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WO/2020/221700A1 |
Embodiments of the invention are shown in the figures, where a method for manufacturing a gearbox, the method comprising: providing a predefined interval around an integer; providing a gearbox setup; determining a speed ratio of at least...
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WO/2020/219007A1 |
A method and system is provided of controlling a pump having a pumping element comprising: determining, by a controller, a suspension of one or more fuel delivery events for a pumping element of the at least one pumping element; subseque...
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WO/2020/216639A1 |
Method for regulating a turbomachine (10) comprising a temporary power-increasing device (26), said regulating method comprising a step (E3) in which the injected refrigerant fluid flow rate is adjusted as a function of the atmospheric p...
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WO/2020/201652A1 |
The invention concerns a method for monitoring at least one aircraft engine, said method comprising an acquisition (100) depending on first and second sets of measurements of respectively endogenous and exogenous variables. The method al...
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WO/2020/200853A1 |
A method for controlling a non-propulsive power generation turbine engine (T) configured to supply power to a plurality of propulsion rotors (R1-R4) of an aircraft, each propulsion rotor (R1-R4) being connected to a power distribution mo...
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WO/2020/201292A1 |
Ducting (10) is described. The ducting is for use with: a high pressure turbocharger (HPT) having a HPT exhaust gas outlet, and a low pressure turbocharger (LPT) having an LPT exhaust gas inlet. The ducting (10) comprises first and secon...
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WO/2020/193919A1 |
Method for controlling a first, a second and a third variable of a turbomachine as a function of a first, a second and a third turbomachine control quantity, each of which can become saturated as a function of the turbomachine operating ...
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WO/2020/193148A1 |
Machine control based on automated learning of subordinate control skills For controlling a machine (100) according to multiple control objectives, a device (200) provides multiple subordinate control skills (221, 222, 223, 224, 225), ea...
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WO/2020/188000A1 |
The invention concerns a bypass turbomachine (1) with a primary flow path and a secondary flow path, comprising: - a low-pressure body comprising a low-pressure compressor (120) connected to a low-pressure turbine (122) via a low-pressur...
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WO/2020/188177A1 |
The invention relates to a method for regulating a temperature of the exhaust gases of a turbomachine (1), the method comprising the following steps: - regulating the injection of fuel into a combustion chamber (5) of the turbomachine (1...
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WO/2020/188059A1 |
The present invention relates to a method for monitoring the operating state of a hydromechanical unit (100) of an aircraft turbomachine, comprising: a metering valve (130) comprising a mobile metering part (138), a regulating valve (140...
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WO/2020/169897A1 |
Method for controlling a fuel-metering device with a mobile metering element, comprising at least two iterations of the following steps: - detecting (E1) a potential change in operational status of one of two metering-element position se...
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WO/2020/128038A9 |
A gas turbine engine comprising at least one radially extending bleed passage in fluid communication with at least one generally circumferentially extending plenum. A plenum has an upstream end in fluid communication with a bleed passage...
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WO/2020/165790A1 |
A cooling system for cooling hot components of a radial or axial gas turbine engine, which includes a recuperator heat exchanger, provides engine cooling without loss of thermal efficiency. Air flow leaving a compressor is split between ...
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WO/2020/162076A1 |
This fuel supply control device (10) is a fuel supply control device that generates an operation amount for feedback control of the rotation of a gear pump (3) on the basis of a deviation of a detected fuel flow rate with respect to a ta...
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WO/2020/154259A1 |
Disclosed techniques include energy management using a converged infrastructure. Access to one or more fluid-based energy storage and generation assemblies is obtained, where each assembly comprises a pump-turbine and a pressure vessel. ...
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WO/2020/152425A1 |
The invention concerns a method for monitoring the operating state of a system for positioning variable-geometry members (18) of a turbomachine (10), the members (18) being configured to travel over an operating area comprising a first p...
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WO/2020/142984A1 |
Provided is an active fault tolerant control method of an aero-engine based on error interval observer, which belongs to the field of aviation control technology, including tracking the reference model status and output by the aero-engin...
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WO/2020/126848A1 |
The invention relates in particular to a power plant assembly, comprising - a turbine (TT) for driving at least one rotor shaft (RS); - a combustion chamber (76) for generating drive energy for the turbine (TT); - at least one electric m...
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WO/2020/130990A2 |
The present invention relates to a range extender system (1) with a micro gas turbine, in which compressor (4) and turbine (9) are located on separate shafts and, compressor (4) is driven (operated) by compressor motor (3) that is a sepa...
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WO/2020/128286A1 |
The invention relates to a system and method for controlling an aircraft turbine engine. According to the invention, the control system (100) comprises: - a nominal-mode processing chain (110) comprising a global corrector (21) designed ...
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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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