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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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WO/2018/038875A1 |
A method and aircraft for providing bleed air to environmental control systems of an aircraft using a gas turbine engine, including determining a bleed air demand for the environmental control systems, selectively supplying low pressure ...
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WO/2018/016623A1 |
This twin-shaft gas turbine facility is provided with: a twin-shaft gas turbine (10); an induction motor (22) coupled to a compressor (11) of the twin-shaft gas turbine (10); a secondary battery (23); a first frequency converter (24) whi...
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WO/2018/017176A1 |
Systems and methods for shutting down a gas turbine engine in response to a severe mechanical failure include determining a rate of change of one or more process conditions. If the rate of change of the one or more process conditions exc...
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WO/2018/012100A1 |
A gas turbine equipped with: a low-pressure bleed passage (41), a medium-pressure bleed passage (42), and a high-pressure bleed-passage (43) for supplying compressed air bled from respective bleed chambers (25a, 25b, and 25c) to a turbin...
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WO/2018/009192A1 |
A distribution method for a gas turbine engine distributes fuel based on a calculated ratio of air flow burnt to total air flow through all combustion zones in the gas turbine engine. This ratio is used to achieve a predetermined flame t...
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WO/2018/007464A1 |
Method for controlling steam admission into a steam turbine (1), the turbine (1) comprising a high pressure casing (2), at least one reduced pressure casing (3, 4, 5, 6) and an admission steam control system (13), the high pressure casin...
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WO/2018/009668A1 |
A fuel gas blending system for internal combustion engines combines two or more gas streams to achieve a blended fuel gas having a suitable heating value (HV) for a given engine. A relatively high HV gas, for example gas produced from an...
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WO/2018/005217A1 |
Providing wear-related prognostics and diagnostics on a turbine engine includes, while operating a turbine control device, tracking a total device travel distance over time by recurrently: selectively identifying actual device movement b...
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WO/2018/002511A1 |
The invention relates to a circuit for metering fuel (1) for a turbomachine, comprising: - a fuel metering element (20), – a pump (10) designed to pump a flow of fuel to the metering element, and – a control valve (30) designed to re...
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WO/2017/221923A1 |
A method for predicting the turbine outlet temperature of a gas turbine during future use on the basis of past usage records for the gas turbine, wherein parameters for environment/operation conditions scheduled for future use and a fan ...
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WO/2017/213816A1 |
A gas turbine engine and method of operation are provided. The gas turbine engine may include a variable geometry component operably driven by a component actuator. The component actuator may be in fluid communication with a primary line...
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WO/2017/206084A1 |
The invention discloses a regenerative cycle gas turbine system and a combined cooling heating and power system. The regenerative cycle gas turbine system comprises an air compressor, an air regenerator, a combustion chamber, a turbine, ...
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WO/2017/204779A1 |
A gas turbine (100) and a method for operating a gas turbine (100) having a fuel gas monitoring system (200) are presented. The fuel gas monitoring system (200) provides a measurement of a parameter of a fuel gas (150) in real time. An o...
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WO/2017/198528A1 |
It is described a system (100) for controlling a gas turbine (105), comprising: a control system (101) for providing control signals (103) to a gas turbine (105); a tuning system (107) for providing tuning signals (109), a modelling syst...
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WO/2017/196293A1 |
The present disclosure provides a method for predicting a fluid type, comprising sensing, by a first sensor, mass flow data of a fluid in an engine, wherein the first sensor operates based on a first fluid property; sensing, by a second ...
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WO/2017/195094A1 |
A mixed flow turbine (1) for the expansion phase of steam thermodynamic cycles of an organic Rankine cycle provided with a first section (A) in which a first expansion of a main flow of working fluid takes place, in a substantially radia...
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WO/2017/189566A2 |
A large frame heavy duty industrial gas turbine engine that produces twice the power as conventional single spool industrial engines and operates at full power during a hot day. The engine includes a high spool directly driving an electr...
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WO/2017/188052A1 |
The integrated gasification combined cycle power generation plant comprises: a gasification furnace; a gas turbine which is configured to be drivable by using combustible gas generated by the gasification furnace as fuel; a flow rate con...
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WO/2017/189440A1 |
An industrial gas turbine engine with a high spool and a low spool in which low pressure compressed air is supplied to the high pressure compressor, and where a portion of the low pressure compressed air is bled off for use as cooling ai...
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WO/2017/170227A1 |
Provided is a combustor equipped with: a nozzle main body (16) having a shaft body (24) extending along an axial line, and swirl blades (26) that extend from the outer circumferential surface of the shaft body (24) in the radial directio...
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WO/2017/170209A1 |
Provided is a gas turbine in which a first nozzle (1) comprises first nozzle inner diameter-side fuel injection holes (13) for injecting a first nozzle fuel and first nozzle outer diameter-side fuel injection holes (14) that are for inje...
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