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WO/2020/115405A1 |
The method for detecting a rotating stall comprises; - a step (E90, E100) of determining a level of variation of a static pressure in a combustion chamber of the turbojet engine around an average value of this static pressure; - a step (...
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WO/2020/114045A1 |
An ignition method and ignition apparatus for a gas turbine. The ignition method comprises: a first ignition apparatus (3) is started, a liquid fuel introduced into a combustion chamber (2) is vaporized by heating and ignited, a fuel gas...
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WO/2020/099779A1 |
The present invention relates to a fuel metering unit (120) for an aircraft engine, comprising: - a metering member (125) configured to receive a position control signal and to meter the feed of fuel to the engine depending on said posit...
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WO/2020/095955A1 |
A gas turbine system (S) comprises: a gas turbine engine body (GT) that has a compressor (1) for compressing air, a combustor (3) for mixing fuel into the air that has been compressed at the compressor (1) and causing same to combust, an...
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WO/2020/095593A1 |
This control device is provided with a load fuel quantity calculation unit (111), an allowable fuel quantity calculation unit (120), a flow rate low value selection unit (131), a basic drive quantity calculation unit (141), a fuel deviat...
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WO/2020/093264A1 |
A design method for optimizing an aero-engine transition state control law. The SQP algorithm is adopted for optimizing the transition state of an engine, and the transition state control law design under the constraint boundary conditio...
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WO/2020/089555A1 |
The invention relates to a device for monitoring the lifetime of at least one hydraulic apparatus of an aircraft that is subject to variations in hydraulic pressure during flight, comprising an interface for receiving measurement data wh...
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WO/2020/078720A1 |
A method for controlling a turbomachine (T) comprising an electric motor (ME) forming a torque injection device on a high-pressure rotation shaft (22), in which method a fuel flow setpoint QCMD and a torque setpoint TRQCMD provided at th...
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WO/2020/081135A1 |
The present disclosure describes a fuel system for an engine. The fuel system includes a fuel metering valve, a flow measuring system, and a controller in communication with the fuel metering valve and the flow measuring system. The fuel...
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WO/2020/078921A1 |
A pump having a sensor for detecting output pressure of the pump and a controller for controlling a speed of the pump depending on the detected output pressure, wherein the controller is arranged to control the speed of the pump so as to...
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WO/2020/079413A1 |
A pump has a sensor for detecting output pressure of the pump and a controller for controlling a speed of the pump depending on the detected output pressure. The controller is arranged to control the speed of the pump so as to maintain t...
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WO/2020/052698A1 |
The invention relates to an interface assembly (30) for a power unit controller (40) of a power unit (100), in particular of an aircraft- and/or gas turbine power unit, comprising a memory (42) for storing at least one controller variabl...
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WO/2020/049262A1 |
The invention relates to a device (30) for cooling heat-sensitive control members (29) of a pneumatic or electropneumatic valve (20), comprising a containment casing (31) designed to contain said control members (29); a fresh air inlet (...
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WO/2020/048744A1 |
The invention relates to a method for reducing the residual energy of an electricity-generating machine (3) of a power plant (1) in the event of a sudden load drop, the machine (3) having at least one turbine (4), which has a turbine con...
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WO/2020/048252A1 |
A fuel oil pump control circuit and method. The circuit comprises a locomotive microcomputer control circuit (101), a fuel oil pressure sensor (102), a switch control circuit (103), and a diesel engine electric injection control circuit ...
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WO/2020/043977A1 |
A duct for evacuating hot air (4) from an aircraft engine is extended by a movable stack (13) that can project from the wall (1) such that the hot air is ejected a distance from the wall (1) without risk of damaging the wall. The stack (...
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WO/2020/040637A1 |
A fuel/air supply device (19) comprises a fuel supply arrangement (12) designed to convey fuel to a fuel outlet of the fuel/air supply device (19), a primary air supply arrangement (11 ) designed to convey air to an air outlet of the fue...
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WO/2020/031715A1 |
Provided is a combined cycle power plant configured so that the time until vapor is produced by the low-pressure heat exchanger of a waste heat recovery boiler can be reduced. This combined cycle power plant is provided with: a waste hea...
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WO/2020/030363A1 |
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...
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WO/2020/023028A1 |
An analytic tool (10) useful in predicting drive-train over-speed under a large number of different loss of load scenarios, as well as under a number of different engine and drive- train configurations, is provided. The tool and its asso...
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WO/2020/011426A1 |
The invention relates to a method for operating a gas turbine plant with gaseous fuel, which is conveyed to the gas turbine plant through a gas line (6), burnt in a combustion chamber (4) and then supplied to a gas turbine. At least one ...
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WO/2020/007847A1 |
A turbomachine for an aircraft extending axially along an axis X comprising a primary flow path in which an air stream flows intended for the combustion chamber (102) and a secondary flow path in which an air stream flows intended for pr...
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WO/2019/243371A1 |
A control system (50) for a turbopropeller engine (2) of an aircraft (1) having a gas turbine (11) and a propeller assembly (3) coupled to the gas turbine (11), the gas turbine (11) having a compressor (12) coupled to an air intake (13) ...
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WO/2019/245549A1 |
A locking assembly for locking a first attachment member to a second attachment member is provided. The first attachment member and the second attachment member are operable to connect a first rotatable guide vane and a second rotatable ...
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WO/2019/239112A1 |
A combustion engine (10) comprises a radial compressor (16) in flow communication via a flow passage (22) with a compressor-combustor array (20) radially outward of the radial compressor (16), both rotatable around a central axis (12). T...
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WO/2019/234368A1 |
The invention relates to an aircraft propulsion system, comprising a main transmission unit (12) and at least two turbojet engines connected to the main transmission unit (12), respectively a first turbojet engine (14a) and a second turb...
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WO/2019/236062A1 |
An arrangement of a last stage of rotating blades and stationary vanes of a turbomachine (10) is provided. The arrangement includes a last stage of rotating blades (60) mounted to a rotor (50), the rotor coaxial with a turbine casing (20...
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WO/2019/222271A1 |
Embodiments described herein are directed to regulating pressure and/or fluid flow within a system. In one scenario, a system for regulating pressure includes a controller, a pneumatic pressure regulator with a dome that adjusts pressure...
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WO/2019/221727A1 |
Outboard-transverse flame migration in an annular profile combustion gas pathway (22) of an aeroderivative turbine engine (10) is detected with a dual-immersion thermocouple probe (32). A first thermocouple (34) in the probe is oriented ...
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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 ...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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...
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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 ...
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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 ...
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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 (...
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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). ...
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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...
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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...
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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...
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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)...
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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...
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