Matches 1 - 50 out of 152 1 2 3 4 >


Match Document Document Title
US20140260308 REAR MOUNTED WASH MANIFOLD RETENTION SYSTEM  
A retention system includes a structure clamp to connect the retention system to another structure; and a manifold clamp connected to the structure clamp, the manifold clamp including a trough to...
US20150121894 BIFURCATION FIRE PURGE SYSTEM  
A bifurcation assembly for a gas turbine engine is disclosed and includes a housing defining an inner cavity. A first partition and a second partition extend across the inner cavity and define a...
US20140083111 GAS TURBINE ASYMMETRIC FUEL NOZZLE COMBUSTOR  
A combustor of a gas turbine engine includes a multiple of fuel nozzles arranged asymmetrically
US20140137535 CLOCKED COMBUSTOR CAN ARRAY  
The present application provides a clocked combustor can array for coherence reduction in a gas turbine engine. The clocked combustor can array may include a number of combustor cans positioned in...
US20130232989 GAS TURBINE ENGINE FUEL HEATING SYSTEM  
A fuel heating system for a gas turbine engine comprises a first heat exchanger, a second heat exchanger, a fuel pump and a valve. The first heat exchanger produces a heated air flow. The second...
US20150040578 DEVICE AND METHOD FOR GAS TURBINE UNLOCKING  
An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a...
US20120260667 Power Plant  
A power plant is provided and includes a gas turbine engine to generate power, a heat recovery steam generator (HRSG) to produce steam from high energy fluids produced from the generation of power...
US20150211420 COMBUSTOR IGNITER ASSEMBLY  
A gas turbine engine comprising a combustor having a combustor liner assembly and a mounting bracket provided on the combustor liner assembly, a floating collar being slidingly received on the...
US20150219018 SYSTEM AND METHOD FOR OPERATING A GAS TURBINE  
A system and method for operating a gas turbine include a controller that determines, for at least one combustion instability, a frequency; a quantification of the frequency or a quantification of...
US20140315136 METHODS OF OPERATING A GAS TURBINE TO INHIBIT VANADIUM CORROSION  
A method of inhibiting vanadic corrosion of a hot part of a gas turbine system is provided. The method includes introducing, in the combustor, a first oxide comprising magnesium oxide (MgO) and at...
US20130318994 ULTRA-VIOLET FLAME DETECTOR WITH HIGH TEMPERATURE REMOTE SENSING ELEMENT  
A flame sensor apparatus is provided including a sensor assembly for sensing characteristics of a flame within a combustion chamber. The flame sensor apparatus further includes an electrical...
US20150101343 GAS TURBINE COMBUSTOR  
A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device...
US20140260307 REAR MOUNTED WASH MANIFOLD AND PROCESS  
An engine wash manifold delivers wash liquid to an engine that includes an inlet, a fan, a case with an exhaust duct and a core inlet splitter. The manifold includes a wash delivery segment...
US20100319358 Nosecone ice protection system for a gas turbine engine  
A system includes a first anti-icing electrothermal heater located at tip of a gas turbine engine nosecone, and a plurality of anti-icing electrothermal heater strips extending rearward from the...
US20130098057 CONTROLLABLE SPEED WINDMILL OPERATION OF A GAS TURBINE ENGINE THROUGH LOW SPOOL POWER EXTRACTION  
A gas turbine engine that includes at least one component geared to a spool to control a speed of the low spool during a “windmilling” condition.
US20140196468 COMBUSTION ARRANGEMENT AND TURBINE COMPRISING A DAMPING FACILITY  
A combustion arrangement for a turbine is provided including: a casing; a combustion chamber within the casing, an inner casing volume may be defined as a volume inside the casing but outside the...
US20110146294 AIRPLANE ENGINE DEFLECTOR SYSTEMS  
A protective deflector for airplane engines system is disclosed herein comprising a turbine-covering screen assembly which may be installed to an airplane engine turbine housing by a securable...
US20140075954 Methods And Systems For Substance Profile Measurements In Gas Turbine Exhaust  
Methods and systems for substance profile measurements in gas turbine exhaust. In an embodiment, a concentration of a substance may be determined and associated with a combustor out of a plurality...
US20120216548 SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES  
Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative method for reducing overspeed potential of a turbine of a gas turbine...
US20140109589 GAS TURBINE ENGINE VARIABLE BLEED VALVE FOR ICE EXTRACTION  
A variable bleed valve includes a variable bleed valve door disposed in a bleed inlet in transition duct and rotatable about an axis at or near a forward end of door. Valve is operable to open and...
US20090158747 METHOD FOR THE CONTROLLED PURGING OF THE FUEL FEEDING SYSTEM IN THE COMBUSTOR OF A GAS TURBINE  
A method is described for the controlled purging of the fuel feeding system in the combustor of a gas turbine comprising at least one compressor, capable of compressing the air introduced into it...
US20150184592 DRAINAGE METHOD AND PURGE COLLECTOR OF A CARBURATION SYSTEM OF A HELICOPTER  
A helicopter engine collector includes an external longitudinal wall and two closed end walls, a longitudinal symmetry axis inclined ascendingly, couplings configured to be connected to purge...
US20130000318 ECOLOGY SYSTEM FOR DRAINING THE MANIFOLD OF A GAS TURBINE ENGINE  
A fuel system including a fuel pump metering unit (FPMU) for delivering fuel to an engine manifold with an ecology valve for draining and storing fuel from the engine manifold. The ecology valve...
US20130061599 FUEL MANIFOLD COOLING FLOW RECIRCULATION  
Cooling flow recirculation in fuel manifolds, such as fuel manifolds associated with gas turbine engines is disclosed. An example system for jet pump driven recirculation of manifold cooling flow...
US20130312423 METHOD OF DETECTING SHAFT BREAK  
A method of detecting shaft break in a gas turbine engine having a shaft system. The shaft system including a shaft that couples a compressor and a turbine. First construct a frequency model of...
US20090100821 Managing leaks in a gas turbine system  
A mixture of air and fuel is compressed in a compressor of a gas turbine system. The gas turbine system includes components that define one or more fuel leak locations, and leaked fuel is directed...
US20090060707 COMPRESSOR INLET GUIDE VANE DE-ICE CONTROL SYSTEM AND METHOD  
A system and method are provided for effectively removing ice that may have formed on gas turbine engine compressor inlet guide vanes and/or preventing, or at least inhibiting, reformation of ice...
US20140075953 SYSTEM AND METHOD FOR DETECTING AND CONTROLLING FLASHBACK AND FLAME HOLDING WITHIN A COMBUSTOR  
A system is provided for detecting and controlling flashback and flame holding in a combustor of a gas turbine. The system includes at least one flame indicator disposed in a combustor and at...
US20130199203 Linear Detonation Wave Diverter  
The presently disclosed linear detonation wave diverter provides a structure and method for quickly and controllably venting a detonation event out of the diverter without igniting working fluid...
US20130291552 ELECTRICAL CONTROL OF COMBUSTION  
A system for electrically controlling combustion includes a combustion chamber, one or more sensors, an actuator, and a controller. The controller detects dynamic instabilities based upon input...
US20130152600 SHAFT BREAK DETECTION  
A method to detect shaft break includes monitoring first and second parameters and defining a two-dimensional parameter space that is a function of the first and second parameters, the...
US20120204572 METHOD AND DEVICE FOR DETERMINING THE CAPACITY OF AN AIRCRAFT PUMP TO DELIVER A PREDETERMINED FUEL OUTPUT  
The invention proposes a method for determining the capacity of an aircraft pump to deliver a predetermined fuel flow rate, characterised in that it comprises a step of rotating the pump at a...
US20140102113 EXHAUST HEAT RECOVERY FOR A GAS TURBINE SYSTEM  
A system includes a gas turbine and an anti-icing system coupled to the gas turbine. The gas turbine is configured to receive air and fuel and to combust a mixture of the air and the fuel into...
US20070006596 Flashback-detecting equipment, flashback-detecting method and gas turbine  
When a temperature of cooling steam being measured by a temperature-measuring device 13 in one combustor 2-x among combustors 2-1 through 2-8 is confirmed to be higher than a temperature of a...
US20130133333 SHAFT BREAK DETECTION  
The present invention provides a method of detecting shaft break in a shaft system comprising a shaft coupled between two masses. The method comprises a number of steps. Firstly, to define a...
US20130199204 METHOD AND A DEVICE FOR PERFORMING A CHECK OF THE HEALTH OF A TURBINE ENGINE OF AN AIRCRAFT PROVIDED WITH AT LEAST ONE TURBINE ENGINE  
A method of automatically performing an engine health check for checking the health of at least one turbine engine of an aircraft. During flight, the stability of at least one monitoring parameter...
US20080236169 COMBUSTOR FLOATING COLLAR WITH LOUVER  
A gas turbine combuster ia provided with a dome heat shield having a fuel nozzle opening, the opening receiving a floating collar assembly for permitting relative movement between nozzle and heat...
US20130192247 GAS TURBINE ENGINE VARIABLE AREA FAN NOZZLE WITH ICE MANAGEMENT  
A method of managing a gas turbine engine variable area fan nozzle includes the steps of evaluating an icing condition to determine the likelihood of ice presence. A variable area fan nozzle...
US20090092487 Systems and Methods Involving Multiple Torque Paths for Gas Turbine Engines  
Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative spool assembly for a gas turbine engine, which incorporates a compressor,...
US20140345292 RETURN FLUID AIR COOLER SYSTEM FOR TURBINE COOLING WITH OPTIONAL POWER EXTRACTION  
In an aircraft including a gas turbine engine, a system for cooling the gas turbine engine includes a tank provided in a wing of the aircraft, the tank being configured to store a cooling fluid...
US20070245746 Methods and systems for detecting rotor assembly speed oscillation in turbine engines  
A method for operating a gas turbine engine is provided. The method comprises coupling at least one sensor within the gas turbine engine to transmit a signal indicative of a rotational speed of a...
US20060179816 Cooled dual wall liner closeout  
An example exhaust duct assembly includes a front liner, an intermediate liner and a rear liner. Each of the front, intermediate and rear liners include an inner liner exposed to combustion gases...
US20140238041 COMBUSTOR CAN TEMPERATURE CONTROL SYSTEM  
The present application provides a fuel delivery system for a combustor with reduced coherence and/or reduced combustion dynamics. The combustor can assembly may include a first manifold for...
US20130192248 GAS TURBINE ENGINE BUFFER SYSTEM  
A gas turbine engine includes a buffer system. The buffer system can include a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the buffer...
US20130239581 Systems and Methods for Preventing Flashback in a Combustor Assembly  
Embodiments of the present application include a combustor assembly. The combustor assembly may include a combustion chamber, a first plenum, a second plenum, and one or more elongate air/fuel...
US20140311156 COMBUSTOR CAP FOR DAMPING LOW FREQUENCY DYNAMICS  
A combustor cap for use with a number fuel nozzles, the combustor cap including a cold side plate, a hot side plate, and a cap cavity extending between the cold side plate and the hot side plate...
US20100180564 Systems and Methods for Mitigating a Flashback Condition in a Premixed Combustor  
A method may mitigate a flashback condition in a gas turbine. The gas turbine may include a fuel nozzle. The method may include detecting the flashback condition in the fuel nozzle, and...
US20140216053 GEARED TURBOFAN GAS TURBINE ENGINE WITH RELIABILITY CHECK ON GEAR CONNECTION  
A gas turbine engine includes a fan and a compressor. A combustor drives a turbine, including a first turbine with a shaft to drive the compressor. A fan drive turbine drives the fan through a...
US20130219913 GEARED TURBOFAN GAS TURBINE ENGINE WITH RELIABILITY CHECK ON GEAR CONNECTION  
A gas turbine engine includes a fan and a compressor. A combustor drives a turbine, including a first turbine with a shaft to drive the compressor. A fan drive turbine drives the fan through a...
US20100043390 CONTROLLING ICE BUILDUP ON AIRCRAFT ENGINE AND NACELLE STATIC AND ROTATING COMPONENTS  
A turbofan engine deicing system includes a core nacelle (12) housing a turbine. A turbofan (20) is arranged upstream from the core nacelle. A controller (50) manipulates the turbofan in response...

Matches 1 - 50 out of 152 1 2 3 4 >