Matches 401 - 426 out of 426 < 1 2 3 4 5 6 7 8 9


Match Document Document Title
US20150354466 GAS TURBINE SYSTEM, CONTROLLER, AND GAS TURBINE OPERATION METHOD  
The gas turbine system has: a gas turbine having a compressor, a combustor, and a turbine; a fuel supply mechanism for supplying fuel to the combustor; a composition detection unit for detecting...
US20150354460 Distributed Spark Igniter for a Combustor  
An ignition system for a combustor of a gas turbine engine is disclosed. The ignition system may include an igniter operatively associated with the combustor, and an electrode operatively...
US20150354459 FUEL INJECTOR FOR HIGH ALTITUDE STARTING AND OPERATION OF A GAS TURBINE ENGINE  
A fuel injector for a combustor of a gas turbine engine includes an air swirler adjacent to a pressure atomizer.
US20150354458 METHOD FOR STARTING A COMBUSTION SYSTEM  
A method for starting a combustion system having a first ignition device and an at least second ignition device, a processing unit and a sensor system. To obtain a reliable ignition the method...
US20150352483 METHOD AND DEVICE FOR GENERATING FUEL FOR A GAS TURBINE  
The invention relates to a method for fractionating a feed gas (1) containing hydrogen and carbon dioxide, from which feed gas carbon dioxide is largely selectively removed by scrubbing in a first...
US20150345791 APPARATUS AND A METHOD OF CONTROLLING THE SUPPLY OF FUEL TO A COMBUSTION CHAMBER  
Combustion chamber includes a primary stage fuel burner to supply fuel into a primary combustion zone and secondary stage fuel burner supplies fuel into a secondary combustion zone. A sensor is...
US20150345402 SYSTEMS AND METHODS FOR VARIATION OF INJECTORS FOR COHERENCE REDUCTION IN COMBUSTION SYSTEM  
A system includes a gas turbine engine having a first combustor and a second combustor. The first combustor includes a first fuel conduit having a first plurality of injectors. The first plurality...
US20150338102 COMBUSTOR FOR GAS TURBINE ENGINE  
A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel...
US20150337742 GAS TURBINE WITH FUEL COMPOSITION CONTROL  
A method for operating a gas turbine plant is provided. According to the method a first fuel gas with a first fuel reactivity and a second fuel gas with a second fuel reactivity which is higher...
US20150337739 RAMP RATE CONTROL FOR A GAS TURBINE  
A method for operating a gas turbine is disclosed. The method can include receiving a command for a new load set-point for a gas turbine. In response to the received new load set-point, a fuel...
US20150330636 SYSTEM AND METHOD FOR CONTROL OF COMBUSTION DYNAMICS IN COMBUSTION SYSTEM  
A system includes a gas turbine engine that includes a first combustor and a second combustor. The first combustor includes a first fuel nozzle disposed in a first head end chamber of the first...
US20150330311 FUEL METERING VALVE AND METHOD OF MANAGING FUEL IN A METERING VALVE  
A fuel metering valve includes a main flow path extending axially between an inlet and an outlet. Also included is a plunger disposed around a portion of a plunger guide, the plunger and the...
US20150330307 LASER-CHARGED HIGH-SPEED PROPULSION SYSTEM AND METHOD FOR PRODUCTION OF HIGH-POWERED LASER  
A high-speed propulsion system for a high-speed vehicle includes an air intake duct, a compression section, a combustion section, and an expansion section. A gas dynamic laser generator is...
US20150323187 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...
US20150316267 RECESSED FUEL INJECTOR POSITIONING  
A combustion chamber for a gas turbine is provided. The combustion chamber has a pilot burner device, a fuel injector and an ignitor unit. The pilot burner device has a pilot body with a pilot...
US20150316266 BURNER WITH ADJUSTABLE RADIAL FUEL PROFILE  
A burner (1) with a longitudinal burner axis (2) and a mixing channel (3, 4), formed in an annular manner around the longitudinal burner axis (2), for the mixing of fuel and air. Each mixing...
US20150316000 GAS TURBINE ENGINE SYSTEMS AND METHODS INVOLVING ENHANCED FUEL DISPERSION  
Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path...
US20150308348 CONTINUOUS DETONATION WAVE TURBINE ENGINE  
A gas turbine engine includes a transient plasma igniter in communication with a continuous detonation wave combustor. A method of operating a gas turbine engine includes maintaining ignition of a...
US20150300646 METHOD FOR PREMIXING AIR WITH A GASEOUS FUEL AND BURNER ARRANGEMENT FOR CONDUCTING SAID METHOD  
A method for premixing air with a gaseous fuel for being burned in a combustion chamber includes: guiding the air in an air stream along a burner axis through a coaxial air tube into a combustion...
US20150292416 Gas Turbine Power Generation Equipment  
This invention provides a gas turbine power generation equipment adapted to prevent step out of an electric power generator due to a system trouble such as a momentary power failure in a local...
US20150292405 BURNER ARRANGEMENT, COMBUSTOR, GAS TURBINE ENGINE AND METHOD FOR DETERMINING A RATE OF SOOT DEPOSITION IN GAS TURBINE COMBUSTORS  
A burner arrangement for a combustor of a gas turbine engine including a burner body is provided. The burner arrangement includes a cut-out and a burner face, the cut-out piercing the burner face,...
US20150275769 BLEED AIR SYSTEMS FOR USE WITH AIRCRAFT AND RELATED METHODS  
Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet, a compressor outlet, and a first drive shaft. The...
US20150267611 APPLICATIONS OF OXY-FUEL COMBUSTION TECHNOLOGY INTO GAS TURBINE COMBUSTORS AND ION TRANSPORT MEMBRANE REACTORS  
Experimental and numerical investigations on an atmospheric diffusion oxy-combustion flame in a gas turbine model combustor are conducted. The combustor is fuelled with CH4CH4 and a mixture of CO2...
US20130291550 AERO COMPRESSION COMBUSTION DRIVE ASSEMBLY CONTROL SYSTEM  
A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the...
US20120131927 Advanced Optics and Optical Access for Laser Ignition for Gas Turbines Including Aircraft Engines  
A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system including a laser light source configured to generate a laser beam,...
US20120131926 ADVANCED LASER IGNITION SYSTEMS FOR GAS TURBINES INCLUDING AIRCRAFT ENGINES  
A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system comprises at least one laser light source configured to generate a...

Matches 401 - 426 out of 426 < 1 2 3 4 5 6 7 8 9