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Matches 351 - 400 out of 8,852

Document Document Title
WO/2014/088671A8
A gas turbine engine variable bleed apparatus (48) includes a variable bleed valve door (50) disposed in a bleed inlet (47) in a transition duct (29), rotatable about two or more separate pivot points (160), operable to open and close an...  
WO/2015/062966A1
The invention concerns a method of operating a gas turbine (100) in order to ensure that a gas turbine operates reliably and economically in natural gas supply mains with a power-to-gas feed. To that end, the hydrogen content of the fuel...  
WO/2015/063735A1
Control method and device for controlling a gas turbine plant (1) provided with at least a gas turbine (5), a combustion chamber (4) and a compressor (3); the method comprising the steps of: - setting a plurality of reference values for ...  
WO/2015/062948A1
The invention relates to a gas turbine (100) and suitable operating methods, wherein the gas turbine (100) comprises a compressor (1) for providing compressed air (2), a combustion chamber (4) provided with a burner (3), and an expansion...  
WO/2015/064428A1
This temperature control device is equipped with: a temperature difference calculation unit that calculates a temperature difference between the inlet and outlet of a booster compressor that outputs cooling air, obtained by cooling compr...  
WO/2015/062979A1
The invention relates to a gas turbine (10) and to a method for producing a gas turbine (10) with a housing (1) and a compressor (2), wherein the compressor (2) has a rotor (3) with multiple compressor discs (4a, 4b). The rotor (3) carri...  
WO/2015/054834A1
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 compressor shaft and is configured to sele...  
WO/2015/053003A1
Provided is a fuel injection device for gas turbines that is capable of uniformizing, with a simple structure and at low cost, the concentration distribution of a fuel gas and water vapor in a combustion chamber, and that is capable of e...  
WO/2015/052458A1
A method (100) of diagnosing an auxiliary power unit (10) fault in an aircraft (50) having an auxiliary power unit and multiple sensors related to the auxiliary power unit, components thereof, and systems related thereto, including recei...  
WO/2015/052413A1
The invention relates to a method for optimising the specific consumption of a helicopter provided with two turboshafts (1, 2), each one comprising a gas generator (11, 21) provided with a combustion chamber (CC), each of said turboshaft...  
WO/2015/054079A1
Methods and apparatus for measuring liquid fuel flows within a conduit (104) are disclosed. An example flow sensor (101) may include a conduit (104) arranged to flow fuel therethrough along a flow axis (154), the conduit (104) defining a...  
WO/2015/023323A3
According to various embodiments, a fuel pump system 50 having a servo controlled pump bypass 67 is utilized. The servo controlled bypass around the fuel pump provides the capability for the fuel flow rate to be adjusted and controlled i...  
WO/2015/050601A2
A fuel system for a gas turbine engine comprises an injector disposed to inject fuel and air into a combustor of the gas turbine engine. In a first embodiment, the fuel system further comprises an air separation module configured to supp...  
WO/2015/046133A1
A fuel system (1A) is provided with a centrifugal pump (2a) that pressurizes and discharges fuel (N) that is supplied to an aircraft engine (E). The fuel system (1A) is also provided with a transmission (2c) that: connects the engine (E)...  
WO/2015/045905A1
This fuel system (1A) is provided with: a constant volume pump (2i) and a centrifugal pump (2a) that pressurize and discharge a fuel (N) that is supplied to an aircraft engine (E); a calculation control means (4) that is configured so as...  
WO/2015/046177A1
A fuel system (1A) is provided with a constant volume pump (2c) that pressurizes and discharges fuel (N) that is supplied to an aircraft engine (E). The fuel system (1A) is additionally provided with a transmission (2d) that: connects th...  
WO/2015/047468A2
A control system for turbofan engine includes a first sensor measuring rotation of a first shaft at a first location and a fan shaft sensor measuring a speed of a fan shaft. A controller utilizes measurements of a first speed of the firs...  
WO/2015/048214A1
A gas turbine engine includes a fan, a turbine having a fan drive rotor, and a speed reduction device effecting a reduction in the speed of the fan relative to an input speed from the fan drive rotor. The fan drive rotor has a number of ...  
WO/2015/041346A1
A gas turbine (10) equipped with a compressor (11), a combustion chamber (12) and a turbine (13) is further equipped with: a pressurizing device (40) for taking in some of the compressed air compressed by the compressor (11), and pressur...  
WO/2013/143827A3
The invention discloses a method for operating a combined cycle power plant (10) with an integrated CO2 capture unit (14), wherein flue gas of a gas turbine (11) is led along an flue gas path through a heat recovery steam generator (19),...  
WO/2015/042123A1
A system 100 for controlling a gas turbine based power plant 10 includes a plurality of sensors 34 configured to transmit signals 72 indicative of one or more operating parameters of the gas turbine 12, and a control system 20 in electro...  
WO/2015/040569A1
A method of controlling emissions of a gas turbine plant (1), including a compressor (7), a combustion chamber (9) and a gas turbine (10), includes detecting the oxygen concentration (S02) in the exhaust gases (QE) of the gas turbine (10...  
WO/2015/038247A1
A fluid pressure regulating system includes a turbomachine configured and adapted to pressurize fluid in a first mode and to depressurize fluid in a second mode. An energy exchange device is operatively connected to the turbomachine to p...  
WO/2015/036233A1
The invention relates to a gas turbine (1) comprising a compressor (2), a turbine unit (3), at least one combustion chamber (4) and a secondary air system (10), which secondary air system (10) has at least one cooling line (20) having a ...  
WO/2015/034513A1
An aircraft including a jet engine including a core having a compressor and combustion chamber, and a particulate sensor located within the core and a particulate detection method for an aircraft having a jet engine where the method incl...  
WO/2015/034133A1
The present invention provides a gas turbine combustion instability control device, which is combustion instability device for controlling the operation of a gas turbine by measuring the combustion dynamics of the gas turbine, and the de...  
WO/2015/033786A1
A fuel supply system for a gas turbine engine is provided with: a confluence passage (19) connected to a combustion nozzle (11); a first pump (P1) for discharging fuel into the confluence passage (19); a first electric motor (M1) for dri...  
WO/2015/033046A1
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 control circuit (9a) and in the main ci...  
WO/2015/006153A3
A fan drive gear system for a turbofan engine includes a geared architecture and a gear controller supporting the geared architecture and controlling rotation of the geared architecture relative a static structure.  
WO/2015/033769A1
This control device (50) is provided with: a temperature control unit (51) which controls the degree of opening of a fuel flow regulator valve (47) so as to maintain the inlet of a turbine (21) into which a fuel gas enters at a constant ...  
WO/2015/031318A1
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 representation of a second derivative with re...  
WO/2014/189574A3
A method of controlling a variable vane assembly includes the steps of sensing a first angular deflection of a first array of variable vanes about a first vane axis, and a second angular deflection of a second array of variable vanes abo...  
WO/2014/200597A3
Advanced gas turbines and associated components, systems and methods are disclosed herein. A gas turbine configured in accordance with a particular embodiment includes a rotor operably coupled to a shaft and a stator positioned adjacent ...  
WO/2015/025109A1
The invention relates to a system for injecting fuel into a combustion chamber of an engine, comprising at least two fuel circuits, one with a constant flow rate (1) and the other with an intermittent flow rate (2), members (4, 5) for do...  
WO/2014/185997A3
Disclosed is a gas turbine engine including a compressor section in communication with a bleed flow path. A rotary valve is provided in communication with the bleed flow path to selectively regulate a flow of fluid within the bleed flow ...  
WO/2015/026444A1
A turbine section including a high pressure turbine, an intermediate pressure turbine and a fan drive turbine, the fan drive turbine driving a gear reduction to in turn drive a fan, and effecting a reduction in the speed of the fan relat...  
WO/2015/023323A2
According to various embodiments, a fuel pump system 50 having a servo controlled pump bypass 67 is utilized. The servo controlled bypass around the fuel pump provides the capability for the fuel flow rate to be adjusted and controlled i...  
WO/2015/022786A1
A gas turbine engine optimization control device estimates a fuel consumption rate (SFC) using a given control parameter for a variable mechanism, finds the change between the estimated value for the fuel consumption rate based on the co...  
WO/2014/189568A3
An example section of a gas turbine engine includes a plurality of variable vanes circumferentially disposed about an engine axis, a first moveable annular ring disposed on an upstream side of the variable vanes, a second movable annular...  
WO/2015/022378A1
The present invention provides a purge system for a gas turbine, the gas turbine comprising a compressor (1), a combustion chamber (2), at least one burner (3) and a gas fuel system, characterized in that the purge system comprises: a co...  
WO/2015/020892A1
A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The...  
WO/2015/019003A1
This module (5) allows the filtering of a raw setpoint (N1_CMD_OP) intended for a corrector network (6) in an engine regulating system (20). It comprises: - a module (54) for detecting a filtering condition of said raw setpoint, and; - m...  
WO/2015/017080A1
A system includes a gas turbine engine that includes a combustor section having a turbine combustor that generates combustion products, a turbine section having one or more turbine stages driven by the combustion products, an exhaust sec...  
WO/2015/017405A1
A method of immobilizing a contaminant within a component includes identifying the contaminate; and thermally processing the component via a specific thermal cycle related to the contaminate. A method of repairing a component includes im...  
WO/2014/186017A3
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan, a compressor section having a low pressure compressor and a high pressure compressor, a combustor section, and a turbine...  
WO/2014/186008A3
A gas turbine engine has a compressor rotor with blades and a disk. A bore is defined radially inwardly of the disk. A combustor includes a burner nozzle. A tap taps air that has been combusted in the combustor section through a valve, a...  
WO/2015/009942A1
A fuel circulation system and methods are provided. The system includes a supply pump for providing an outlet flow of fuel. The system also includes at least a first and a second servo. The first servo is connected to an outlet of the su...  
WO/2015/010033A1
An engine fuel system and methods are provided. The engine fuel system includes a supply arrangement for providing an outlet flow of fuel to a bypass metering arrangement. The bypass metering arrangement in turn provides a metered flow o...  
WO/2015/009392A2
A turbine nozzle apparatus includes: a vane (16) extending between inner and outer bands (12, 14), the interior of the vane (16) being open and communicating with an aperture (30) in the outer band (14), wherein the vane (16) and the ban...  
WO/2014/106265A3
A gas turbine system includes a combustor configured to combust an oxidant and a fuel in the presence of an exhaust gas diluent to produce combustion products, an oxidant supply path fluidly coupled to the combustor and configured to flo...  

Matches 351 - 400 out of 8,852