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| Number | Title | Issue Date |
| 8156746 | Lean direct injection atomizer for gas turbine engines A lean direct injection fuel nozzle for a gas turbine is disclosed which includes a radially outer main fuel delivery system including a main inner air swirler defined in part by a main inner air passage having a radially inner wall with a diverging downstream surfa... | 04/17/2012 |
| 8122725 | Methods and systems for operating gas turbine engines Methods and systems for delivering fuel in a gas turbine engine are provided. The system includes a plurality of can annular combustors that includes at least a first set of combustors of the plurality of can annular combustors and at least a second set of combustor... | 02/28/2012 |
| 8096135 | Pure air blast fuel injector An air blast fuel injector for a gas turbine engine includes an elongate feed arm having an inlet fitting for receiving fuel and for distributing the fuel to first and second fuel delivery conduits extending through the feed arm. A nozzle body is operatively connect... | 01/17/2012 |
| 8082739 | 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 compre... | 12/27/2011 |
| 8079220 | Fuel distribution manifold system for gas turbine engines A fuel distribution manifold system for a gas turbine engine is disclosed that includes a plurality of interconnected manifold segments, each manifold segment extending between a pair of fittings, each manifold segment including at least one fuel transfer tube and a... | 12/20/2011 |
| 8069671 | Burner fuel lance configuration and method of use A burner (1) for a combustion chamber of a turbogroup includes a swirl generator (2), a mixer (3), and a lance (4) for introducing pilot fuel into a combustion space (10). In order to stabilize combustion, the lance (4) is d... | 12/06/2011 |
| 8056344 | Gas turbine engine and method for reducing turbine engine combustor gaseous emission In a turbine engine hydrogen is injected into the combustor in response to a power output level of the turbine engine. In a preferred embodiment, gaseous hydrogen is always injected at low-power operations and switched off at mid-power and high-power operations.... | 11/15/2011 |
| 8033117 | NOx adjustment method for gas turbine combustors A method for controlling NOx emissions from a gas turbine having a fuel adjustment system may include setting an outer nozzle fuel flow to achieve a desired level of combustion dynamics for at least one of a plurality of combustion chambers, determining a delta adju... | 10/11/2011 |
| 8024934 | System and method for attenuating combustion oscillations in a gas turbine engine A system and method for modifying the supply of fuel to injectors to attenuate combustion oscillations in a gas turbine engine. The gas turbine engine may comprise a combustor, a plurality of injectors and a manifold. The plurality of injectors may be operable to pr... | 09/27/2011 |
| 8006500 | Swirl combustor with counter swirl fuel slinger A combustor for a small gas turbine engine in which a compressor discharges a swirling air flow into the combustor, and a fuel impeller is rotatably connected to the compressor and slings atomized fuel into the combustor in a direction to produce a stagnation zone w... | 08/30/2011 |
| 7926287 | Method of operating a gas turbine engine A method of operating a gas turbine engine having a rotatable turbine shaft with an electric machine mounted to the shaft. The method includes providing supplemental acceleration and/or deceleration of the turbine shaft of the gas turbine engine through the use of t... | 04/19/2011 |
| 7921651 | Operation of dual gas turbine fuel system The present application provides a method of operating a dual gas fuel delivery system comprising selecting a manifold and fuel flow split; setting the stroke of a high-energy gas control valve based on the fuel split; measuring the primary manifold nozzle pressure ... | 04/12/2011 |
| 7810336 | System for introducing fuel to a fluid flow upstream of a combustion area Aspects of the invention relate to a system and method for introducing fuel to the flow of air along a surface upstream of a combustion area. Fuel injectors can be used to deliver fuel to the air flow at or near the boundary layer of the air flow. The fuel injectors... | 10/12/2010 |
| 7784287 | Pulse detonation firing detuning and frequency modulated firing An aircraft engine is provided with at least one pulse detonation device, and the operational frequency of the pulse detonation device is varied over an operational range of frequencies around a mean frequency value. The pulse detonation device can be positioned ups... | 08/31/2010 |
| 7770400 | Non-linear fuel transfers for gas turbines A method for controlling the rate of transfer between operation with gas and liquid fuel types to minimize the time in undesirable operational mode, thereby preventing excessive wear and damage to gas turbine hardware. The method includes completing a fuel prefill f... | 08/10/2010 |
| 7716933 | Multi-channel fuel manifold A fuel manifold for a gas turbine engine having a first peripheral surface having a first channel defined therein and a second peripheral surface having a second channel defined therein, each of the first and second channels being sealingly enclosed to define a corr... | 05/18/2010 |
| 7665309 | Secondary fuel delivery system A secondary fuel delivery system for delivering a secondary stream of fuel and/or diluent to a secondary combustion zone located in the transition piece of a combustion engine, downstream of the engine primary combustion region is disclosed. The system includes a ma... | 02/23/2010 |
| 7654092 | System for modulating fuel supply to individual fuel nozzles in a can-annular gas turbine A fuel modulation system usable in can-annular combustor systems of turbine engines for more efficiently managing fuel flow to reduce the amount of NOx while maintaining appropriate combustor flame temperatures. The fuel modulation system controls individ... | 02/02/2010 |
| 7654091 | Method and apparatus for cooling gas turbine engine combustors A method for operating a gas turbine engine includes channeling fluid from a cooling fluid source to a combustor that includes at least one deflector and flare cone. The deflector and flare cone are coupled together and are configured to define a cooling fluid chann... | 02/02/2010 |
| 7594402 | Method for the introduction of fuel into a premixing burner A method and a device for the introduction of fuel into a premixing burner, with a pilot gas feed and a premix gas feed for the operation of a gas turbine in the entire load range, in which the pilot gas feed is carried out via a burner lance provided in the premixi... | 09/29/2009 |
| 7568349 | Method for controlling combustion device dynamics A method for controlling a combustion dynamics level within a combustion device includes defining a high dynamics operating state at a first fuel split ratio. The first fuel split ratio is a ratio of an amount of fuel supplied to the combustion device through a firs... | 08/04/2009 |
| 7565805 | Method for operating gas turbine engine systems Methods and systems for operating a gas turbine engine system include an electrical generator configured to provide electrical energy to a load, a gas turbine engine including at least one combustor that includes a plurality of fuel injection points configured to in... | 07/28/2009 |
| 7546740 | Nozzle A fuel injector has a number of groups of nozzles. The groups are generally concentric with an injector axis. Each nozzle defines a gas flowpath having an outlet for discharging a fuel/air mixture jet. There are means for introducing the fuel to the air. One or more... | 06/16/2009 |
| 7509811 | 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... | 03/31/2009 |
| 7467518 | Externally fueled trapped vortex cavity augmentor A gas turbine engine augmentor includes an externally fueled annular trapped vortex cavity having a cavity opening open to an exhaust flowpath and a sole source of fuel located upstream of the trapped vortex cavity and being operable for injecting fuel into the exha... | 12/23/2008 |
| 7448218 | Premix burner and method for burning a low-calorie combustion gas The invention relates to a pre-mix burner for burning a low-calorie combustion gas, said burner comprising an air duct which extends along an axis of the burner and can be used to supply combustion air. A swirling device is arranged in the air duct and is used to ap... | 11/11/2008 |
| 7437876 | Augmenter swirler pilot A turbofan gas turbine engine augmenter includes a fuel/air swirler disposed between an axially extending bypass flowpath and an axially extending exhaust flowpath. A swirler inlet is axially open to and positioned substantially normal to the bypass flowpath and a s... | 10/21/2008 |
| 7434404 | Method for operating a gas turbine combustion chamber including a plurality of burners arranged in groups A method for operating a combustion chamber (1) for a gas turbine. The combustion chamber (1) has a combustion space (2) and a plurality of burners (3), which are each arranged at an inlet (13) of the combustion space (2). T... | 10/14/2008 |
| 7430868 | Method of operating a thermal power plant A method of operating a thermal power plant, such as a gas turbine power plant, in which a rotary unit, such as at least one gas turbine stage, is driven by burning gaseous fuel inside a combustion chamber, with hot gases being formed, the rotary energy of which rot... | 10/07/2008 |
| 7380402 | Method for operating a gas turbine and gas turbine system for carrying out the method A method for operating a gas turbine uses a first fuel at full load. An improved emission behavior is achieved by operating the gas turbine (11) at partial load with a second fuel, which has a richer mix of higher-value hydrocarbons (C2+) with 2 and more carb... | 06/03/2008 |
| 7377114 | Turbine engine pulsed fuel injection utilizing stagger injector operation A method to control the output of a turbine engine pulses individual fuel injectors completely on and then completely off in selectable groups rather than in unison. The operation of the groups are staggered in time to minimize the periods of no fuel flow to the eng... | 05/27/2008 |
| 7370478 | Method of controlling a gas combustor of a gas turbine A gas combustor has a peripheral premix burner, and a central diffusion burner whose nozzle defines an eccentric first channel housing an ignition device, an axial second channel, and a third channel interposed radially between the first and second channel; the gas ... | 05/13/2008 |
| 7367194 | Pulse detonation engine system for driving turbine A pulse detonation engine system (1) for driving a turbine is comprises a detonation generator section (5) including a detonation tube (7) having a tubular hollow section for permitting detonation to be generated therein during combustion stage ... | 05/06/2008 |
| 7363756 | Method for combustion of a fuel In a method for the combustion of a fuel, a fuel or a premixed combustible mixture is introduced into a combustion space as a combustible fluid open jet. The velocity of the open jet is selected in such a way that it is impossible for a stable flame front to form, i... | 04/29/2008 |
| 7360364 | Method and apparatus for assembling gas turbine engine combustors A method enables a combustor for a gas turbine engine to be assembled. The method includes coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, wherein the outer liner is fabricated from a plurality of panels coupled toge... | 04/22/2008 |
| 7350359 | Method for utilizing gas reserves with low methane concentrations and high inert gas concentrations for fueling gas turbines The invention is directed to a method of fueling gas turbines from natural gas reserves with relatively low methane concentrations. The invention uses such reserves to generate electric power. The invention permits the use of these reserves at significantly lower co... | 04/01/2008 |
| 7350358 | Exit duct of annular reverse flow combustor and method of making the same A gas turbine engine comprising an annular reverse-flow combustor having a sheet metal combustor wall between a long exit duct portion and a small exit duct portion of the combustor. An exit duct portion of the combustor forms a sliding joint with a downstream turbi... | 04/01/2008 |
| 7350357 | Nozzle The fuel injector has a first means defining a number of flowpaths each having an inlet for receiving air and an outlet for discharging a fuel/air mixture. One or more arrays of vanes are each positioned to impart swirl to an associated one or more of the flowpaths.... | 04/01/2008 |
| 7343745 | Gas turbine combustor and operating method thereof A gas turbine combustor has a combustion chamber into which fuel and air are supplied, wherein the fuel and the air are supplied into said combustion chamber as a plurality of coaxial jets. ... | 03/18/2008 |
| 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 |
