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Matches 201 - 250 out of 8,850

Document Document Title
WO/2016/185119A1
The invention relates to an intermediate casing hub of an aircraft turbojet engine, which includes: an outer shroud (14) intended for defining a secondary flow space of a stream of secondary gas on the inside and an inter-flow area on th...  
WO/2016/181069A1
The invention relates to a butterfly valve (24) for bleeding a compressor for an aircraft turbine engine, the valve including a valve body (32), a butterfly (36), and a device (42) for controlling the angular position of the butterfly, t...  
WO/2016/177538A1
The invention relates to a method for computer-supported processing of a digitally saved series of measurement data. In the method according to the invention, a first function, which approximates the progression of the data points of the...  
WO/2016/176174A1
The invention relates generally to an electrical power and storage system and more specifically to ways and methods of using a thermal storage medium as a heat source to heat compressed air from a power augmentation system for use in a g...  
WO/2016/175753A1
A fuel delivery system (10) for a gas turbine engine (12) that employs a technique for purging fuel delivery tubes (82). The fuel delivery system includes a multifunction valve (64) that has a flow through position (66) and a bi-directio...  
WO/2016/172083A1
A fuel metering valve includes a valve body housing a valve element in an interior chamber between an inlet port and an outlet port, an actuator coupled to move the valve element relative to the valve body, and a controller configured to...  
WO/2016/172244A1
A fuel metering valve includes a valve body housing a valve element in an interior chamber between an inlet port and an outlet port, an actuator coupled to move the valve element relative to the valve body, and a controller configured to...  
WO/2016/167925A1
A method of operating a multi-engine, rotary wing aircraft in a single engine, in-flight mode, the method includes stopping a first engine while operating a second engine; closing variable inlet guide vanes on the first engine; and turni...  
WO/2016/162139A1
The invention relates to a device (100) for detecting the rotational angle of the position of a plurality of adjustable guide vanes (11) of a gas turbine (10), comprising at least three rotational angle sensors (1, 2, 3) at different loc...  
WO/2016/163907A1
´╗┐The present patent application provides a monitoring system for use with a mechanical device, especially a gas turbine, comprising a number of sensors configured to measure physical data from the mechanical device, a data acquisition ...  
WO/2016/156739A1
The invention relates to a hub (2) of an intermediate casing (1) for a dual-flow turbine engine, said hub (2) comprising: a discharge flow duct (18) extending between an inner shroud (3) and an outer shroud (5) of the hub (2), the discha...  
WO/2016/156740A1
The invention relates to a flow limiter which comprises a body (1) comprising a fluid intake (2) and a fluid outlet (3), in which body a pipe (5) for circulating the fluid is provided, comprising a series of chambers having different cro...  
WO/2016/151849A1
A turbine rotor blade according to an embodiment of the present invention comprises: a hub part that is connected to one end of a rotating shaft; a plurality of main blades that are provided on a peripheral surface of the hub part so as ...  
WO/2016/147077A1
Methods and related apparatus for improving synchronization of two or more engines on an aircraft are disclosed. Such method may be used where each engine comprises a first spool and a second spool, and, where a rotational speed of a fir...  
WO/2016/144752A1
A gas turbine system includes a turbine combustor (160). The turbine combustor includes one or more first fuel injectors coupled to a head end (166) of the turbine combustor and configured to deliver a first portion of a fuel to a first ...  
WO/2016/136588A1
A turbine, wherein: a turbine nozzle includes a ring-shaped partition plate for forming an inside nozzle channel in the interval between the partition plate and the nozzle inner ring, and forming an outside nozzle channel in the interval...  
WO/2016/131561A1
The invention relates to a method for operating a turbine installation (4). In order that the turbine installation (4) can be operated cost-effectively, in particular in compliance with a predetermined operating condition, a power contro...  
WO/2016/128479A1
The method is used for improving partial load efficiency in a gas turbine engine (1) comprising a compressor (2), burners (3), an high pressure turbine (4) and a low pressure turbine (5); it comprises the step of operating the gas turbin...  
WO/2016/126873A1
A gas turbine system includes a turbine combustor, a turbine, an exhaust gas compressor, an exhaust gas recirculation (EGR) system, a carbon black recovery system, and a carbon black production controller. The carbon black production con...  
WO/2016/123613A1
An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a GT engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes mo...  
WO/2016/122297A1
The invention relates to a fuel drive pump, having a monolithic structure, for turbines of aircraft, comprising a pump body, wherein all the components are assembled to establish and control the pressure and flow in the pump, including a...  
WO/2016/120626A1
A system for reducing pressure in a gas flow for a gas let-down system comprising: an expander driven by a first gas input; a heat exchanger, wherein an output of the expander is input to the heat exchanger; and a compressor driven by a ...  
WO/2016/111772A1
A method for calibrating a fuel control valve assembly (30) including a valve (31) and an actuator (32) is disclosed. The method includes determining an encoder offset by actuating the valve (31) until a predetermined value for the effec...  
WO/2016/012715A9
The main subject matter of the invention is a system (1) for supplying pressurised air installed in an aircraft turbine engine, configured to supply pressurisation air to a portion of the aircraft for using compressed air from pressurisa...  
WO/2016/109725A1
A method includes combusting a fuel and an oxidant in a combustor of an exhaust gas recirculation (EGR) gas turbine system that produces electrical power and provides a portion of the electrical power to an electrical grid. The method fu...  
WO/2016/102878A1
The invention relates to a method for detecting a high temperature fluid leak in a turbomachine (10). The turbomachine (10) comprises a source of high temperature pressurised fluid, at least one fluid distribution line (14, 15) suitable ...  
WO/2016/098503A1
This gas turbine plant control unit is provided with: an opening setting part for setting the opening of a fuel pressure adjusting valve of a gas turbine on the basis of gas turbine state information which is the information about the st...  
WO/2016/098220A1
The gas turbine power generation system of the present invention repeats either the supply or absorption of power, in addition to generating power. The gas turbine power generation system is provided with a first rotation shaft, a compre...  
WO/2016/098266A1
A gas turbine power generation system having an improved function to stabilize the power system is disclosed. The gas turbine power generation system has a dual-shaft gas turbine, an electric generator mechanically connected to a low pre...  
WO/2016/092239A1
A device (44) for controlling an exhaust nozzle (32) with variable cross-section of a turbojet engine (20) nacelle (10) of an aircraft, the device (44) comprising a computer (46) suitable for determining a position setpoint of the nozzle...  
WO/2016/091604A1
The method allows to control a test apparatus for a gas turbine engine; WI values of one or more tentative fuel gas mixtures are predicted by calculations and the predicted WI values are used for setting the composition of a fuel gas mix...  
WO/2016/078932A1
The invention relates to a method for cooling down a gas turbine (2), wherein the gas turbine (2) is run down from the power operation thereof to cool-down operation, and wherein a liquid is sprayed into air sucked in by a compressor (3)...  
WO/2016/077440A1
Control systems and methods suitable for combination with power production systems and methods are provided herein. The control systems and methods may be used with, for example, closed power cycles as well as semi-closed power cycles. T...  
WO/2016/072998A1
A compressor includes a purge flow extraction path extending radially and configured to direct an airflow radially inwardly. Also included is a center bore at least partially defined by a rotor structure extending axially and fluidly cou...  
WO/2016/066376A1
The invention relates to a turbine control unit (1) for controlling a turbine (6, 8, 10), in particular for controlling the start-up of a turbine (6, 8, 10), said unit being designed as a cascade controller comprising a master controller...  
WO/2016/056180A1
A fuel injecting device (36) for a combustor (12) has a pilot burner (40) and a main burner (4). The main burner (4) has at least one first fuel injection port (41a) to supply a first fuel to an upstream section of a combustion chamber (...  
WO/2016/055738A1
Method for notifying an authorization to completely shut down an aircraft gas turbine engine and aircraft gas turbine engine comprising a device for such notification, the method comprising, following the detection (E10) that the engine ...  
WO/2016/055354A1
The invention relates to a gas turbine (1) comprising at least one rotor (2) and an inner housing part (3) in order to form an annular chamber (4) between the rotor (2) and the inner housing part (3). The annular chamber (4) is fluidical...  
WO/2016/055278A1
A (micro) gas turbine arrangement has a gas turbine device (12) with a combustion chamber system (28), a turbine (30) driven by an exhaust gas stream (32) from the combustion chamber system, and a compressor (22) for supplying the combus...  
WO/2016/052205A1
In the present invention, gas turbine equipment is provided with a gas turbine (10) for which a mixed gas of natural gas and boil-off gas is the fuel, a fuel flow control valve (31) for regulating the flow rate of the fuel supplied to th...  
WO/2015/187230A3
A multi-stage centrifugal pump assembly allows for multiple fixed ratio pressure levels. The multiple pressure levels permit optimization of actuation loops without the need for pressure regulators, and can be used directly by the actuat...  
WO/2016/042960A1
A combustion burner comprises: a nozzle; a swirl vane that has a fuel injection hole for injecting fuel, is provided around the nozzle in an annular air flow channel extending along the axial direction of the nozzle, and is configured so...  
WO/2016/038672A1
In order to enhance the tracking performance of power generation equipment with respect to a load variation and increase the reliability of the power generation equipment, a dynamic characteristic model simulating the dynamic characteris...  
WO/2016/039943A1
Systems and methods for regulating a bulk flame temperature in a dry low emission engine are provided. According to one embodiments of disclosure, a method may include measuring an exhaust gas temperature (EGT) and determining a target E...  
WO/2016/035433A1
Failure detection accuracy is improved by providing: an accumulated data storage unit (30); a unit space generating means (13) which extracts, from the accumulated data storage unit, sensor values for a unit space to be used by an MT sys...  
WO/2016/035416A1
A gas turbine control device comprising a compressor, a combustor, and a turbine, executes load control that varies an operation control point for controlling gas turbine operation in accordance with the gas turbine load. The gas turbine...  
WO/2016/031355A1
A control device (14) for a gas turbine in which indrawn air is compressed by a compressor to produce compressed air, the compressed air is mixed with fuel supplied from a combustor and is burned to generate combustion gas, and the turbi...  
WO/2016/030616A1
The invention relates to a device for starting a gas turbine, comprising a starter system able on command to drive said gas turbine in rotation. The starter system comprises means for receiving information representative of the rotationa...  
WO/2016/030352A1
The invention relates to a method for operating a gas turbine (1) in the event of load shedding, which comprises the following steps: generating an electrical signal (10) by means of the control system (11) in order to initiate load shed...  
WO/2016/023987A1
The invention relates to a method for operating a power plant (1) comprising a gas turbine (2) and an emergency fuel system (11). In a normal operating state, gas (5) is supplied from a supply line (3) to the combustion process (4) of th...  

Matches 201 - 250 out of 8,850