Matches 351 - 400 out of 426 < 1 2 3 4 5 6 7 8 9 >


Match Document Document Title
US20160258629 FUEL STAGING IN A GAS TURBINE ENGINE  
A gas turbine system includes a turbine combustor. The turbine combustor includes one or more first fuel injectors coupled to a head end of the turbine combustor and configured to deliver a first...
US20160252019 METHOD AND SYSTEM TO INCREASE GAS TURBINE ENGINE DURABILITY  
A method of operating a gas turbine engine includes measuring an exhaust gas temperature of the gas turbine engine. A first stage turbine nozzle assembly of the gas turbine engine is adjusted to a...
US20160237892 STORING ENERGY USING A THERMAL STORAGE UNIT AND AN AIR TURBINE  
The invention relates to a method for storing energy by converting the energy into thermal energy and then generating power by means of a gas turbine set with a compressor (1), an expander (6) and...
US20160230668 FUEL INJECTION DEVICE FOR A GAS TURBINE  
A fuel injection device for a gas turbine, including a plurality of streamlined bodies arranged in a ring adjacent to one another in a circumferential direction relative to a central axis of the...
US20160230667 ACCUMULATOR ASSISTED GAS TURBINE ENGINE START SYSTEM AND METHODS THEREFOR  
A gas turbine engine assembly is provided having a gas turbine engine and a fuel supply in flow communication with the gas turbine engine. An accumulator is positioned in flow communication...
US20160215703 CONTROL SYSTEM FOR CAN-TO-CAN VARIATION IN COMBUSTOR SYSTEM AND RELATED METHOD  
A control system for a combustor system including a plurality of can combustors, each can combustor accommodating combustion of a plurality of combustion fluids in a combustion chamber thereof is...
US20160209038 DUAL FUEL NOZZLE WITH SWIRLING AXIAL GAS INJECTION FOR A GAS TURBINE ENGINE  
A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, the outer air swirler defines an outer annular air passage. An inner air swirler along the axis...
US20160209037 Dual Fuel Nozzle With Liquid Filming Atomization for a Gas Turbine Engine  
A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner...
US20160208716 METHOD FOR DETECTING A FAULT, FAULT DETECTION SYSTEM AND GAS TURBINE ENGINE  
A method for detecting a fault in a gas supply system for a gas turbine engine. The method comprises: measuring a pressure difference between two gas supplying ducts of the gas supply system;...
US20160201919 METHOD AND SYSTEM FOR INJECTING FUEL INTO AN ENGINE COMBUSTION CHAMBER  
A system of injecting fuel into the combustion chamber of an engine, including at least two fuel circuits, one permanent flow circuit and one intermittent flow circuit, fuel proportioning and...
US20160201563 FUEL MANAGEMENT SYSTEM FOR A TURBINE ENGINE  
A system is provided for a turbine engine that includes a fuel injector and an actuator. The system includes a fuel management system configured to receive fuel from a flow path. The fuel...
US20160195025 GAS TURBINE FLAMEOUT DETECTION  
A method includes receiving an indication of exhaust gas temperature (EGT) for a gas turbine engine, and determining, by at least one processor, based on the received indication of the EGT, a...
US20160195024 FUEL SYSTEM FOR TONE CONTROL AND OPERABILITY  
Aspects of the disclosure are directed to controlling a distribution of fuel to a plurality of nozzles associated with at least one aircraft engine by: determining a state of operation associated...
US20160195020 MULTIPOINT FUEL INJECTION SYSTEM FOR A TURBOMACHINE AND ASSOCIATED REGULATION METHOD  
The invention concerns a fuel system (1) for a turbomachine comprising: —a control circuit (9a), —a main circuit (9b), —a flow rate regulator (2), suitable for regulating the flow of fuel in the...
US20160178207 AXIALLY STAGED MIXER WITH DILUTION AIR INJECTION  
A method is disclosed for operating an axially staged mixer arrangement with dilution air or dilution gas injection in connection with a combustion arrangement of a gas turbine engine or turbo...
US20160177835 GAS TURBINE ENGINE WITH ANGULARLY OFFSET TURBINE VANES  
A gas turbine engine includes a combustor having a plurality of fuel nozzles arranged circumferentially equidistant from one another about a first center. The plurality of fuel nozzles produce a...
US20160169120 Fuel Schedule for Robust Gas Turbine Engine Transition Between Steady States  
A fuel injection system for a gas turbine engine can be used to ensure successful transition in all conditions, while avoiding the possibility of steady state, or increasing power mode, operations...
US20160169115 TURBINE ENGINE CONTROL SYSTEM  
A method of operating a turbine engine, the turbine engine having an inlet, a shaft, a turbine, a control system, a fuel system and a modular liquid fuel burner system having at least two...
US20160169111 PIVOTING STOWABLE SPRAYBAR  
An exemplary fuel spray bar system can include a conduit, which is pivotally attached to an engine frame and configured to deliver fuel from a fuel line to an engine flow path. The system further...
US20160169110 PREMIXING NOZZLE WITH INTEGRAL LIQUID EVAPORATOR  
The present application provides a fuel nozzle for a gas turbine engine using a primary fuel and a secondary fuel. The fuel nozzle may include a number of primary fuel injection ports for the...
US20160153364 GAS TURBINE FUEL CONTROL SYSTEM  
A method of controlling a flow of a fuel mixture of different types of fuel in a gas turbine engine is described which includes determining a combustive energy value of an input of the fuel...
US20160146467 COMBUSTOR LINER  
The present invention relates to a combustor liner for a gas turbine, the combustor liner having substantially cylindrical shape and comprising a first section and a second section wherein the...
US20160146464 COMBUSTOR WITH ANNULAR BLUFF BODY  
The present invention relates to a gas turbine combustor comprising: a flow sleeve; a combustion liner located at least partially within the flow sleeve thereby creating a main passage between the...
US20160138807 Gas Turbine Engine Flow Regulating  
A gas turbine combustor assembly includes a fuel injector, a dome stator around the fuel injector, and a dome sleeve coupled to the dome stator. The dome sleeve defines an air inlet opening with...
US20160138479 APPLICATION OF FUEL FLOW-BASED PROBABILISTIC CONTROL IN GAS TURBINE TUNING, 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...
US20160138469 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...
US20160123237 VARIABLE PRESSURE AIR SUPPLY  
The present disclosure relates to engine buffer systems. An engine buffer system may include a low pressure supply line and a high pressure supply line. A continuously variable valve may be...
US20160115839 SYSTEM AND METHOD FOR EMISSIONS CONTROL IN GAS TURBINE SYSTEMS  
A system includes an emissions control system. The emissions control system includes a processor programmed to receive one or more selective catalytic reduction (SCR) operating conditions for an...
US20160097538 FUEL NOZZLE  
A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway...
US20160097537 FUEL NOZZLE  
A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway...
US20160097536 FUEL NOZZLE  
A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway...
US20160084503 FUEL NOZZLE  
A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, a primary air passageway centrally defined axially in the body, and a...
US20160084169 METHOD OF OPERATING A MULTI-STAGE FLAMESHEET COMBUSTOR  
The present invention discloses a novel way of controlling a gas turbine engine using detected temperatures and detected turbine rotor speed. An operating system provides a series of operating...
US20160069276 A METHOD AND A DEVICE FOR GENERATING A COMMAND FOR THE FLOW RATE OF FUEL THAT IS TO BE INJECTED INTO A COMBUSTION CHAMBER OF A TURBINE ENGINE  
During a stage (E0) of starting the turbine engine, the method of the invention comprises: an open-loop generating step (E10) of generating a fuel flow rate command (WF_OL) from at least one...
US20160069271 Bulk Flame Temperature Regulator for Dry Low Emission Engines  
Systems and methods for regulating a bulk flame temperature in a dry low emission engine are provided. According to one embodiment of the disclosure, a method may include measuring an exhaust gas...
US20160069261 Ultra-High Efficiency Gas Turbine (UHEGT) with Stator Internal Combustion  
Provided is an internal combustion system for an ultra-high efficiency gas turbine (UHEGT) engine which includes a fuel injection system, an ignition system, a stator system, and a rotor system....
US20160061114 METHOD FOR CONTROLLING A GAS TURBINE  
The invention relates to a method for controlling a gas turbine, operating with an integral fuel reactivity measurement concept. In order to fast determine a safe operation range of the gas...
US20160061110 LOW NOX TURBINE EXHAUST FUEL BURNER ASSEMBLY  
A low NOX burner in which the amount of air flow to the low NOX (nitrous oxides) burner can be adjusted (e.g., based on determinations related to the TEG air flow to the low NOX burner). A low NOX...
US20160047550 DISTRIBUTED FUEL CONTROL SYSTEM  
Distributed fuel control system and methods are disclosed. A distributed fuel control system may comprise a controller, a fuel delivery system, and fuel delivery system sensors and combustion...
US20160047318 Torch Igniter  
A gas turbine combustor assembly includes a primary combustion chamber in fluid communication with a primary fuel injector and a primary air inlet. A torch igniter is carried by the primary...
US20160047315 ATOMIZING FUEL NOZZLE  
A fuel nozzle for a gas turbine engine. The nozzle has a body and a center axis. The body has an inner circumferential surface circumscribing a central passageway which is coaxial with the center...
US20160040885 SEQUENTIAL COMBUSTION WITH DILUTION GAS  
An exemplary sequential combustor arrangement includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the hot gases leaving the first combustion chamber during...
US20160033135 Fuel Injector For High Flame Speed Fuel Combustion  
A multiple fuel capable, pre-mixed, low emission injector is provided which is particularly suited for burning high flame speed fuels. The fuel injector includes an injector body having a...
US20160018110 AXIALLY STAGED GAS TURBINE COMBUSTOR WITH INTERSTAGE PREMIXER  
The present invention discloses a novel and improved apparatus and method for reducing the emissions of a gas turbine combustion system. More specifically, a combustion system is provided having a...
US20160010867 SEQUENTIAL COMBUSTOR ARRANGEMENT WITH A MIXER  
The invention refers to a sequential combustor arrangement having a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the hot gases leaving the first combustion...
US20160010548 SYSTEM AND METHOD FOR A TURBINE COMBUSTOR  
A system includes a turbine combustor, which includes a head end portion having a head end chamber. The head end portion includes an exhaust gas path, a fuel path, and an oxidant path. The turbine...
US20160010493 SYSTEM AND METHOD OF CONTROL FOR A GAS TURBINE ENGINE  
A system includes plurality of combustors and a distributed flow measurement system coupled to the plurality of combustors. Each combustor of the plurality of combustors includes one or more...
US20150377490 SUPPLEMENTARY LASER FIRING FOR COMBUSTION STABILITY  
A combustion system for a gas turbine includes a combustion chamber having an end section and a pre-combustion section extending from the end section, a swirler device, an optional pilot burner...
US20150377138 SYSTEMS AND METHODS FOR A FUEL PRESSURE OSCILLATION DEVICE FOR REDUCTION OF COHERENCE  
A system with a gas turbine engine is provided. The gas turbine engine includes a first combustor comprising a first fuel nozzle, a second combustor comprising a second fuel nozzle, and a first...
US20150377059 METHOD FOR MONITORING A DEGREE OF CLOGGING OF THE STARTING INJECTORS OF A TURBINE ENGINE  
A method for monitoring a degree of clogging of the starting injectors of a turbine engine, which includes: a combustion chamber into which at least one starting injector supplied with fuel leads,...

Matches 351 - 400 out of 426 < 1 2 3 4 5 6 7 8 9 >