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US20120240592 |
Combustor with Fuel Nozzle Liner Having Chevron Ribs
The present application and the resultant patent provide a fuel nozzle for mixing a flow of air and a flow of fuel within a combustor. The fuel nozzle may have one or more air passages for the... |
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US20170176015 |
SLOTTED INJECTOR FOR AXIAL FUEL STAGING
An axial fuel staging injector for a gas turbine includes a body. The body includes an upstream end and a downstream end. The body defines a primary compressed air flow path through which... |
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US20170175639 |
ENGINE FUEL SYSTEM FOR USE WITH COMPOSITE AIRCRAFT
A fuel system for a composite aircraft is described which includes an ejector pump having a vacuum inlet in communication with a fuel storage tank, an engine feed pump having an inlet in fluid... |
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US20170175625 |
SYSTEMS AND METHODS FOR AIR-BREATHING WAVE ENGINES FOR THRUST PRODUCTION
A pulse combustor system for efficiently operating a pulse combustor. The pulse combustor system includes the pulse combustor and a duct. The pulse combustor has a combustion chamber defining an... |
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US20170159576 |
GAS TURBINE FIRING TEMPERATURE CONTROL WITH AIR INJECTION SYSTEM
The present invention discloses a novel modular system and methods of operating an increased air supply to a gas turbine engine such that the upon supplying a source of external air to the system,... |
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US20170152796 |
Gas Turbine Energy Supplementing Systems and Heating Systems, and Methods of Making and Using the Same
Electrical power systems, including generating capacity of a gas turbine, where additional electrical power is generated utilizing a separately fueled system during periods of peak electrical... |
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US20170138273 |
METHOD FOR CONTROLLING THE OPERATION OF A GAS TURBINE WITH AN AVERAGED TURBINE OUTLET TEMPERATURE
A method is disclosed for operating a gas turbine having a compressor, a combustor, a turbine downstream of the combustor, and a total number of turbine outlet temperature measurements. The method... |
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US20170138271 |
FUEL SUPPLY SYSTEM FOR USE IN A GAS TURBINE ENGINE AND METHOD OF CONTROLLING AN OVERSPEED EVENT THEREIN
A fuel supply system for use in a gas turbine engine is provided. The fuel supply system includes a fuel manifold, and a shutoff valve coupled in flow communication with the fuel manifold and... |
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US20170138236 |
FUEL COMBUSTING METHOD WITH CO2 CAPTURE
A method for capturing emissions from a fuel combustion process comprising: providing a fuel to a combustor on a gas turbine, providing an oxidant to the combustor, combusting the fuel and the... |
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US20170122222 |
System and Method for Determining Fuel Splits for a Gas Turbine
A method for determining fuel splits may generally include monitoring an airflow-related parameter of a gas turbine and determining first and second reference values for the airflow-related... |
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US20170114726 |
APPARATUS AND METHOD FOR CONTROLLING AND MONITORING AN ELECTRO-HYDRAULIC SERVOVALVE
A method for actively calculating a capability of an electronically controlled valve is provided. The method including the steps of: a) operating the electronically controlled valve in accordance... |
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US20170107908 |
Controlling Injection of Bio-Diesel into a Gas Turbine Combustor
Certain embodiments may include systems and methods that comprise for injecting biofuel into a gas turbine system. The systems and methods comprise of storing a biofuel in a storage tank,... |
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US20170102147 |
FUEL-AIR PREMIXER FOR A GAS TURBINE
The present disclosure relates to a fuel-air premixer for a turbine system. The fuel-air premixer includes a swirler and a centerbody. The swirler is configured to direct a flow of air through the... |
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US20170089583 |
AXIALLY STAGED MICROMIXER CAP
A method of providing fuel to a combustion chamber of a combustion can in a radial direction of the combustion can, and a micromixer cap having axially arranged fuel stages that receive fuel from... |
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US20170089577 |
METHOD AND SYSTEM FOR IGNITER HEALTH MONITORING IN A GAS TURBINE ENGINE
Techniques for monitoring health of an igniter (202) in a gas turbine engine (201) include a sensor (270) mounted to detect signals in a combustor (260) and a processor (180) in electrical... |
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US20170089268 |
GAS TURBINE COMBUSTION CONTROL DEVICE AND COMBUSTION CONTROL METHOD AND PROGRAM THEREFOR
A combustion control device is installed in a gas turbine including a compressor, a combustor, a turbine, a turbine bypass pipe through which compressed air from a casing is discharged to a... |
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US20170089266 |
METHOD AND DEVICE TO CONTROL A FUEL SPLIT IN A COMBUSTION DEVICE
A method, control unit and rotating machine for determining a fuel split setting value for adjusting a fuel split setting for a combustion device, the fuel split setting defining a relation... |
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US20170089265 |
LIQUEFIED PETROLEUM GAS FUEL CONDITIONING SYSTEM FOR GAS TURBINE ENGINES
The present application provides a fuel conditioning system for conditioning a flow of a liquefied fuel for use with a gas turbine engine. The fuel conditioning system may include a fuel skid... |
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US20170074520 |
COMBUSTOR
A fuel burner includes a tube extending from a first end to a second end and having an outer surface and an inner surface defining a central passage. The central passage is supplied at the first... |
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US20170074518 |
PREFILMING FUEL/AIR MIXER
A turbine combustor assembly includes a fuel/air mixer assembly having a plurality of fuel/air mixer elements and a fuel injector coupled to the fuel/air mixer assembly. Each of the fuel/air mixer... |
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US20170074516 |
VALVE FOR A FUEL INJECTOR
A fuel injector for injecting fuel in a burner of a gas turbine where the fuel injector has a body with an inner hole and a valve element which is slideably arranged inside the inner hole. The... |
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US20170074175 |
GAS TURBINE COMBUSTION CONTROL DEVICE AND COMBUSTION CONTROL METHOD AND PROGRAM THEREFOR
A combustion control device (50) is installed in a gas turbine including a compressor (2), combustors (3), a turbine (4), a bleed air pipe (12) through which bleed air is returned to an inlet of... |
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US20170074174 |
METHOD FOR STARTING A GAS TURBINE
A method of starting a gas turbine is provided, comprising the step of providing an apparatus for regulating the flow of fuel in a gas turbine, the apparatus comprising a main line connecting a... |
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US20170059164 |
GAS TURBINE WITH A SEQUENTIAL COMBUSTION ARRAGEMENT AND FUEL COMPOSITION CONTROL
The present disclosure refers to a method for operating a gas turbine with a sequential combustor arrangement having: a first burner, a first combustion chamber, and a second combustor. A fuel gas... |
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US20170051682 |
SYSTEM AND METHOD FOR ABATEMENT OF DYNAMIC PROPERTY CHANGES WITH PROACTIVE DIAGNOSTICS AND CONDITIONING
A system includes a fluid transfer system that has instrumentation configured to measure fuel properties; a fluidic buffer volume device located downstream of a fuel sensing point, wherein the... |
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US20170045230 |
COMBUSTION CYCLE PROCESS
An aspect of the present disclosure is a process for generating work, in particular via a combustion cycle. The process comprises the steps of compressing an oxidator, e.g. air. The process... |
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US20170045228 |
SEQUENTIAL COMBUSTION ARRANGEMENT WITH COOLING GAS FOR DILUTION
A gas turbine with a sequential combustor arrangement as disclosed includes a first combustor with a first burner for admitting a first fuel into a combustor inlet gas during operation and a first... |
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US20170044995 |
METHOD FOR SELECTING OPERATING POINTS OF A GAS TURBINE
A method for selecting operating points of a gas turbine while taking into consideration at least one controlled variable, the operating points being defined at least by parameter combinations of... |
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US20170044994 |
FUEL CONTROL METHOD FOR GAS TURBINE, CONTROL DEVICE FOR EXECUTING SAID METHOD, AND GAS TURBINE INSTALLATION PROVIDED WITH SAID CONTROL DEVICE
A control device includes a fuel equivalent value calculation unit for determining the flow rate of fuel supplied to a gas turbine in accordance with a target value deviation between an actual... |
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US20170023251 |
COMBUSTION CHAMBER COMPRISING ADDITIONAL INJECTION DEVICES OPENING UP DIRECTLY INTO CORNER RECIRCULATION ZONES, TURBOMACHINE COMPRISING SUCH A CHAMBER AND FUEL SUPPLY METHOD FOR SUCH A CHAMBER
A combustion chamber (18) for aircraft turbomachine, comprising an annular chamber end wall (40), an annular row of injection systems (42) mounted in the annular chamber end wall (40), each... |
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US20170002742 |
FUEL INJECTION LOCATIONS BASED ON COMBUSTOR FLOW PATH
Systems and methods for dual-fuel operation of a gas turbine combustor are provided. An exemplary gas turbine combustor may comprise one or more components, such as a cylindrical combustion liner,... |
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US20160363049 |
Vaporization Systems and Methods of Using the Same
Embodiments of the invention relate to vaporizer systems including two-phase heat transfer devices for vaporizing liquids and methods of using the same. |
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US20160356501 |
METHOD AND APPARATUS FOR ASSISTING WITH THE COMBUSTION OF FUEL
An apparatus and method for assisting with the combustion of fuel are described. The apparatus includes a swirler assembly and a fuel nozzle. Fuel is directed into a fuel nozzle mixing chamber and... |
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US20160320061 |
ONLINE ESTIMATION OF SPECIFIC GRAVITY OF GAS FUEL
A method for determining an estimate of the specific gravity of a fuel for a gas turbine engine is disclosed. The gas turbine engine includes a fuel control valve and one or more fuel injectors.... |
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US20160312706 |
METHOD FOR DETECTING A FAILURE IN A MOTIVE FLOW VALVE OF AN AIRCRAFT ENGINE FUEL CIRCUIT
A method detects a failure in a fuel return valve of an aircraft engine fuel circuit. A fuel system is connected to a fuel tank of the circuit and includes a high-pressure pump delivering a flow... |
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US20160305664 |
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... |
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US20160305344 |
APPLICATION OF PROBABILISTIC CONTROL IN GAS TURBINE TUNING FOR FUEL FLOW-EXHAUST ENERGY PARAMETERS, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS
Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a... |
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US20160305343 |
APPLICATION OF PROBABILISTIC CONTROL IN GAS TURBINE TUNING FOR EMISSIONS-FUEL FLOW PARAMETERS, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS
Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a... |
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US20160305342 |
APPLICATION OF PROBABILISTIC CONTROL IN GAS TURBINE TUNING FOR FUEL FLOW-POWER OUTPUT PARAMETERS, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS
Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a... |
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US20160305340 |
APPLICATION OF PROBABILISTIC CONTROL IN GAS TURBINE TUNING FOR EXHAUST ENERGY-FUEL FLOW PARAMETERS, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS
Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a... |
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US20160305339 |
APPLICATION OF PROBABILISTIC CONTROL IN GAS TURBINE TUNING FOR FUEL FLOW-EMISSIONS PARAMETERS, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS
Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a... |
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US20160305329 |
APPARATUS FOR DISCRIMINATING IGNITION IN A GAS-TURBINE AEROENGINE
An apparatus for discriminating ignition in a gas-turbine aeroengine is configured to discriminate that ignition occurred in a combustion chamber upon discriminating that a calculated... |
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US20160298851 |
INTELLIGENT CONTROL METHOD WITH PREDICTIVE EMISSIONS MONITORING ABILITY
A combustor system for a gas turbine engine includes a combustion chamber into which a pilot fuel and a main fuel is injectable and flammable, wherein an exhaust gas generated by the burned pilot... |
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US20160290650 |
MICROMIXER SYSTEM FOR A TURBINE SYSTEM AND AN ASSOCIATED METHOD THEREOF
A micromixer system includes a casing having a first side wall and a second side wall. Further, the micromixer system includes a plurality of pipes spaced apart from each other and disposed within... |
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US20160281993 |
INTEGRATED DUAL FUEL DELIVERY SYSTEM
The present invention relates to dual fuel delivery system for a gas turbine. A dual fuel delivery system for a gas turbine includes: a main fuel line having a main fuel oil conduit and a main... |
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US20160281990 |
FUEL NOZZLE FOR AXIALLY STAGED FUEL INJECTION
The present invention discloses a fuel nozzle assembly and method for axially staging fuel injection. The fuel nozzle assembly comprises a plurality of vanes connected to a core, with an annular... |
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US20160281656 |
FUEL SYSTEM FOR A GAS TURBINE ENGINE
A fuel system for a gas turbine engine having a combustor that is fed fuel from a fuel tank includes a main fuel line providing fuel flow from the fuel tank to the combustor, at least one pump... |
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US20160281606 |
INTEGRATED DUAL FUEL DELIVERY SYSTEM
The present invention relates to dual fuel delivery system for a gas turbine. A dual fuel delivery system for a gas turbine includes a main fuel line having a main fuel oil conduit and a main fuel... |
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US20160273456 |
GAS TURBINE SYSTEM AND METHOD
A fuel supply system includes a first fuel gas compressor coupled to a fuel gas compressor shaft and configured to pressurize a fuel for a gas turbine system. A clutch is coupled to the fuel gas... |
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US20160265444 |
RETURN FLOW POWERED TURBINE
A fuel system for an aircraft is provided having an improved fluid circuit and method of operation. Un-burnt fuel is directed via a return loop towards a fuel tank reservoir. A turbine is located... |