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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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WO/2018/089057A9 |
A method of preventing standing waves in an installed gas turbine having a fan, having a fan speed, and a compressor, having a compressor speed, includes correcting the fan and compressor speeds for temperature and monitoring the correct...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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...
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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...
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WO/2018/140150A1 |
A turbine engine includes, in a serial flow relationship, an axially oriented compressor, a combustion section, a turbine section, and an exhaust section. An air flowpath extends from an inlet duct to the exhaust section such that the co...
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WO/2018/140130A2 |
The turbine includes a first turbine rotor disc, a second turbine rotor disc, a first source of cooling fluid, and a first cooling fluid conduit. The first turbine rotor disc has a first outer circumference and a first plurality of blade...
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WO/2018/138456A1 |
The invention relates to a system for supplying fuel to a turbomachine, comprising: a pump (1); a hydromechanical group (2'); a drive device (6') arranged so as to drive the pump (1); and a branch comprising actuators for controlling var...
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WO/2018/140138A1 |
A gas turbine engine includes a compressor section defining a compressor exit temperature, T3. The gas turbine engine also includes a combustion section and a turbine section, with the turbine section defining a turbine inlet temperature...
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WO/2018/138454A1 |
The invention relates to a system for supplying fuel to a turbomachine, comprising a fuel circuit comprising a pressurisation means (202) at the outlet (3) of said system, and a pump (1). The circuit comprises a flow rate sensor (201) ar...
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WO/2018/138428A1 |
The invention relates to a transmission device (6) for driving a fuel pump (1) for a turbomachine using a drive shaft of said turbomachine, said transmission comprising a planet reduction gearing (11) comprising three elements, a central...
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WO/2018/134378A1 |
In a fuel control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4) : a main fuel regulator (12) determines a demand (Wfdem) of fuel flow (Wf) to be introduced in the ga...
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WO/2018/134379A1 |
A control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4), is provided with: a control unit (12) to control a forward operating mode or a reverse operating mode of the...
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WO/2018/136291A1 |
A method of monitoring a turbomachinery is disclosed herein. The method includes measuring the pressure drop across the intake filter (66). The method further includes determining clog rate parameters for a clog rate of a filter area of ...
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WO/2018/131654A1 |
This control system regulates the flow rate of heating water supplied to a fuel heating device which heats gas turbine fuel, to control the temperature of the fuel supplied to a combustor of a gas turbine via the fuel heating device. The...
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WO/2018/128684A2 |
A turbine engine including a core engine cowl including a compartment, and a cooling system positioned within the compartment. The cooling system includes a cooling fan configured to exhaust heat from the compartment, a temperature senso...
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WO/2018/116975A1 |
The present invention provides a plurality of main nozzles (34) of a combustor, the main nozzles (34) being provided spaced apart in a circumferential direction on an outer circumferential side of a pilot nozzle. The main nozzles (34) ea...
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WO/2018/111479A1 |
A system is provided comprising a memory configured to store instructions and a processor configured to execute the instructions. The processor is configured to execute the instructions to receive sensor data comprising sensed operations...
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WO/2018/110477A1 |
Disclosed is a gas turbine engine (1) that combusts, with a combustor (3), compressed air (CA) compressed by a compressor (2), and drives a turbine (5) by a high-temperature, high-pressure combustion gas (G) which has been generated, the...
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WO/2018/111665A1 |
In one aspect, a power generation system may include a core turbine engine, an electric generator, an electric motor, and an auxiliary compressor. The core turbine engine defines an axial direction, and may include a compressor and a tur...
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WO/2018/110476A1 |
Disclosed is a gas turbine engine (1) that combusts, with a combustor (3), compressed air (CA) compressed by a compressor (2), and drives a turbine (5) by a high-temperature, high-pressure combustion gas (G) which has been generated, the...
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WO/2018/112321A1 |
The subject matter of this specification can be embodied in, among other things, an identification system includes a first component having a first resistor and a second resistor, a second component having a sensor configured to sense a ...
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WO/2018/110696A1 |
According to the present invention, a first fuel flowrate command value indicating the command value CSO of a fuel input amount is calculated so as to match, with a target output, the output of a gas turbine. The upper limit value of the...
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WO/2018/089458A1 |
A first cooling stage is fluidly coupled to a bleed port of a compressor to receive and cool bleed air with the air stream to produce a cool bleed air. A cooling pump receives and increase a pressure of the cool bleed air to produce a pr...
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WO/2018/088184A1 |
The gas turbine plant is provided with a gas turbine (10), a heating device (60), a decomposition gas line (70), and a decomposition gas compressor (85). The heating device (60) heats ammonia so that the ammonia is pyrolyzed and decompos...
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WO/2018/084902A1 |
A turbofan engine includes a core (30); and a low-pressure turbine (22) configured to drive a fan (46) to produce a fan flow that exits the engine without passing through a turbine. The fan includes a rotor having at least one rotor stag...
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WO/2018/076050A1 |
A multi-stage axial turbine (typically between 4 and 10 stages) designed to operate more efficiently with partial admission of low temperature steam in each stage except the last one or two stages. Each stage of the subject turbine opera...
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WO/2018/059804A1 |
The invention is related to a gas turbine arrangement for at least dual fuel operation, comprising a plurality of fuel manifolds (21,22,23), each connected to each of at least one combustor (12) and a control system (17). A first manifol...
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WO/2018/060030A1 |
A rotating device for a compressor of a gas turbine is presented. The rotating device, connectible with the compressor, includes a first shaft, a second shaft, rotatable blades, a bearing assembly, an external drive and an input port for...
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WO/2018/059798A1 |
The invention is directed to a method for controlling a power plant (1), the power plant (1) at least comprising a gas turbine engine (5) and a generator (3). The generator (3) is initially driven by the gas turbine engine (5) in a gener...
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WO/2018/059885A1 |
A rotating device for a compressor of a gas turbine is presented. The rotating device, connectible within the compressor, includes a first shaft, a second shaft, rotatable blades, a bearing assembly, an energizable drive and an input por...
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WO/2018/063575A1 |
A system for an aircraft having a first gas turbine engine and a second gas turbine engine includes a first engine controller comprising a first motion sensor. The first motion sensor defines a first orthogonal coordinate system, and is ...
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WO/2018/054613A1 |
The invention relates to a method for detecting damage during the operation of a gas turbine, comprising the following steps: calculating an average value (Tavg,k) of individual temperature measurement values (Ti,k) over a defined sampli...
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WO/2018/055825A1 |
A performance estimation device according to one aspect of the present disclosure outputs, on the basis of a control input value for controlling a target device and a sensor measurement value measured by a sensor disposed in the target d...
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WO/2018/050964A1 |
The gas turbine comprises a compressor (10), a combustor (20), and a turbine (30). The method comprises: compressing air with the compressor and feeding compressed air continuously to the combustor, feeding fuel to the combustor, continu...
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