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WO/2022/117938A1 |
The invention relates to a fan blade (3) made of composite material the fibrous reinforcement of which comprises first strands (12) having a first stiffness, second strands (13) having a second stiffness and third strands (14) having a t...
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WO/2022/106780A1 |
The invention relates to a part (10) made of composite material, in particular for an aircraft turbine engine, comprising: - a body (40) produced from fibres (41) woven in three dimensions and immersed in a resin, in particular an organi...
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WO/2022/100891A1 |
The invention relates to an aircraft comprising a display screen (7) and at least one turbomachine (2), each turbomachine (2) comprising a motor (10), the aircraft (1) comprising the following elements associated with each turbomachine (...
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WO/2022/102556A1 |
This monitoring device for a rotary machine is for monitoring a clearance in the rotary machine including a casing that receives a rotating part and a stationary part therein, and comprises: at least one position sensor which is provided...
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WO/2022/101029A1 |
The invention relates to a guide vane wheel (4) of a turbomachine, having a plurality of guide vanes (41), which form a vane row (42) and are designed to extend radially inwards in a flow path (6) of the turbomachine, and two boroscope a...
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WO/2022/102835A1 |
In a directional control hydraulic valve and a hydraulic system including same according to the present invention, the directional control hydraulic valve comprises: a first valve configured to control a flow of a fluid flowing in from a...
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WO/2022/094564A1 |
A method for determining mass differential in a hot gas path component of a gas turbine (13) includes monitoring operational conditions of the gas turbine (13); determining whether changes in a gas turbine (13) wheel space (51) temperatu...
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WO/2022/087617A1 |
A method for is provided. The method can include receiving data characterizing a first measurement image having a first state and a first set of three-dimensional coordinate data corresponding to the first measurement image. The first me...
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WO/2022/084615A1 |
The present invention relates to a blade (3) of a fan (1), made of composite material, of a turbomachine. On a portion (15) of the blade (7) which extends from a lower limit (16) located at a predetermined distance (d) from the shank (6)...
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WO/2022/064160A1 |
The invention relates to an aircraft turbine engine (10) with main axis A, comprising: an arm (18) that is radial with respect to the main axis A, extending through an air flow duct (14); a support wall (22) belonging to the radial arm (...
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WO/2022/053753A1 |
The present invention relates to a fan blade (1) of a turbomachine comprising a structure made of composite material comprising a fibrous reinforcement (4) obtained by three-dimensional weaving of strands (12, 14) and a matrix in which t...
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WO/2022/051586A1 |
A supercritical CO2 turbo-generator system is disclosed. The turbo-generator system comprises: a plurality of turbine generator units (200A-200C), a direct current bus (410), a plurality of active rectifiers (290A-290C), and a voltage co...
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WO/2021/257076A1 |
A rotor blade locking key system includes a rotor blade for a turbine engine having an airfoil and a root, a disc having a circumferentially extending groove for receiving the root, a locking key, and a data collection system coupled to ...
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WO/2021/255371A1 |
This electromechanical installation (100) for an aircraft comprises: - an electrical network (102) comprising electrical subnetworks (104, 106); - a turbogenerator (118) comprising a gas turbine (120), an electricity generator (122) with...
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WO/2021/233640A1 |
The invention relates to a method for operating a gas turbine at a high temperature and a gas turbine assembly. In the method, after operation with an operating temperature above 1000°C, a gas turbine (1) having a structural material (2...
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WO/2021/198602A1 |
The invention relates to an assembly (22) for an aircraft turbine engine, comprising a fan drive reduction gear (20) and a lubrication system (24) comprising: - a reduction gear housing (31a); - a lubricant tank (26); - a lubricant suppl...
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WO/2021/191529A1 |
The invention relates to a dynamic sealing device (220) for a measuring system (200) comprising a measuring probe (210) intended to pass through a first motor compartment (140) of a turbomachine and to measure a physical variable in a se...
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WO/2021/191559A1 |
The present invention relates to a turbomachine rotary-fan blade (2), comprising a body (20) made of a composite material, a metal reinforcement part (3) comprising a metal upstream nose (31), characterised in that the metal upstream nos...
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WO/2021/185524A1 |
The invention relates to a method for provisionally ensuring the functional capability of a housing of a machine in the event of damage to the housing, the housing having a housing upper part and a housing lower part, which are detachabl...
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WO/2021/181031A1 |
The invention relates to a fan module (100) for an aircraft turbomachine (10), comprising: - a fan (14) comprising a disc (32a) carrying fan blades (30), - a rotor (62a) of an electric machine (62), this rotor (62a) having an annular gen...
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WO/2021/176168A1 |
The invention relates to a method for refitting blade (10, 10a) shrouds (14a) of a rotor wheel in an aircraft turbomachine, the rotor wheel having a disc bearing blades (10; 10a) that each have an airfoil (26) extending between a root an...
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WO/2021/167735A1 |
An attachment device that includes an attachment body having a proximal end and a distal end configured to receive an applicator to mark a target. The attachment body further includes an engagement tab disposed between the proximal end a...
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WO/2021/160969A1 |
The present invention relates to a shaft (15) for a propulsion system (1) configured to rotate a reducing mechanism (12) about a rotational axis (X), the shaft (15) comprising: - a first end (16) configured to engage with an input gear (...
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WO/2021/160951A1 |
The invention relates to a fibrous texture (10) for forming the fibrous reinforcement of a vane of a turbine engine from composite material, comprising a zone (24) of reduced rigidity with warp threads made from second fibres having an e...
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WO/2021/160953A1 |
One aspect of the invention relates to a method for controlling a turbojet thrust reverser during an aborted aircraft takeoff, the thrust reverser comprising: - doors that can move between a closed position, an over-closed position and a...
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WO/2021/148743A1 |
Fan module (20) for an aircraft turbomachine testbed, this module comprising: - a drive shaft (22), - a fan (24) comprising a disc (26) and bearing blades (28) extending substantially radially outward from the disc, and - a thrust balanc...
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WO/2021/140292A1 |
Method for controlling a clearance between blade tips of an aircraft engine turbine rotor and a turbine shroud, which comprises estimating the clearance to be controlled and controlling a valve supplying a flow of air to the turbine shro...
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WO/2021/140301A1 |
The invention relates to an assembly for a turbomachine turbine (10) with longitudinal axis (A-A), comprising: - a turbine rotor disc (12) centred on the longitudinal axis, - a turbine shaft (14) centred on the longitudinal axis and rota...
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WO/2021/121457A1 |
The invention relates to a monitoring system (12) for a gas turbine (10), in particular for an aircraft engine. The monitoring system (12) comprises at least one borescope device (24) that is able to be mounted in a borescope opening (22...
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WO/2021/115511A1 |
The present invention relates to a method for detecting a first component (21.1) of a turbomachine (1), in which method - a first image (41) of the first component (21.1) is recorded (61); - on the basis of the first recorded image (41),...
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WO/2021/111093A1 |
Method for monitoring a turbomachine comprising a stator and a rotor, device, system, aircraft and computer program product. The method comprises a step of acquiring an input signal which represents a deformation of the stator or rotor o...
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WO/2021/113508A1 |
A method and system (600) of determining the location and size of a crack in a blade (200) includes measuring a time of arrival of a tip of the blade at an angular position in a rotation by means of one or more sensors (602), using the t...
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WO/2021/108057A1 |
A pressure capture canister (700) for a turbine engine is disclosed. The pressure capture canister (700) includes a body (720), a cap (730), and a seal (740). The cap (730) and the seal (740) are positioned within the body (720) and are ...
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WO/2021/094700A1 |
A modular and autonomous assembly (1) for detecting the angular position of the blades of an impeller intended to be mounted on a turbine engine, the assembly (1) comprising: - at least one electrical power source (711b, 71b, 72b) enabli...
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WO/2021/094533A2 |
The invention relates to a borescope (1), in particular for the borescopy of fuel chambers (58) of aircraft engines (50), and to an assembly (31) comprising a borescope (1). The borescope (1) comprises an electronic image capturing unit ...
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WO/2021/086208A1 |
A method and system for aligning a component within a turbine casing (100), and a related turbine casing, are disclosed. In a top-on position, a location of an optical target (140) and another, vertically spaced optical target (148) on t...
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WO/2021/080680A1 |
An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the com...
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WO/2021/080818A1 |
A control system for a power generation system includes a generator coupled to a turbine via a shaft. The control system includes a memory storing instructions. The control system also includes a processor coupled to the memory and confi...
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WO/2021/073984A1 |
The invention relates to a planetary gearbox (30) in a gas turbine engine (10), wherein a plurality of planetary gears (32) are each mounted on a planetary gear bearing journal (51) by a slide bearing (50), characterized in that a bushin...
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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/2021/067083A1 |
A traverse mechanism for measuring flow characteristics in a fluid flow path is provided. The traverse mechanism includes a rotating member configured to rotate 360 degrees about an axis in a circumferential direction. The traverse mecha...
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WO/2021/054585A1 |
The present invention relates to a Rankine cycle system having a liquid recirculation channel and a method for controlling the system and, more specifically, to a Rankine cycle system having a liquid recirculation channel, the Rankine cy...
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WO/2021/049093A1 |
Provided is an electro-hydraulic actuator system comprising an emergency shut-off circuit that has a simple configuration and operates stably. This electro-hydraulic actuator system comprises: a hydraulic cylinder 24 having a piston 25 t...
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WO/2021/038164A1 |
Method for producing an annular casing for an aircraft turbine engine, this casing comprising an annular body (12) made from a composite material based on a first resin, and a fire-resistant outer layer which covers an external annular s...
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WO/2021/038101A1 |
The invention relates to a method and system for detecting a functional failure in a power gearbox, in particular an epicyclic gearbox (30) in an aircraft gas turbine engine (10) comprising • a) measuring operational data (101) in the ...
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WO/2021/023947A1 |
The invention relates to a position sensor (18) for an aircraft nacelle thrust reverser door for an aircraft turbojet engine, comprising: - a target (26) to be detected; - a detector (24) having a detection range and comprising a detecti...
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WO/2021/011148A1 |
A control system (600) for a gas turbine engine (100) is disclosed. In embodiments, control system (600) includes a controller (610) and a high speed recorder (660). The controller (610) obtains a sensor value from a sensor (22) connecte...
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WO/2021/008816A1 |
The invention relates to a turbine casing for an exhaust-gas turbine, which turbine casing has a connection flange for bearing-casing-side attachment to a bearing casing in which casing-connection holes that are mutually spaced in the ci...
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WO/2021/008842A1 |
A blade for a turbomachine fan, the blade (1) being made from a composite material containing a plurality of longitudinal conductive fibres (F) embedded in an electrically non-conductive matrix, the blade (1) having at least one fastenin...
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WO/2021/007056A1 |
A flow regulating system (200) for increasing a flow of cooling fluid (140, 202) supplied to a cooling system of a component of a gas turbine system (10) is provided. The flow regulating system (200) includes: a pneumatic circuit (206) e...
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