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| Number | Title | Issue Date |
| 8091362 | Fuel injector sans support/stem A fuel nozzle is provided. The fuel nozzle includes a heat shield, a fuel tube and a plurality of support members. The support members are radially interposed between the heat shield and the fuel tube. The support members are preferably cylindrical tubes, thus creat... | 01/10/2012 |
| 7654089 | Gas-turbine combustion chamber with air-introduction ports This invention relates to a gas-turbine combustion chamber with at least one pilot burner (2) and at least one main burner (3) which are axially and radially offset relative to each other, said combustion chamber (1) comprising an outer flame-tu... | 02/02/2010 |
| 7631499 | Axially staged combustion system for a gas turbine engine An axially staged combustion system is provided for a gas turbine engine comprising a main body structure having a plurality of first and second injectors. First structure provides fuel to at least one of the first injectors. The fuel provided to the one first injec... | 12/15/2009 |
| 7621132 | Pilot combustor for stabilizing combustion in gas turbine engines The subject application is directed to burners for gas turbine engines that use a pilot flame to assist in sustaining and stabilizing the combustion process. An embodiment of the disclosed burners includes, inter alia, a burner housing, a pilot combustor and a quenc... | 11/24/2009 |
| 7546736 | Methods and apparatus for low emission gas turbine energy generation A low-emission method for producing power using a gas turbine includes premixing a plurality of fuel and air mixtures, injecting the fuel and air mixtures into a combustion chamber using a plurality of fuel nozzles, and adjusting a ratio of fuel and air injected by ... | 06/16/2009 |
| 7340900 | Method and apparatus for decreasing combustor acoustics A method for decreasing combustor acoustics in gas turbine engines is provided. The method includes fabricating a plurality of premixers, chamfering a trailing edge of a main swirler shroud of each premixer, coupling a respective one of the chamfered premixers to ea... | 03/11/2008 |
| 7290394 | Fuel injector flexible feed with moveable nozzle tip In a fuel injector assembly, for an internal combustion engine, a curved outer housing, fixed at one end, fully encloses a curved flexible fuel feed member, affixed to the housing inlet end and has a nozzle assembly operatively connected to an inner end, wherein the... | 11/06/2007 |
| 7222488 | Fabricated cowl for double annular combustor of a gas turbine engine A fabricated cowl for a double annular combustor of a gas turbine engine having a longitudinal axis extending therethrough, including an outer annular portion, an inner annular portion, and a middle annular portion. A plurality of circumferentially spaced radial slo... | 05/29/2007 |
| 7198483 | Burner unit and method for operation thereof Arranged upstream of each swirl-stabilized premix burner (1) of a burner system there is respectively an adjustable distributing device (5) with control valves (V1, . . . , V8) and/or on/off valves (V″1, . . . , V″ | 04/03/2007 |
| 7185494 | Reduced center burner in multi-burner combustor and method for operating the combustor A single stage combustor for a gas turbine having an annular array of outer fuel nozzles arranged about a center axis of the combustor; a center fuel nozzle aligned with the center axis, wherein the center fuel nozzle is substantially smaller than each of the outer ... | 03/06/2007 |
| 7171813 | Fuel injection nozzle for gas turbine combustor, gas turbine combustor, and gas turbine A fuel injection nozzle has a cylindrical nozzle body having a cavity where fuel passes through. A plurality of hollow spokes, each having an aerofoil cross section, are provided around the nozzle body. Each hollow spoke has four fuel injection holes in total on bot... | 02/06/2007 |
| 7159403 | Apparatus for assembling gas turbine engine combustors A method for assembling a gas turbine engine combustor facilitates reducing costs and time required for assembly. The combustor includes a spectacle plate, a plurality of swirlers, and a plurality of deflector plates. The method includes coupling an assembly fixture... | 01/09/2007 |
| 7155913 | Turbomachine annular combustion chamber The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several... | 01/02/2007 |
| 7143583 | Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor A gas turbine combustor comprises a premixed combustion burner disposed on the periphery of a pilot burner, an approximately cylindrical combustor liner disposed on the downstream side of the premixed combustion burner, which defines a combustion chamber in the line... | 12/05/2006 |
| 7140185 | Heatshielded article A heatshielded article includes a support 18 and at least one heatshield 20 secured adjacent to the support. The heatshield includes a shield portion 28 spaced from the support. The shield portion includes a hot side 30 and an uncoated co... | 11/28/2006 |
| 7140560 | Nozzle assembly with fuel tube deflector A deflector at the downstream end of a fuel tube deflects incoming fuel into an annular fuel channel in a fuel swirler of an injector. The deflector prevents direct impact of the cooler fuel on the exposed walls of the swirler body. The deflector can be formed by a ... | 11/28/2006 |
| 7137256 | Method of operating a combustion system for increased turndown capability A method of operating a gas turbine engine combustion system at lower load conditions while maintaining required emissions levels is disclosed. The present invention includes multiple embodiments of axial, radial, and circumferential fuel staging within a can-type c... | 11/21/2006 |
| 7137809 | Method for the production of a burner unit In the case of swirl-stabilized premix burners (1), an axial mass flow distribution of the fuel introduced which has especially favorable values with respect to characteristics such as NOx emission and maximum amplitudes of pulsations occurring is ... | 11/21/2006 |
| 7137258 | Swirler configurations for combustor nozzles and related method A combustor includes a center nozzle surrounded by a plurality of outer nozzles, the center nozzle and each of the outer nozzles having a fuel passage and an air passage, with a swirler surrounding the fuel passage and having a plurality of vanes projecting radially... | 11/21/2006 |
| 7117675 | Cooling of liquid fuel components to eliminate coking A system for cooling at least one gas turbine liquid fuel component located in a high temperature environment to eliminate coking in the component is disclosed. The system includes a sleeve surrounding the liquid fuel component, a device for providing a current of c... | 10/10/2006 |
| 7107772 | Multi-point staging strategy for low emission and stable combustion The present invention relates to an improved multi-point injector for use in a gas turbine engine or other types of combustors. The multi-point fuel injector has a plurality of nozzles arranged in at least two arrays such as concentric rings. The injector further ha... | 09/19/2006 |
| 7107773 | Turbine engine sequenced combustion Aspects of the invention relate to a method for facilitating the reduction of carbon monoxide emissions during part load operation of a turbine engine by holding high combustor temperatures. The combustor section of the turbine engine includes a plurality of combust... | 09/19/2006 |
| 7096668 | Cooling and sealing design for a gas turbine combustion system An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are lowered. An aft end of a combustion liner is telescopically received... | 08/29/2006 |
| 7096671 | Catalytic combustion system and method Aspects according to the invention relate to a catalytic combustor system for a turbine engine and an associated method. Catalytic combustors are used in connection with turbine engines because they can minimize the formation of oxides of nitrogen during combustion.... | 08/29/2006 |
| 7093419 | Methods and apparatus for operating gas turbine engine combustors A method facilitates assembling a gas turbine engine. The method comprises coupling a combustor including a dome assembly and a combustor liner that extends downstream from the dome assembly to a combustor casing that is positioned radially outwardly from the combus... | 08/22/2006 |
| 7086234 | Gas turbine combustion chamber with defined fuel input for the improvement of the homogeneity of the fuel-air mixture A gas turbine combustion chamber with a burner 7, includes means for the supply of fuel and an atomizer 6, wherein the means for the supply of fuel are provided such that the fuel is injected in areas with maximum airflow velocity. ... | 08/08/2006 |
| 7065972 | Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissions A fuel-air mixer for use in a combustion chamber of a gas turbine engine is provided. The fuel air mixing apparatus comprises an annular fuel injector having a plurality of discrete plain jet orifices, a first swirler wherein the first swirler is located upstream fr... | 06/27/2006 |
| 7055331 | Burner arrangement for the annular combustion chamber of a gas turbine In a burner arrangement for the annular combustion chamber of a gas turbine, a plurality of burners are arranged above one another, in each case in pairs in the radial direction, on concentric rings. In a burner arrangement of this type, the mechanical integrity of ... | 06/06/2006 |
| 7022940 | Combustor linear and method for making thereof A combustor liner is provided having first and second annular bands which define an overlapping circumferential joint area, wherein a weld is disposed in the joint area encompassing substantially all of the axial length of the joint area. A method for producing such... | 04/04/2006 |
| 7007479 | Method and apparatus to decrease combustor emissions A method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and an annular centerbody extending therebetween. The method comprises injecting ... | 03/07/2006 |
| 6996991 | Fuel injection system for a turbine engine A fuel system for a turbine engine for reducing CO emissions caused during fuel staging processes while the turbine engine operates at reduced loads. The fuel system may include a first premix injector assembly and a second premix injector assembly, each formed from... | 02/14/2006 |
| 6983605 | Methods and apparatus for reducing gas turbine engine emissions A gas turbine engine includes a combustor system including a lean premix combustor and a water delivery system. The combustor is operable with a fuel/air mixture equivalence ratio less than one and the water delivery system is configured to supply at least one of wa... | 01/10/2006 |
| 6962055 | Multi-point staging strategy for low emission and stable combustion The present invention relates to an improved multi-point injector for use in a gas turbine engine or other types of combustors. The multi-point fuel injector has a plurality of nozzles arranged in at least two arrays such as concentric rings. The injector further ha... | 11/08/2005 |
| 6957537 | Combustor of a gas turbine having a nozzle pipe stand Manifolds are shaped cross star having curved surfaces inside thereof, and holes are bored in four corners of the manifolds. In mounting a combustor to a casing, oil in the manifolds is transmitted to the holes by way of the curved surfaces. As a result of this, oil... | 10/25/2005 |
| 6935116 | Flamesheet combustor A gas turbine combustion system having reduced emissions and improved flame stability at multiple load conditions is disclosed. The improved combustion system accomplishes this through complete premixing, a plurality of fuel injector locations, combustor geometry, a... | 08/30/2005 |
| 6931831 | Distributor purge valve A combination distributor purge valve unit for a turbine engine has a pilot air section, a fuel section, a distributor section and a purge air section. A spool moves along a spool axis to control flow through six sets of radially arranged removable fill nozzles and ... | 08/23/2005 |
| 6931853 | Gas turbine combustor having staged burners with dissimilar mixing passage geometries A gas turbine combustor (10) having a first grouping (64) of pre-mix burners (12, 12′, 12″) having mixing passages (36) that are geometrically different than the mixing passages (38) of a second grouping (66) of pre-mix ... | 08/23/2005 |
| 6886341 | Gas-turbine engine combustor A gas-turbine engine combustor having a plurality of venturi mixers, each connected to an air supply path that passes air compressed by a compressor and to a supply source of gaseous fuel, which mix the air and the gaseous fuel to produce an air-fuel mixture and sup... | 05/03/2005 |
| 6871501 | Method and apparatus to decrease gas turbine engine combustor emissions A method enables a gas turbine engine including a combustor to be operated. The combustor includes a mixer assembly including an air swirler, a premixer, a dome plate, and a heat shield. The method comprises discharging fluids from the air swirler into the premixer,... | 03/29/2005 |
| 6862889 | Method and apparatus to decrease combustor emissions A method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and an annular centerbody extending therebetween. The method comprises injecting ... | 03/08/2005 |
