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WO/2024/014349A1 |
A fuel supply apparatus comprising: a water electrolysis device; a dehumidifier that is provided in a hydrogen line through which hydrogen from the water electrolysis device flows, and includes an adsorbing material for adsorbing water c...
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WO/2024/015218A1 |
A combined cycle power plant (100) includes a gas turbine engine (102) that includes a compressor (106) having a compressor inlet (168), a compressor outlet (170), and an interstage inlet (172) defined therebetween. The turbine (110) als...
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WO/2024/012715A1 |
An energy conversion plant is disclosed, having one or more driving units, for driving respective loads, such as an electric motor or a centrifugal compressor. The energy conversion plant comprises at least one heat exchange recuperator,...
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WO/2024/012909A1 |
A gear changing system for the driving of an apparatus by an accessory gearbox comprising: a train comprising a ring gear (5), a planetary gear (6) integral with an output shaft (4) and a planet carrier (7) integral with an input shaft (...
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WO/2024/009587A1 |
Provided are an assembly method and an assembly device capable of identifying, from among a plurality of overlapping regions, an overlapping region that requires adjustment. In this assembly method for assembling a bulkhead (30) to an ou...
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WO/2024/009715A1 |
A gas turbine system (1), including a gas turbine engine (3) having a compressor (11), a combustor (13), and a turbine (15), and a fuel gas pressure adjustment device (5) that adjusts the pressure of the fuel gas (F) introduced into the ...
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WO/2024/009024A1 |
The invention relates to a propulsion unit comprising: an electric motor (10), which includes an annular stator (11) about a longitudinal axis (X) and a rotor arranged radially inside the stator (11), so as to be rotated about the longit...
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WO/2024/009755A1 |
This gas turbine control device is a control device for controlling the operation of a gas turbine, and comprises a fuel command value calculation unit for calculating a fuel command value to be given to the gas turbine, and a speed incr...
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WO/2024/008698A1 |
The invention relates to a system (1) for heating a fuel for supplying an aircraft turbine engine (M), the heating system (1) comprising a fuel circuit (2); at least one first heat exchanger (41) configured to be mounted in an inner duct...
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WO/2024/010565A1 |
A micro-turbine core fabricated as a single part using 3D additive manufacturing (AM) to simultaneously form sequential layers of at least two static components from any of the following static components: central bearing support structu...
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WO/2024/006185A1 |
A redundant fuel metering system and method for a multi-stage combustor that utilizes a fuel metering valve EHSV from a less critical combustor stage fuel metering system as a redundant backup to the main metering valve EHSV. In the even...
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WO/2024/003083A1 |
The invention concerns an aircraft fuel heating arrangement comprising an exhaust cone for a gas turbine engine, the exhaust cone having an outer body defining an internal cone cavity, the internal cone cavity comprising one or more cond...
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WO/2024/003475A1 |
The present invention relates to an oil tank (40) for an aircraft turbine engine, comprising: an enclosure (54) capable of containing the oil and having a main axis intended to be oriented vertically in the mounting position; an oil inle...
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WO/2024/004529A1 |
This gas turbine stator blade is provided with: a leading edge part partition that divides a cavity inside the blade into a leading edge side cavity and a trailing edge side cavity; a negative pressure surface side partition wall that is...
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WO/2024/003494A1 |
This aircraft propulsion system (12) comprises a turbine engine (20), a control system (24), a member (72) for determining a current engine speed (Rc) of the spool of the turbine engine (20), and a rotary machine (22) coupled to the tran...
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WO/2024/004509A1 |
This stator blade has an airfoil, a plurality of blade air passages, and a plurality of rear end air passages. The plurality of blade air passages are arranged side by side from the side of the leading edge of the airfoil to the side of ...
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WO/2023/247847A1 |
The present invention relates to an oil tank (40) for an aircraft turbomachine, the oil tank comprising: a main chamber (54) suitable for containing oil; an inlet (66) for oil mixed with air; and an oil outlet (72), the invention being c...
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WO/2023/247846A1 |
The invention relates to an oil tank (40) for a turbomachine, the oil tank comprising an oil chamber having a main axis and walls defining a first compartment (56) and a second compartment (58) which is separated from the first compartme...
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WO/2023/248728A1 |
This method comprises: a shaping step in which, while a metal powder is being disposed on a base plate, the metal powder is bonded together and solidified to thereby form an additively manufactured object having inner passages and discha...
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WO/2023/246980A1 |
The invention relates to a propulsion system (1) for an aircraft, comprising a gas turbine (2) having a core flow channel (10), wherein a compressor (12), a combustion chamber (13), a first turbine, in particular a high-pressure turbine ...
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WO/2023/246979A1 |
A method (100) for operating an aircraft-engine turbomachine (1) having a compressor (3), through which a gas flow (6) passes in a flow direction, a combustion chamber (4), a turbine (5) and a heat exchanger (8) downstream of the turbine...
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WO/2023/249659A1 |
An integrated hydrogen-electric engine including an air compressor system, a hydrogen fuel source, a fuel cell, a heat exchanger, an elongated shaft, a motor assembly and a combustion chamber including a turbine downstream of the fuel ce...
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WO/2023/243734A1 |
This gas turbine combustor comprises: a shell that surrounds a combustion chamber; a liner that is positioned inward of the shell, and faces the combustion chamber; and a fitting that attaches the liner to the shell. The fitting includes...
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WO/2023/242506A1 |
The invention relates to a gear train comprising a sun gear (10) having a central axis (X), a ring gear (20) arranged coaxially around the sun gear (10), a planet carrier (30), and a first and a second plurality of planet gears (31, 32)....
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WO/2023/240377A1 |
An aerospace low-noise engine, comprising a housing (1). The middle of the left side of the housing (1) is fixedly connected to a spiral shaft (2), and an inner wall of the spiral shaft (2) is fixedly connected to a noise reduction devic...
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WO/2023/242507A1 |
The invention relates to a gear train comprising a sun gear (10) having a central axis (X), a ring gear (20) arranged coaxially around the sun gear (10), a planet carrier (30), and a first and a second plurality of planet gears (31, 32)....
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WO/2023/241823A1 |
A hybrid train system is disclosed. The hybrid train system comprises at least one gas turbine to drive a load, and an electric machine unit, also connected to the load. A clutch is installed between the gas turbine and the load. Also, a...
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WO/2023/243434A1 |
A hydrogen combustor according to one embodiment of the present invention comprises at least one fuel injector module and a hydrogen supply pipe. The at least one fuel injector module is configured by forming a module from a plurality of...
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WO/2023/244179A1 |
Some embodiments relate to a power generation system. An example power generation system comprises: a gas turbine to generate electrical power from combustion of natural gas; a gas supply line for supplying vaporised liquefied natural ga...
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WO/2023/244180A1 |
Some embodiments relate to a power generation system. An example power generation system comprises: a gas turbine to generate electrical power from combustion of natural gas; an organic Rankine cycle (ORC) generator to generate electrica...
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WO/2023/244182A1 |
Some embodiments relate to a power generation system. An example floating power generation system comprises: a vessel, the vessel including: a vessel frame, a hull around the vessel frame and defining fore and aft sections, and a deck su...
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WO/2023/241021A1 |
A gas jet split stream-type rotor supercharged gas turbine, which comprises a gas compressor (21) and a turbine (23) connected by means of a mechanical shaft; a rotor (25) having multiple rows of combustion chambers (26) is arranged betw...
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WO/2023/237154A1 |
The invention relates to an exhaust gas treatment apparatus (1) for an aircraft engine (2), the exhaust gas treatment apparatus comprising an exhaust gas channel (7), through which an exhaust gas of the aircraft engine (2) can flow, a fi...
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WO/2023/239825A1 |
Various exemplary embodiments of a power system for converting thermal energy from a heat source to electricity are disclosed. In one exemplary embodiment, the power conversion system includes a turbomachinery engine based on fossil-fuel...
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WO/2023/237152A1 |
The invention relates to a propulsion system (1) for an aircraft, comprising a gas turbine (2) with a main flow channel (10) and a bypass flow channel (20), a water system (30) and a steam system (40), wherein the water system (30) compr...
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WO/2023/234134A1 |
This stator blade comprises a blade body having a cross-sectional shape that forms a blade profile. The blade body includes: a trailing end space and an adjacent space that are located between a leading edge and a trailing edge; and a pl...
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WO/2023/232828A1 |
The invention relates to a de-icing device for an air intake of an aircraft turbojet engine nacelle, having at least one injector (3) for injecting a stream of hot air (FAC) comprising a peripheral member (30) which internally defines a ...
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WO/2023/233109A1 |
The invention relates to an acoustic panel (9) for an aircraft turbomachine (1), the acoustic panel (9) comprising: - a first skin (10) formed from a first composite material having a first polymer matrix and reinforcing fibres embedded ...
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WO/2023/227411A1 |
The present invention relates to a lubrication assembly (1) comprising two pumps (10, 20), the shafts (11, 21) of which are rotatably coupled by means of at least one polygonal profile coupling (40).
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WO/2023/227842A1 |
The invention relates to a heat exchanger device (1) for an aircraft turbomachine, which device comprises a heat exchanger body (30), an upstream hot-fluid header (12) attached to the heat exchanger body (30) and configured to collect a ...
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WO/2023/225355A1 |
A high voltage discharge generating a plasma wave front is disposed within a headspace over an oil-containing liquid in order to create various chemical changes within the headspace, and ultimately within the liquid in order to inactivat...
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WO/2023/222549A1 |
The invention relates to a de-icing system configured to be mounted on a surface (3A, 3B) of a mechanical part (1) to be de-iced, said system comprising at least: - a piezoelectric actuator (9), - a fastening device (11) configured to fa...
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WO/2023/223655A1 |
This shaft sealing device is disposed between a rotor and a stator, and partitions an annular space between the outer peripheral surface of the rotor and the inner peripheral surface of the stator into a first axial side and a second axi...
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WO/2023/224797A1 |
Embodiments of a metering valve for a fuel nozzle are disclosed. The metering valve includes a fitting having an interior cavity and an inlet, a liner disposed within the interior cavity, and a spool having an orifice. The liner includes...
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WO/2023/218771A1 |
A power generation system comprises a rotating electric machine, a plurality of storage batteries, a discharge control unit for controlling the discharging of the plurality of storage batteries, and an abnormality detection unit for dete...
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WO/2023/216762A1 |
A deflagration engine having an air intake end not in communication with a fixed combustion chamber, the deflagration engine comprising an air intake duct, a bearing, a shaft, and an aircraft. The deflagration engine further comprises a ...
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WO/2023/219100A1 |
The present disclosure provides a maintenance method for gas turbines, said method comprising: a step for preparing a third actuator; a step for removing a first actuator and attaching the third actuator at a first inspection time; a ste...
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WO/2023/218776A1 |
This electric power generation system comprises: a rotating machine; a storage battery that is discharged when the rotating machine is started; and a discharge control unit controlling the discharge of the storage battery, wherein the di...
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WO/2023/217798A1 |
The invention relates to a method for controlling a turbomachine comprising a fan positioned upstream of a gas generator, the turbomachine comprising an electric motor forming a torque injection device for a high-pressure rotary shaft, i...
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WO/2023/218777A1 |
This cylinder for a combustor that enables combustion of fuel on an inner peripheral side thereof comprises: a plurality of cooling paths that are formed between an inner peripheral surface and an outer peripheral surface and enable circ...
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