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WO/2021/200702A1 |
This early sign detection device comprises: a plurality of sensors; a data acquisition unit for acquiring the time-series change data of a physical quantity from the plurality of sensors; a calculation unit for calculating, from the time...
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WO/2021/200818A1 |
This control device adjusts the amount of fuel on the basis of the rotation speed of a gas turbine such that the frequency of power output by a power generator that generates power using the gas turbine is within a fixed range. The contr...
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WO/2021/200194A1 |
This control device controls a gas turbine. The control device is provided with: a predicting unit configured to use a prediction model to predict a future state quantity of the gas turbine in response to a control input to the gas turbi...
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WO/2021/188538A1 |
A maritime sulfur dioxide emissions switch monitoring system has an emissions sampling apparatus that is self-powered and requires a low power for operation. The emissions sampling apparatus has sensitive and selective chemical sensing t...
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WO/2021/186256A1 |
Disclosed is a system including a turbine having a plurality of spokes. The first spoke end is coupled to a shaft and the second spoke end is coupled to a blade of a plurality of blades. Each blade is a cup with an open surface. A dispen...
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WO/2021/181027A1 |
The invention relates to a method for controlling a turbomachine (T) comprising a gas generator, the turbomachine comprising an electric machine (ME) forming a torque injection/removal device on one of the low-pressure/high-pressure rota...
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WO/2020/208318A9 |
The invention concerns a hybrid propulsion installation (100) for an aircraft, comprising: an internal combustion engine comprising at least one combustion chamber (114); at least one electricity generator (134a, 134n); an electrical pro...
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WO/2021/174326A1 |
The technology herein relates to aircraft auxiliary power unit (APU) control systems, and more particularly to APU control methods and systems for defining steady state speed of an APU according to aircraft operating conditions. More par...
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WO/2021/170947A1 |
The invention relates to a combustion assembly for a gas turbine, comprising a flame tube (14) and fuel supply means having a flow limiter (18) which supplies an injector (19), the flow limiter (18) and the fuel injector (19) being forme...
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WO/2021/164549A1 |
An electric energy-driven jet aircraft engine, comprising a jet core engine (3) comprising a gas compressor (31) and an accelerator (32) which are sequentially arranged in a gas inlet direction, wherein the gas compressor (31) is used fo...
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WO/2021/152230A1 |
The invention relates to a fuel supply circuit of an aircraft engine, comprising a centrifugal pump which is mechanically coupled to a drive shaft (18) delivering a mechanical power. The circuit further comprises at least one electromagn...
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WO/2021/148731A1 |
An aspect of the invention relates to a method for monitoring a starting sequence of a turbomachine comprising a compressor provided with a rotor, a starter capable of rotating the rotor and a combustion chamber, the method comprising th...
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WO/2021/139004A1 |
Disclosed is a turbofan engine direct data driving control method based on an adaptive boosting algorithm. The method comprises: firstly, designing a turbofan engine controller on the basis of a least squares support vector machine algor...
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WO/2021/136910A1 |
A device (17) for identifying a configuration of a kinematic chain connected to an actuator of a stage of a turbine of an aircraft, comprising a command module (18) capable of commanding a manoeuvre of the actuator, a module (20) for rec...
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WO/2021/136911A1 |
A system (36) for controlling an aircraft thrust reversal means comprises a reverse idle control means (38), a first detection means (31) configured to detect, when the reverse idle control is active, a condition for activation of the th...
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WO/2021/134887A1 |
A variable cycle engine intelligent control method based on a dynamic neural network. By means of adding a structural adjustment algorithm based on a gray relational analysis method to a neural network training algorithm, adjusting the s...
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WO/2021/123146A1 |
The invention relates to a turbomachine compressor module (47), comprising an annular row of structural arms (46) defining inter-arm spaces (56) between two circumferentially adjacent arms (46, 48); and an annular row of stator vanes (39...
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WO/2021/116558A1 |
In an electromechanical actuation chain for controlling the movement of moving loads (22) of an aeronautical turbomachine from a control unit (24), one or more of these moving loads being actuated by an electromechanical actuator (30), p...
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WO/2021/097696A1 |
An adaptive dynamic programming (ADP) method for an aero-engine in optimal acceleration tracking control, relating to the field of aero-engine control. Firstly, according to the operating state of an aero-engine, a nonlinear dynamical mo...
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WO/2021/094667A1 |
The invention relates to a device and method for managing a fleet of information-communicating devices that are able to be reversibly fastened to aircraft turbomachines, comprising: associating (S02) one device of said fleet of devices w...
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WO/2021/091702A1 |
Systems and methods include an AC motor (44) and one or more gas turbine generators (48) configured to provide electrical power to the AC motor. The system also includes a controller (38) configured to control operation of the one or mor...
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WO/2021/086715A1 |
Method and system for transitioning from a first liquid fuel supplied to a combustor of a gas turbine system to a second liquid fuel supplied to the combustor utilizing a fuel pump configured to supply both fuels from the fuel pump durin...
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WO/2021/074531A1 |
Disclosed is a method for quickly stopping the propulsion rotor of a helicopter after landing, comprising, following a request (100) by a pilot of the helicopter to quickly stop the engine, the following steps managed by the control unit...
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WO/2021/071643A1 |
A method and control system for controlling shaft speed for a gas turbine engine (100) is disclosed. The power output of a gas turbine engine (100) can vary and be below desired output levels due to operating conditions such as ambient t...
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WO/2021/069824A1 |
The invention relates to an apparatus for monitoring over time the state of an aircraft propulsion engine, characterised by a module (ACQ) for capturing flight (Vi) data (DVi) from the engine, the data comprising input values (E1i)...
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WO/2021/052759A1 |
The invention relates to an exhaust turbine, having: - a turbine wheel (7) having a plurality of rotor blades (8); - an exhaust outlet duct (12), which is arranged downstream of the rotor blades of the turbine wheel, wherein the exhaust ...
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WO/2021/054861A1 |
The invention relates to a method for controlling a thrust reverser of a gas turbine engine during aircraft braking in the case of landing or aborted takeoff. The method consists in: identifying aircraft touchdown on the basis of the pre...
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WO/2021/045646A1 |
The invention relates to the field of aircraft engineering. The present autonomous integrated device for collecting, recording and monitoring the parameters of an aircraft gas turbine engine comprises an engine parameter recording unit w...
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WO/2021/042260A1 |
A method for controlling a dry gas seal booster pump (100), including: determining whether a condition for starting the dry gas seal booster pump (100) is satisfied (S210); determining whether a condition for stopping the dry gas seal bo...
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WO/2021/038604A1 |
A two-gas shaft turbine control system (31) is disclosed. The gas turbine control system comprises a fuel controller (35), which receives a speed error signal, indicating whether the low-pressure turbine wheel (11) of the gas turbine (1)...
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WO/2021/039927A1 |
This gas turbine engine is provided with: a fan that is disposed on the front of a compressor and that rotates in conjunction with the rotational shaft; a casing that includes an inner shell having accommodated therein a compressor, a co...
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WO/2021/038161A1 |
A bellcrank (30) for a variable adjustment device for an aircraft turbomachine, this bellcrank being articulated respectively to a control housing (12), to a synchronization bar (9), to a piston stem (11) of an actuator (A) and to a turn...
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WO/2021/033559A1 |
This combustion control device is a combustion control device for a gas turbine in which compressed air is supplied to a combustor, said compressed air being from a compressor and having flowed into a casing. The combustion control devic...
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WO/2021/027093A1 |
An active fault-tolerant control method for a turbofan engine control system. A linear variable parameter gain scheduling robust tracking controller with good dynamic performance is designed. According to the change in the operation stat...
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WO/2021/028199A1 |
Method for computer-implemented determination of control parameters of a turbine The invention describes a method for computer-implemented determination of control parameters (CP) of a turbine (T1,...,Tn) by consideration of component-re...
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WO/2021/018524A1 |
The system for controlling the idling and power take-off speed has a unit (4) for determining a current value of available power, a unit (5) for determining a current value of consumed power, a unit (6) for determining a value of power v...
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WO/2021/013957A1 |
The invention relates to an axial turbine engine comprising a compression device with a rectifier stage having variable orientation vanes (24); a combustion chamber downstream of the compression device; a turbine device downstream of the...
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WO/2021/001527A1 |
The present invention relates to a propulsion assembly for an aircraft, comprising a coupled-turbine turbomachine comprising a combustion chamber and a shaft that is mounted so as to rotate and is designed to rotate at a turbomachine rot...
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WO/2021/001563A1 |
The invention relates to a method for metering fuel in a fuel supply circuit of an aircraft engine, the circuit comprising a metering device for a fuel circuit of an aircraft engine comprising, downstream of a fuel pumping system and ups...
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WO/2020/248184A1 |
An aircraft engine actuator fault-orientated disturbance-free switch-in fault-tolerant control method. With regard to the problem that, when an actuator fault occurs in an aircraft engine, using a virtual actuator-based active fault-tole...
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WO/2020/247842A1 |
A fuel system for a generating unit disposed within an enclosure, the enclosure having an enclosure width and an enclosure height, includes a bulk fuel storage tank and a vertical day tank, a supply line and a return line. The vertical d...
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WO/2020/241543A1 |
In this gas turbine, this method for controlling the same, and this combined cycle plant, provided are: a compressor (11) which compresses air (A); a combustor (12) which mixes and burns fuel (F) and compressed air (CA) compressed by the...
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WO/2020/242556A1 |
A water delivery system (18) for delivering water for injection into gas turbine engine combustor (4) includes a centrifugal pump (19) and a metering valve (23). The centrifugal pump (19) has an inlet (20) connected to a water source and...
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WO/2020/240117A1 |
The invention relates to a fuel supply system of a turbomachine, comprising a fuel circuit having a pressurizing means (202) at the outlet (3) of said circuit, a pump (1) arranged to send a flow of fuel into said circuit, and a flow sens...
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WO/2020/229655A1 |
The invention relates to a method for estimating a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint closing signal of the flap...
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WO/2020/229651A1 |
The invention relates to a method for estimating and using a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint signal for closi...
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WO/2020/229305A1 |
The invention concerns an airflow arrangement for a gas turbine engine in which air can be selectively directed to and from a bypass channel of the engine and into a duct communicating air into a compressor of a gas turbine engine.
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WO/2020/230485A1 |
This fuel gas supply device and method comprises: a fuel gas supply line (L3) that connects a fuel gas supply source (100) and a combustor (12); a fuel gas compressor (24) that is provided to the fuel gas supply line (L3) and compresses ...
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WO/2020/230531A1 |
The present invention provides: a burner for a gas turbine in which the occurrence of large-scale vortices is controlled, whereby combustion oscillation is suppressed; and a method for controlling combustion in the burner. A burner for...
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WO/2020/223079A1 |
Systems, methods, and computer readable medium are provided for determining interferometric data and spectral data associated with combustion conditions of a flame in a combustion chamber using a sensor head including a first vacuum cavi...
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