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US20110302927 FUEL CONTROL METHOD FOR STARTING A GAS TURBINE ENGINE  
A method for controlling a flow of fuel to a starting gas turbine engine includes controlling the flow of fuel to the engine by controlling fuel pressure to the engine, and modulating the flow of...
US20140216048 Variable Volume Combustor  
The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned...
US20070107437 Low emission combustion and method of operation  
A combustor is provided. The combustor includes a combustor liner and a swirl premixer disposed on a head end of the combustor liner and configured to provide a fuel-air mixture to the combustor....
US20150075174 Combustor and Method of Fuel Supply and Converting Fuel Nozzle for Advanced Humid Air Turbine  
A fuel control device and method of a gas turbine combustor, for advanced humid air turbines, in which plural combustion units comprising plural fuel nozzles for supplying fuel and plural air...
US20120031103 Combustor and the Method of Fuel Supply and Converting Fuel Nozzle for Advanced Humid Air Turbine  
A fuel control device and method of a gas turbine combustor, for advanced humid air turbines, in which plural combustion units comprising plural fuel nozzles for supplying fuel and plural air...
US20150101342 ENGINE  
The present disclosure relates to an engine having two modes of operation—air breathing and rocket—that may be used in aerospace applications such as in an aircraft, flying machine, or aerospace...
US20120227412 METHOD OF OPERATING A MULTI-FUEL COMBUSTION SYSTEM  
A method of operating a multi-fuel combustion system is provided. The method includes a first phase and a second phase, wherein the first phase includes providing ignition to a combustor basket to...
US20140216050 Variable Volume Combustor with Nested Fuel Manifold System  
The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles, a fuel manifold system in communication with the...
US20140109587 SYSTEM AND METHOD FOR REDUCING MODAL COUPLING OF COMBUSTION DYNAMICS  
A system and method for reducing combustion dynamics includes first and second combustors, and each combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. Each...
US20140123654 FUEL METERING VALVE SYSTEM  
A fuel metering valve system for use with a flow of fuel in a gas turbine engine may include a number of orifice plate lines, a number of differently sized orifice plates, and a number of orifice...
US20100011771 COANDA INJECTION SYSTEM FOR AXIALLY STAGED LOW EMISSION COMBUSTORS  
The low emission combustor includes a combustor housing defining a combustion chamber having a plurality of combustion zones. A liner sleeve is disposed in the combustion housing with a gap formed...
US20110154829 BURNER, COMBUSTOR AND REMODELING METHOD FOR BURNER  
A combustor with a burner maintains combustion stability. The burner includes an air hole member 31 with a plurality of air holes 34, 35 provided at an upstream side of the combustion gases...
US20130318992 Combustor with a Brief Severe Quench Zone  
The present application provides a combustor for combusting a number of flows of air and a number of flows of fuel. The combustor may include a central swirler for producing a high swirl quench...
US20150176842 METHOD FOR OPERATING A COMBUSTOR FOR A GAS TURBINE AND COMBUSTOR FOR A GAS TURBINE  
The invention provides a new path of combustion technology for gas turbine operation with multifuel capability, low emissions of NO and CO and high thermal efficiency. Further to the present...
US20120232768 SYSTEM AND METHOD FOR TRANSITIONING BETWEEN FUEL SUPPLIES FOR A COMBUSTION SYSTEM  
A system includes a turbine fuel controller. The turbine fuel controller includes a purge control logic configured to control a purge sequence of mixing a purge gas with a first fuel during a...
US20110041510 FUEL CONTROL APPARATUS FOR GAS TURBINE ENGINE  
In an apparatus for controlling a flow rate of fuel to be supplied to a combustion chamber of a gas turbine engine having a turbine rotated by combustion gas injected from the combustion chamber...
US20120227413 IGNITER  
An igniter arranged to ignite combustion in a primary flow including a fuel and air mixture, the igniter including one or more geometric features arranged to: induce a shockwave flow structure at...
US20060156734 Gas turbine combustor  
A combustor (18) for a gas turbine engine (10) includes a combustor burner (34) receiving an oxidizer flow (36). The combustor burner includes an annular vortex generator (38) disposed around a...
US20070119179 Opposed flow combustor  
In accordance with one embodiment of the present invention a combustor is provided. The combustor includes a combustion chamber having a first inlet adapted to provide a first air flow to the...
US20140090394 FLOW MODIFIER FOR COMBUSTOR FUEL NOZZLE TIP  
A fuel injector nozzle assembly includes a body extending along an axis and a core swirl plug positioned at least partially within the body. The core swirl plug has a flow modifying structure...
US20120036862 SYSTEM AND METHOD FOR OPERATING A GAS TURBINE  
A system for operating a gas turbine includes a compressor, a combustor, and a turbine. The combustor and turbine define a hot gas path. A sensor disposed outside the hot gas path measures...
US20130232986 COMBUSTOR AND METHOD FOR REDUCING THERMAL STRESSES IN A COMBUSTOR  
A combustor includes a combustion chamber and a casing that circumferentially surrounds the combustion chamber to at least partially define an annular passage between the casing and the combustion...
US20140260296 SLINGER COMBUSTOR  
A slinger combustor has an annular combustor shell defining a combustion chamber having a radially inner fuel inlet for receiving a spray of fuel centrifuged by a fuel slinger. The combustion...
US20120023964 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...
US20140338359 COMBUSTOR AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR  
A combustor (10) includes a cap (16), a liner (20), a transition piece (24), and a combustion chamber (22) located downstream from the cap (16) and defined by the cap and liner. A secondary nozzle...
US20130255271 Fuel Supply System  
A fuel supply system is provided having a first fuel gas compressor configured to be driven by a motor and a second fuel gas compressor configured to be driven by a shaft of a gas turbine system....
US20140109588 BURNER FOR A CAN COMBUSTOR  
The present invention relation to a burner for a combustion chamber of a gas turbine with a mixing and injection device. The mixing and injection device includes a limiting wall that defines a...
US20060272332 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...
US20140216051 Variable Volume Combustor with an Air Bypass System  
The present application provides a combustor for use with flow of fuel and a flow of air in a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within a...
US20120255310 COMBUSTOR NOZZLE AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR  
A combustor nozzle includes a center body and a shroud circumferentially surrounding at least a portion of the center body to define a passage between the center body and the shroud. A guide...
US20060248898 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...
US20140157788 FUEL NOZZLE FOR GAS TURBINE  
A gas turbine system includes a fuel nozzle. The fuel nozzle has a first wall extending along an axis and defines a first fluid passage. A second wall surrounds the first wall and defines a second...
US20140260302 DIFFUSION COMBUSTOR FUEL NOZZLE FOR LIMITING NOx EMISSIONS  
The present application and the resultant patent provide a diffusion combustor fuel nozzle for a gas turbine engine. The fuel nozzle may include one or more gas fuel passages for one or more flows...
US20130008172 Systems and Methods for Modified Wobbe Index Control With Constant Fuel Temperature  
The present application provides a gas turbine engine system for combusting a flow of fuel. The gas turbine engine system may include a combustor and a fuel system for providing the flow of fuel...
US20120125007 METHOD AND SYSTEM FOR ENGINE IGNITION AND MONITORING  
A method and system of engine ignition and monitoring is provided. A combustor includes a casing surrounding a combustion zone and an ignitor plug including a tip, a base, and a body extending...
US20120036861 METHOD FOR COMPENSATING FOR COMBUSTION EFFICIENCY IN FUEL CONTROL SYSTEM  
Compensation is provided for a fuel demand signal of a gas turbine controller during transition between operating modes. The compensation adjusts fuel demand to account for combustion efficiency...
US20150184594 SYSTEMS AND METHODS TO MAINTAIN STABILITY OF FUEL FLOW IN GAS TURBINE ENGINES  
A system includes a gas turbine comprising a compressor section, combustor section, and a turbine section. The system further includes a first fuel line and a second fuel line coupled to the gas...
US20130192244 HYBRID APU START FUEL SYSTEM  
A fuel system for an auxiliary power unit includes a mechanical fuel pump, an electric fuel pump, and a controller. The mechanical fuel pump provides fuel flow to the auxiliary power unit and has...
US20070151255 Combustion turbine engine and methods of assembly  
A method of assembling a combustion turbine engine in provided. The method includes coupling at least one fuel nozzle inner atomized air tube to a combustor end cover plate body. The method also...
US20070289311 Combustion apparatus using pilot fuel selected for reduced emissions  
A combustion apparatus (10) incorporating a dry low NOx (DLN) combustor (20) that uses two different fuels (30, 40) simultaneously. One fuel (30) is premixed with air (22) for a primary combustion...
US20120055167 APPARATUS AND METHOD FOR MIXING FUEL IN A GAS TURBINE NOZZLE  
A nozzle includes a fuel plenum and an air plenum downstream of the fuel plenum. A primary fuel channel includes an inlet in fluid communication with the fuel plenum and a primary air port in...
US20110000219 METHOD AND APPARATUS FOR ACTIVELY CONTROLLING FUEL FLOW TO A MIXER ASSEMBLY OF A GAS TURBINE ENGINE COMBUSTOR  
An apparatus for actively controlling fuel flow from a fuel pump to a mixer assembly of a gas turbine engine combustor, where the mixer assembly includes a pilot mixer and a main mixer. The pilot...
US20140298817 ARRANGEMENT FOR PREPARATION OF LIQUID FUEL FOR COMBUSTION AND A METHOD OF PREPARING LIQUID FUEL FOR COMBUSTION  
A preparation of liquid fuel for combustion, particularly for ignition, in the burners of a gas turbine is proposed. A source of heated liquid fuel, particularly heated pressurized fuel, is...
US20080078183 Liquid fuel enhancement for natural gas swirl stabilized nozzle and method  
Conventional swozzle-type burners are modified so as to be capable of selectively running on liquid fuel without requiring water injection for NOx abatement or dedicated air supply for atomizing...
US20070180832 Compact, low pressure-drop shock-driven combustor  
A system for efficiently creating cyclic detonations is provided. The system includes at least a first initiator chamber configured to generate an initial wave, at least one main chamber coupled...
US20070107436 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...
US20120073305 COMBUSTION CHAMBER AND METHOD FOR OPERATING A COMBUSTION CHAMBER  
A combustion chamber of a gas turbine including first and second premixed fuel supply devices connected to a combustion device having first zones connected to the first premixed fuel supply...
US20140338356 System Having a Multi-Tube Fuel Nozzle with an Aft Plate Assembly  
A system including a first multi-tube fuel nozzle including a plurality of first tubes extending in an axial direction, wherein each first tube of the plurality of first tubes includes a first air...
US20130186057 NAPHTHA AND PROCESS GAS/SYNGAS MIXTURE FIRING METHOD FOR GAS TURBINE ENGINES  
A fuel delivery system for a gas turbine designed to efficiently transfer from one type of fuel to a separate fuel, comprising different and cooperating fuel modules, namely high hydrogen fuel...
US20120204571 COMBUSTOR AND METHOD FOR INTRODUCING A SECONDARY FLUID INTO A FUEL NOZZLE  
A combustor is disclosed that includes a baffle plate and a fuel nozzle extending through the baffle plate. The combustor may also include a shroud extending from the baffle plate and surrounding...
Matches 151 - 200 out of 426 < 1 2 3 4 5 6 7 8 9 >