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Matches 1 - 50 out of 8,770

Document Document Title
WO/2019/137598A1
The invention relates to a turbocharger (2) with a compressor housing (14), within which an inflow region (20) for charge air is located, followed in succession downstream in the direction towards a compressor duct (22) for an intake sys...  
WO/2019/138709A1
This gas turbine fuel supply system is provided with: a fuel supply flow passage provided with a fuel heating device which heats fuel, and supplying the fuel heated by the fuel heating device to a first nozzle and a second nozzle; a bypa...  
WO/2019/135053A1
The invention relates to a method for filtering an input signal (3b, 4b, 5b) relative to a physical variable of a turbine engine (9), the input signal being digitised, the method implementing frequency filtering of said signal in a compu...  
WO/2019/130976A1
This control device selects and implements either: a normal control for outputting a fuel flow rate command value by a feedback control based on a deviation between a target output and an actual output of a gas turbine; or a load reducin...  
WO/2019/129976A1
The invention relates to a method for controlling the fuel injection of a turbine engine using a fuel supply circuit (100). The supply circuit (100) comprises a pilot injection line (141) and a main injection line (142). During a transit...  
WO/2019/129084A1
A power control system (100) and an aircraft, the power control system (100) comprising: a controller (110), an engine temperature sensor (120), an intake temperature sensor (130), an intake pressure sensor (140), a throttle position sen...  
WO/2019/121252A1
A controller (300) for a gas turbine engine (10) which operates to a control method. The gas turbine engine (10) comprises a compressor (14) having a casing (50) which extends along, and is centred on, an operational axis (20). An array ...  
WO/2019/123077A1
Techniques for estimating a correction curve (212, 214) for a component (104-110) of a power plant (102) are described. The correction curve (212, 214) indicates variation of a performance indicator of the component due to an operating p...  
WO/2019/117135A1
A fuel supply device provided with: a first motorpump (10) that discharges fuel at a first flow rate toward an engine (X); a second motorpump (18) that discharges fuel at a second flow rate and merges this fuel with the fuel of the first...  
WO/2019/115120A1
The invention relates to a method for storing and producing energy by means of compressed air, comprising the following steps: - compressing the air using staged compressors, during which time the air is cooled, after at least one compre...  
WO/2019/098836A1
When the temperature of ambient air is relatively low, thermal output and thermal efficiency of a micro gas turbine (1) decrease. In order to compensate for the loss of thermal efficiency, the micro gas turbine (1) is equipped with a val...  
WO/2019/097894A1
A fuel supply control device (8) uses, as a fuel supply amount measuring valve, a parallel flow path formed of an orifice (6) and a pressurizing valve (5), and controls a fuel supply pump (3) on the basis of the differential pressure bef...  
WO/2019/091710A1
Method for operating a gas turbine of a power plant with gaseous fuel and liquid fuel The present invention relates to a method for operating a gas turbine (2) of a power plant (1) with gaseous fuel as well as with liquid fuel during a n...  
WO/2019/086294A1
A method of controlling a gas turbine engine (10) having in axial flow series a compressor (14), a combustor (16), a compressor-turbine (18) and an exhaust (30) and preferably a power turbine (19) located between the turbine (18) and the...  
WO/2019/086293A1
A method of controlling a gas turbine engine (10), the gas turbine engine (10) having in axial flow series a compressor (14), a combustor (16), a compressor-turbine (18) and an exhaust (30), the gas turbine capable of operating in at lea...  
WO/2019/078309A1
The purpose of the present invention is to calculate the flow volume per unit time of fuel fed into a gas turbine, and to calculate the flow volume per unit time of air fed into the gas turbine. A turbine entry temperature is calculated ...  
WO/2019/073577A1
Provided is a service menu presentation system which: acquires operation data relating to an electric power generation plant; decides which operation pattern, from among a plurality of operation patterns set in advance in accordance with...  
WO/2019/032295A3
A control system (12) for preventing electrical power supply disruptions in an electrical power system (10) includes an electronic control unit (14) structured to receive a power signal indicative of reactive power in an electrical gener...  
WO/2019/070160A1
The invention relates to a method of creating the required fuel pressure and flow rate in a fuel system of an aircraft gas turbine engine. According to the method, the operation of a fuel system and a gas turbine engine is supported by m...  
WO/2019/069011A1
The invention primarily relates to a discharge duct (30) of an intermediate housing hub for an aircraft turbojet engine, comprising an inlet end (41) and an outlet end (42), intended to ensure the passage of air from at least one dischar...  
WO/2019/059273A1
A rotating machine (1) control device (100) is provided with: an operating terminal (36) for changing a parameter of the rotating machine (1); a clearance measuring device (101) which measures the amount of clearance between a rotor (41)...  
WO/2019/053063A1
A controller (50) for a gas turbine arranged to supply a load L is described. The gas turbine comprises a fuel supply means arranged to supply fuel at a fuel flow rate FF to a combustor. The fuel supply means comprises a first fuel suppl...  
WO/2019/053043A1
A controller (50) for a gas turbine is described. The gas turbine is arranged to supply a load L. The gas turbine comprises a fuel supply means arranged to supply fuel at a fuel flow rate FF to a combustor, wherein the fuel supply means ...  
WO/2019/050648A1
A handheld combustion powered fastening tool may include a driving system that drives fasteners into workpieces in response to combustion of fuel by the driving system. A fuel delivery system may supply fuel to the driving system. The fu...  
WO/2019/032295A2
A control system (12) for preventing electrical power supply disruptions in an electrical power system (10) includes an electronic control unit (14) structured to receive a power signal indicative of reactive power in an electrical gener...  
WO/2019/030441A1
A system for regulating a thermal parameter (TM) associated with a heat exchange assembly (10) of a turbomachine (1), comprising: - at least one means (21) for measuring or for estimating said thermal parameter (TM); - a controlled valve...  
WO/2019/022918A1
An optical monitoring system includes a controller configured to determine a predicted status of a component based on an operational time of a rotary machine and an individual model. The controller is also configured to receive a first s...  
WO/2019/012238A1
A fuel metering circuit (1) for a turbomachine, comprising: - a meter (6), - a pump (4), - a control valve (5) configured to return an excess flow of fuel delivered to the meter (6) towards the pump (4) on the basis of a fuel pressure di...  
WO/2019/001947A1
The invention relates to a method for operating a gas turbine system (1) comprising a gas turbine (2) with a condenser (7) and an expansion turbine (9), a generator (4) which is driven by the gas turbine (2) for generating a current with...  
WO/2019/002925A1
The present disclosure provides systems and methods for controlling thrust produced at takeoff by at least one engine (114, 116) of an aircraft (100). At least one input signal comprising input data indicative of a speed of the aircraft ...  
WO/2018/234021A1
The invention relates to a method for starting and stopping a gas turbine (1) in a combined cycle power plant (2), wherein the gas turbine (1) comprises a compressor (3) having adjustable guide vanes (4) and the gas turbine power can als...  
WO/2018/212001A1
Provided is a gas turbine combustor (3) equipped with a fuel injection device (15) that has a plurality of annular fuel injection parts (25), each having numerous fuel injection ports (25a) formed therein, the gas turbine combustor being...  
WO/2018/202991A1
The invention relates to a system (1) for monitoring the state of health of a monitored aircraft engine (2). The system comprises an anomaly detection unit (3) which analyses engine operating parameters and raises an alarm (Al) if a resu...  
WO/2018/204376A1
A variable output fuel pump includes a BLDC motor and a control module to supply three power phases A, B and C to the motor, wherein the control module connects to a power supply connection of a vehicle, and to a vehicle communications n...  
WO/2018/185409A1
The invention concerns a method (100) for checking the maximum available power of a turbine engine (11, 12) of an aircraft (10) equipped with two turbine engines (11, 12) configured to operate in parallel and together to supply a necessa...  
WO/2018/186927A1
Systems and methods for adjusting an operating parameter of a machine based on an operating state of a component of the machine are provided. A method may be implemented by an electronic control unit (ECU) of the machine and includes det...  
WO/2018/180773A1
Provided is a combustion device equipped with: an ammonia supply unit (6) that, by supplying primary reduction ammonia as a nitrogen oxide reducing agent to within a combustor (2) and mixing secondary reduction ammonia with combustion ex...  
WO/2018/180996A1
This combustion device uses compressed combustion air to cause the combustion of fuel ammonia within a combustion chamber, and is equipped with a combustion air cooling unit (6) that cools the combustion air by means of heat exchange wit...  
WO/2018/181355A1
This operation management device is provided with: a state acquisition unit that acquires the measurement value of a first state quantity indicating the operation state of a power generation plant; a state update unit that updates, on th...  
WO/2018/173122A1
This combustor 20 comprises a tubular combustor liner 70, and a fuel nozzle 21A that is provided to one end of the combustor liner 70 and that sprays fuel and an oxidant into the combustor liner. The fuel nozzle 21A is provided with a pl...  
WO/2018/169605A1
Systems and methods that include and/or leverage a neural network to approximate the steady-state performance of a turbine engine are provided. In one exemplary aspect, the neural network is trained to model a physics-based, steady-state...  
WO/2018/166828A1
The invention relates to an inner casing structure (24) for a low-pressure turbine stage (7) in which a condensation chamber (40) is placed between a first bleeding chamber (35) and a second bleeding chamber (36), steam is supplied to th...  
WO/2018/168338A1
Provided is an engine system capable of promptly dealing with the occurrence of failure in a power supply part or operation control part. The engine system comprises: an engine 40 for outputting shaft power by burning fuel G; a system bo...  
WO/2018/164869A1
A system includes a display, a processor, and memory storing instructions that cause the processor to receive a request to scale one or more objects of on a model depicted on the display, identify the one or more objects of the model, de...  
WO/2018/162994A1
The present disclosure relates to systems and methods that are useful for controlling one or more aspects of a power production plant. More particularly, the disclosure relates to power production plants and methods of carrying out a pow...  
WO/2018/162841A1
A method and device for detecting conditions conducive to the onset of pumping that can affect a low-pressure compressor of an aircraft turbine engine, said turbine engine further comprising a high-pressure compressor, said method compri...  
WO/2018/155552A1
This gas turbine control device is provided with: a first estimation unit for estimating a first temperature that is a turbine inlet temperature estimation value based on a first model, which is a physical model using a fuel flow rate fo...  
WO/2018/151213A1
This control device, which controls an inflow adjusting unit which quantitatively adjusts an inflow of gas to a compressor, and controls a valve provided in a second flow passage which branches from a first flow passage leading from the ...  
WO/2018/146422A1
The invention relates to a method for controlling the speed and the power of a turbine engine propeller, wherein at least two operating modes are implemented: - one operating mode, called "speed mode", in which the pitch (β) of the prop...  
WO/2018/144080A1
Systems and methods for integrated power and thermal management in a turbine-powered aircraft are provided. The systems may include rotationally-independent first and second auxiliary power unit shafts, a power turbine, a first compresso...  

Matches 1 - 50 out of 8,770