Matches 101 - 150 out of 426 < 1 2 3 4 5 6 7 8 9 >


Match Document Document Title
US20140283524 NOZZLE SYSTEM AND METHOD FOR STARTING AND OPERATING GAS TURBINES ON LOWBTU FUELS  
A fuel nozzle system for enabling a gas turbine to start and operate on low-Btu fuel includes a primary tip having primary fuel orifices and a primary fuel passage in fluid communication with the...
US20120210727 METHOD FOR COMBUSTING HYDROGEN-RICH, GASEOUS FUELS IN A BURNER, AND BURNER FOR PERFORMING SAID METHOD  
A method for the combustion of hydrogen-rich, gaseous fuels in combustion air in a burner of a gas turbine includes injecting the hydrogen-rich, gaseous fuel at least partially isokinetically with...
US20120031102 TURBINE COMBUSTOR WITH FUEL NOZZLES HAVING INNER AND OUTER FUEL CIRCUITS  
A combustor cap assembly for a turbine engine includes a combustor cap and a plurality of fuel nozzles mounted on the combustor cap. One or more of the fuel nozzles would include two separate fuel...
US20150192074 FUEL FLOW SPLITTER AND GAS TURBINE FUEL SYSTEM HEALTH MONITORING  
A gas turbine health monitoring fuel system including a fuel splitter, a first and second fuel nozzle, a first and second fuel pump, and a common drive coupled to the first and second fuel pumps....
US20150253011 ANNULAR PREMIXED PILOT IN FUEL NOZZLE  
A combustor for a gas turbine engine has a head end portion that carries at least one fuel/air nozzle. Each fuel/air nozzle includes a premixed pilot nozzle having premix conduits where each...
US20140007585 LIQUID FUEL ASSIST IGNITION SYSTEM OF A GAS TURBINE AND METHOD TO PROVIDE A FUEL/AIR MIXTURE TO A GAS TURBINE  
A liquid fuel assist ignition system for providing a fuel/air mixture to a gas turbine in its start-up phase includes a high pressure tank, a vacuum pump connected to the high pressure tank, a...
US20140083110 SEAL FOR FUEL DISTRIBUTION PLATE  
A fuel flow passes through a micromixer section of a gas turbine that includes a plurality of mixing tubes for transporting a fuel/air mixture and a distribution plate including a plurality of...
US20130305734 Fuel Plenum Premixing Tube with Surface Treatment  
The present application provides a micro-mixer fuel plenum for mixing a flow of fuel and a flow of air in a combustor. The micro-mixing fuel plenum may include an outer barrel and a number of...
US20140157787 FUEL NOZZLE FOR GAS TURBINE  
A gas turbine system includes a fuel nozzle. The fuel nozzle includes a first fluid conduit defining an oxidant passage, a second fluid conduit defining a first fuel passage, and a third fluid...
US20140174096 METHOD AND ARRANGEMENT FOR INJECTING AN EMULSION INTO A FLAME  
An arrangement for injection of an emulsion of a first fluid and a second fluid into a flame of a burner has a central gas duct, an outer gas channel disposed coaxially with the gas duct, and a...
US20140345291 Toroidal Combustion Chamber  
A device comprising a combustion toroid for receiving combustion-induced centrifugal forces therein to continuously combust fluids located therein and an outlet for exhaust from said combustion...
US20140196467 OXIDIZING FUEL  
A mixture of air and fuel is received into a reaction chamber of a gas turbine system. The fuel is oxidized in the reaction chamber, and a maximum temperature of the mixture in the reaction...
US20140123650 MICRO-MIXER NOZZLE  
The present application provides a micro-mixer combustion nozzle for mixing a flow of fuel and a flow of air in a gas turbine engine. The micro-mixer combustion nozzle may include a fuel plate...
US20070021899 Method and system for operating a multi-stage combustor  
A method for operating a multi-stage combustor of a gas turbine engine comprises: (a) determining a combustor air entry temperature; (b) determining the combustor air entry flow rate; and (c)...
US20150082801 GAS TURBINE AND METHOD TO OPERATE THE GAS TURBINE  
It is proposed a gas turbine and a method to operate the gas turbine. A fluid is supplied to the gas turbine by means of fluid paths. A first fluid path is divided into a second and third fluid...
US20140083078 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...
US20080006033 Gas turbine engine combustion systems  
One embodiment is a unique gas turbine engine combustion chamber including primary and secondary burning zones. Other embodiments include unique gas turbine engine apparatuses, systems, methods,...
US20130298569 GAS TURBINE AND METHOD FOR OPERATING SAID GAS TURBINE  
The present disclosure relates to gas turbine including a combustion system with several burners, a conduit system with a fuel manifold for providing the burners with liquid fuel and a system for...
US20070180833 Methods and apparatus for controlling air flow within a pulse detonation engine  
A flow control device for use with a pulse detonation chamber including an inlet coupled in flow communication with a source of compressed air. The inlet extends at least partially into the...
US20120271527 DISTRIBUTED AIRCRAFT ENGINE FUEL SYSTEM  
A gas turbine engine includes a plurality of fuel injectors grouped operatively by stages in a multistage combustor. A fuel system for the gas turbine engine includes at least one fuel metering...
US20150204244 SELECTIVELY DEOXYGENATED STORED FUEL SYSTEM  
A gas turbine engine includes a multi-stage fuel injection system including at least a first fuel injection stage and a second fuel injection stage, a first fuel reservoir fluidly connected to the...
US20140033719 MULTI-STEP COMBUSTOR  
The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles and a combustion zone downstream of the fuel nozzles. The...
US20140090396 COMBUSTOR WITH RADIALLY STAGED PREMIXED PILOT FOR IMPROVED  
The present invention discloses a novel apparatus and method for a mixing fuel and air in a gas turbine combustion system. The mixer helps to mix fuel and air while being able to selectively...
US20080115501 TRIPLE ANNULAR COUNTER ROTATING SWIRLER  
A fuel-air mixer includes an annular shroud, inner and outer counter-rotating swirlers, a hub separating the inner and outer swirlers, a center body extending axially along the annular shroud, a...
US20130199200 FUEL DISTRIBUTION WITHIN A GAS TURBINE ENGINE COMBUSTOR  
A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to...
US20150219337 SYSTEM AND METHOD FOR REDUCING MODAL COUPLING OF COMBUSTION DYNAMICS  
A system and method for reducing modal coupling of combustion dynamics generally include multiple combustors, and each combustor includes multiple fuel nozzle groups for mixing fuel with a...
US20140190175 3D NON-AXISYMMETRIC COMBUSTOR LINER  
A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The...
US20100287946 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...
US20140318145 HYBRID SLINGER COMBUSTION SYSTEM  
There is provided a method for improving the combustion efficiency of a combustor of a gas turbine engine powering an aircraft. The method comprises selectively using two distinct fuel injection...
US20100213285 NOZZLE DESIGN TO REDUCE FRETTING  
A method of designing a fuel nozzle of a gas turbine engine to reduce fretting thereof during use, including establishing an initial nozzle design, determining a first natural frequency of that...
US20150089954 BURNERS HAVING FUEL PLENUMS  
Burners having a fuel plenum in a base are disclosed. One disclosed example apparatus includes a base of a burner, the base comprising a fuel plenum and coupled to fuel nozzles, where at least one...
US20140190177 METHOD FOR RUNNING UP A STATIONARY GAS TURBINE  
A method for running up a stationary gas turbine is provided. The turbine has a combustion chamber, the burners of which have a pilot burner and a main burner and by which various types of fuel...
US20120260666 MULTI-FUEL COMBUSTION SYSTEM  
A multi-fuel combustion system is provided. The system includes a combustor basket adapted to combust at least two type of fuels. The combustor basket includes a circumferential wall with a...
US20120167583 Method for Starting a Burner  
A method for starting a burner for combusting synthesis gases is provided. The burner includes first and second fuel passages, the first fuel passage encompasses the second fuel passage in a...
US20150135723 COMBUSTOR NOZZLE AND METHOD OF SUPPLYING FUEL TO A COMBUSTOR  
A combustor nozzle includes a fuel passage that extends generally axially in the nozzle and a surface that extends radially across at least a portion of the fuel passage. A projection in the...
US20130174570 ENGINE SYSTEMS WITH ENHANCED START CONTROL SCHEDULES  
An engine system for starting a gas turbine engine includes a starter coupled to the gas turbine engine and configured to provide torque to the gas turbine engine; and a controller coupled to the...
US20130074514 SYSTEMS AND METHODS INVOLVING IMPROVED FUEL ATOMIZATION IN AIR BLAST FUEL NOZZLES OF GAS TURBINE ENGINES  
Systems and methods involving improved fuel atomization in air-blast fuel nozzles of gas turbine engines are provided. In this regard, a representative method includes: providing fuel to a chamber...
US20140245745 FUEL SYSTEM OF GAS TURBINE ENGINES  
A method for purging fuel from a fuel system of a gas turbine engine on shutdown of the engine comprises, in one aspect, terminating a fuel supply to the fuel system and using the residual...
US20080072605 Method for control of thermoacoustic instabilities in a combustor  
A method for controlling a temperature distribution within a combustor having a plurality of chamber sections comprising controlling a fuel-to-air ratio in the chamber sections. At least two...
US20140260303 METHODS RELATING TO DOWNSTREAM FUEL AND AIR INJECTION IN GAS TURBINES  
A method for use in a gas turbine engine. The method includes the steps of: configuring a downstream injection system within the interior flowpath that includes two injection stages, a first stage...
US20150128607 Multi-Swirler Fuel/Air Mixer with Centralized Fuel Injection  
A gas turbine combustor assembly has a fuel/air mixer assembly with a plurality of fuel/air mixer elements. Each fuel/air mixer element defines an air flow passage therethrough. A fuel injector is...
US20140144153 SYSTEM AND METHOD TO CONTROL A GAS TURBINE SUBJECT TO FUEL COMPOSITION VARIATION  
A system and method control a gas turbine subject to fuel composition variation. The method includes operating a first effector to control the gas turbine based on fuel composition. The method...
US20130174568 COMBUSTOR AND METHOD FOR DISTRIBUTING FUEL IN THE COMBUSTOR  
A combustor includes a tube bundle that extends radially across at least a portion of the combustor. The tube bundle includes an upstream surface axially separated from a downstream surface. A...
US20130298561 MULTI-TUBE FUEL NOZZLE WITH MIXING FEATURES  
A system includes a multi-tube fuel nozzle having an inlet plate and a plurality of tubes adjacent the inlet plate. The inlet plate includes a plurality of apertures, and each aperture includes an...
US20070137212 Combustor nozzle  
A gas turbine engine swirler/nozzle apparatus has a swirler having a central axis and a nozzle. The nozzle has an outlet end with a plurality of outlets about said axis and having an asymmetry...
US20150219335 SYSTEM AND METHOD FOR REDUCING MODAL COUPLING OF COMBUSTION DYNAMICS  
A system and method for reducing modal coupling of combustion dynamics among multiple combustors are provided. Each combustor may include one or more fuel nozzles axially aligned with a combustion...
US20110289933 Hybrid Prefilming Airblast, Prevaporizing, Lean-Premixing Dual-Fuel Nozzle for a Gas Turbine Combustor  
A dual fuel nozzle for a gas turbine combustor includes a hub defining a fuel inlet and a plurality of liquid fuel jets disposed at a downstream end of the hub. The fuel jets are oriented to eject...
US20130180260 COMBUSTOR RECOVERY METHOD AND SYSTEM  
A method is disclosed for controlling gas turbine operation in response to lean blowout of a combustion can. The gas turbine comprises a pair of combustion cans. The method includes sensing that a...
US20140338357 CAVITY SWIRL FUEL INJECTOR FOR AN AUGMENTOR SECTION OF A GAS TURBINE ENGINE  
A fuel injection system for a gas turbine engine includes a fuel nozzle with a fuel injection aperture to inject a fuel jet and a multiple of airflow passages in the fuel nozzle to communicate a...
US20140352322 ANNULAR STRIP MICRO-MIXERS FOR TURBOMACHINE COMBUSTOR  
A turbomachine combustor is provided. The turbomachine includes a combustion chamber and multiple micro-mixer nozzles arranged concentrically within a radial combustion liner and configured to...

Matches 101 - 150 out of 426 < 1 2 3 4 5 6 7 8 9 >