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Matches 1 - 50 out of 8,840

Document Document Title
WO/2019/217632A1
A turbine control system is provided for decreasing the response time between readings of the speed of the turbine and changing a valve position in response thereto. The speed control system includes a speed probe that detects the speed ...  
WO/2019/206566A1
A method of controlling a combustion system of a gas turbine engine (10). The gas turbine engine (10) has a combustor (28) with a primary combustion zone (110), of which a condition in the primary combustion zone (110) is defined by a pr...  
WO/2019/203696A1
The invention relates to a system for evaluating the technical condition of gas turbine assemblies on the basis of temperature fields, and is directed toward more accurately determining a temperature deviation from an initial value. In a...  
WO/2019/202917A1
[Problem] To observe a predictor of or the occurrence of unstable operation of a turbo machine. [Solution] An observation device 1 having: a detection unit 10 that is arranged in a turbo machine 2 and has one or more sensors 11 and 12 th...  
WO/2019/198730A1
This control device for a gas turbine is configured to include: a target value calculation unit for calculating a control target value that is a target value of an output of the gas turbine; and a command value calculation unit for calcu...  
WO/2019/198793A1
This valve opening degree determining device determines the valve opening degree of a cooling air adjustment valve for controlling the supply of cooling air to a disk cavity, the valve opening degree determining device being provided wit...  
WO/2019/187980A1
This single-shaft combined cycle plant comprises: a power generator; a gas turbine; a steam turbine that is driven by using waste heat from the gas turbine, and is connected to the power generator by a clutch when the rotational speed sy...  
WO/2019/188484A1
This fuel supply device is provided with a first supply pipe (2f), a first on-off valve (V1), a second on-off valve (V1, V2), a second supply pipe (2d), a connecting pipe (2h), a third on-off valve (V3), and a leak check measuring device...  
WO/2019/190662A1
The invention relates to a valve assembly (100) for a multi-scroll turbine (10) for controlling an overflow of exhaust gases between a first spiral (36) and a second spiral (38) and for controlling a bypass opening (50). The valve assemb...  
WO/2019/180260A1
An electronic control system (35) for a turbopropeller engine (2) having a gas turbine (20) and a propeller assembly (3) coupled to the gas turbine (20), the control system (35) implementing a propeller control unit (PEC) to control prop...  
WO/2019/180250A1
An electronic control system (30) for a turbopropeller engine (12) having a gas turbine (20) and a propeller assembly (13) coupled to the gas turbine (20), controls propeller operation based on a pilot input request, via generation of a ...  
WO/2019/180253A1
An electronic control system (35) for a turbopropeller (2) having a gas turbine engine (20) and a propeller assembly (3) coupled to the gas turbine engine (20), the control system (35) having: a propeller control stage (35a), implementin...  
WO/2019/177597A1
One exemplary embodiment is a system including an internal combustion engine operatively coupled with a variable geometry turbocharger, the variable geometry turbocharger including a compressor, a turbine coupled with the compressor and ...  
WO/2019/170984A1
The invention relates to a turbomachine fuel supply system comprising a fuel circuit including a pressurising means at the outlet of the circuit, a pump arranged to supply the circuit with a fuel flow rate that is an increasing function ...  
WO/2019/172372A1
Provided is a fuel supply control device (F, F1) in which a parallel flow passageway of an orifice (8) and a pressurizing valve (7) is used as a complex pressurizing valve for a fuel supply amount, and which controls a fuel supply pump (...  
WO/2019/166214A1
The gas turbine comprising a plurality of combustors for igniting gas. The method comprising receiving first temperature measurements for a first plurality of probing points, each associated with one of the plurality of combustors (S0). ...  
WO/2019/162167A1
A controller (700) for a gas turbine (100) is described. The gas turbine (100) comprises the compressor (101) arranged to operate at a rotational speed n, the combustor (102) and the fuel supply means (127) comprising the first fuel supp...  
WO/2019/164475A1
A method for starting up a gas turbine engine of a combined cycle power plant The invention relates to a method for starting up a gas turbine engine (4) of a combined cycle power plant (2). In order to enable starting up a gas turbine en...  
WO/2019/162168A1
A controller (600) for a gas turbine (100) is described. The gas turbine (100) comprises the compressor (101) arranged to operate at a rotational speed n, the combustor (102) and the fuel supply means (127) comprising the first fuel supp...  
WO/2019/158323A1
The invention relates to a method for operating a burner arrangement (16) of a heat engine, particularly a gas turbine, comprising a plurality of burners (2), each one having at least one pilot burner (6) and at least one main burner (8)...  
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 ...  

Matches 1 - 50 out of 8,840