disclosed is a method of operating a secondary fuel nozzle for a turbomachine combustor including delivering a flow of pilot fuel through a pilot fuel channel toward a combustion zone and delivering a flow of air through a plurality of transfer passages arranged around ... | 07/07/2011 |
| 20110162372 | INTEGRAL FLANGE CONNECTION FUEL NOZZLE BODY FOR GAS TURBINE A fuel nozzle for a gas turbine includes a fuel nozzle body or endcover. The fuel nozzle body or endcover includes at least one seal surface. The fuel nozzle also includes at least one flexible hose and at least one flange connected to the flexible hose. The at least on... | 07/07/2011 |
| 20110162373 | FUEL NOZZLE FOR A TURBINE ENGINE WITH A PASSIVE PURGE AIR PASSAGEWAY A secondary fuel nozzle for a turbine includes a passive purge air passageway which provides purge air to the secondary nozzle at all times that the nozzle is in operation. The passive purge air passageway draws in air from a location adjacent an upstream end of the noz... | 07/07/2011 |
| 20110162374 | ARTICLES HAVING DAMPING COATINGS THEREON An article, such as a bucket, a blade, a nozzle, a vane, a strut, a fuel nozzle, a combustion casing, and a transition piece, the article having a damping coating comprising approximately 8 wt % to approximately 15 wt % Y2O3 and approximately 19 wt... | 07/07/2011 |
| 20110146285 | PULSE DETONATION SYSTEM WITH FUEL LEAN INLET REGION In one embodiment, a pulse detonation system includes a pulse detonation tube and an air valve disposed at an upstream end of the pulse detonation tube. The air valve is configured to provide an air flow into the pulse detonation tube. The pulse detonation system also i... | 06/23/2011 |
| 20110138813 | IMPURITY DETECTION IN COMBUSTOR SYSTEMS The present invention discloses a combustor system and method of measuring impurities in the combustion system. The combustion system includes an up-stream fuel injection point; a down-stream turbine combustor; a flame zone in the turbine combustor comprising a pluralit... | 06/16/2011 |
| 20110113783 | PREMIXING APPARATUS FOR FUEL INJECTION IN A TURBINE ENGINE In one embodiment, a system includes a fuel nozzle that includes a fuel injector that includes a fuel port and a premixer tube. The premixer tube includes a wall disposed about a central passage, multiple air ports extending through the wall into the central passage, an... | 05/19/2011 |
| 20110089267 | FUEL NOZZLE SEAL SPACER AND METHOD OF INSTALLING THE SAME The present application provides a method of mounting lip seals within a sleeve assembly of a fuel nozzle. The method may include the steps of sliding a first lip seal along a second diameter tube until the first lip seal contacts a first tube flange of a first diameter... | 04/21/2011 |
| 20110083440 | HIGH STRENGTH CROSSOVER MANIFOLD AND METHOD OF JOINING A secondary fuel nozzle includes a plurality of tubes axially extending downstream within the secondary fuel nozzle, the tubes defining passages operable to allow a flow of fluid to flow through each of the passages, the passages including an outermost tertiary passage ... | 04/14/2011 |
| 20110079013 | FUEL INJECTOR AND AERODYNAMIC FLOW DEVICE A gas turbine engine includes a reverse flow annular combustor having a liner with opposing ends. One end includes apertures configured to receive compressed air, and an outlet is provided at the other end and is configured to connect to a turbine nozzle. A fuel injecto... | 04/07/2011 |
| 20110067402 | Fuel Nozzle Assembly for Use in a Combustor of a Gas Turbine Engine A fuel nozzle assembly for use in a combustor apparatus of a gas turbine engine. An outer housing of the fuel nozzle assembly includes an inner volume and provides a direct structural connection between a duct structure and a fuel manifold. The duct structure defines a ... | 03/24/2011 |
| 20110056206 | Fuel Injector for Use in a Gas Turbine Engine A fuel injector in a combustor apparatus of a gas turbine engine. An outer wall of the injector defines an interior volume in which an intermediate wall is disposed. A first gap is formed between the outer wall and the intermediate wall. The intermediate wall defines an... | 03/10/2011 |
| 20110016866 | APPARATUS FOR FUEL INJECTION IN A TURBINE ENGINE In one embodiment, a system includes a fuel injector including a liquid fuel passage extending to a first port in a tip portion. The fuel injector also includes a selectable flow passage extending to a second port in the tip portion. The selectable flow passage surround... | 01/27/2011 |
