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WO/2021/058330A1 |
The invention relates to a gas turbine engine (10) comprising a transmission (30). The transmission (30) is arranged radially in an interior space (40) delimited by a support structure (24, 24A, 24B, 24C) secured to the housing and provi...
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WO/2021/060005A1 |
Provided are: a powder material for spraying, the powder material being used for forming a sprayed film that has both low thermal conductivity and high abrasion resistance; and a method for manufacturing a sprayed film in which the powde...
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WO/2021/062185A1 |
A system and method are disclosed for cooling ambient air to be supplied as combustion air to a gas turbine. The system comprises a closed coolant loop direct expansion cooling system including a compressor for compressing a suitable wor...
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WO/2021/058893A1 |
Oil restrictor (30) for emergency lubrication of a component for an aircraft turbine engine, said restrictor comprising a metal cylindrical body having a longitudinal axis (A) and configured to be housed in and shrink-fitted into a cylin...
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WO/2021/058888A1 |
The invention relates to an aircraft propulsion assembly comprising a fan shaft (12) which is connected to a turbine shaft (100) by means of a reduction gear (14). The guiding of the fan shaft (12) is carried out by a first bearing (15) ...
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WO/2021/056174A1 |
An electrically-driven fracturing well site system, comprising a gas source, a power supply system (2), electrically-driven fracturing equipment (3), electrically-driven sand blending equipment (4), sand supply equipment, liquid supply e...
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WO/2021/054851A1 |
The present invention provides a heat exchanging acoustic liner for an electric fan engine and a cooling system with a heat exchanging acoustic liner for an electric fan engine. The heat exchanging acoustic liner for an electric fan c...
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WO/2021/051396A1 |
Disclosed is a turbine fracturing semitrailer, comprising a semitrailer body (3), a turbine engine (7), a reduction gearbox (8), a transmission mechanism and a plunger pump (10), wherein the turbine engine (7), the reduction gearbox (8),...
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WO/2021/049051A1 |
This gas turbine is provided with: a gas turbine cabin through the inside of which a working fluid flows; and a heat conductive member which is formed from a material having a higher heat conduction than the gas turbine cabin, and which ...
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WO/2021/048489A1 |
The invention relates to a structural and/or acoustic panel (30) comprising an inner skin (31), an outer skin (32), a honeycomb structure (33) and at least one sealing flange (40). The sealing flange (40) has a U-shaped section directed ...
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WO/2021/049238A1 |
An outlet seal (70o) connects a combustor that combusts a fuel to generate combustion gas and a shroud for a stator. The outlet seal has a gas path surface (72), a first connection section (81), and a second connection section (91). The ...
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WO/2021/044614A1 |
This seal mechanism, which is inserted into a seal groove formed between mutually facing surfaces of two members, is provided with: a first seal member; a second seal member disposed so as to face the first seal member; and a deformation...
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WO/2021/042371A1 |
Disclosed is a sound insulation compartment for a turbine engine, the sound insulation compartment being sheathed over the turbine engine, and the sound insulation compartment comprising a compartment body, an intake noise reduction unit...
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WO/2021/045645A1 |
A device for bleeding air in the rotor of a turbojet engine compressor consists of air bleed slots, and air bleed tubes for guiding cooling air into a turbine, wherein the air bleed tubes are provided with ledges and with an upper angle-...
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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/2021/039467A1 |
A compressed air energy storage (CAES) electricity generating device 1 is provided with a combined compressor/expander 10, a combined electric motor/electricity generator 20, a pressure accumulating unit 30, and a transmission unit 21. T...
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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/2021/039903A1 |
This gas turbine engine, in which a compressor, a combustor, and a turbine are arranged side by side along an axis of rotation, is provided with: a casing accommodating the compressor, the combustor, and the turbine; a plurality of fuel ...
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WO/2021/039928A1 |
This gas turbine engine includes: a casing for housing a compressor or the like; a plurality of bearings; a main lubricating device which has an oil mist generator for generating oil mist by mixing oil with compressed air bled from the c...
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WO/2021/039902A1 |
This gas turbine engine is provided with: a casing in which a compressor, a combustor, and a turbine are housed; a generator that is disposed in the casing and that is driven by a rotation shaft; an electric power line for transmitting e...
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WO/2021/038169A1 |
The invention relates to a bypass turbomachine (2) for an aircraft, comprising a gas generator (5) and a ducted fan (4) comprising variable pitch blades (18) configured to take a reverse thrust position driving a reverse flow (24) of air...
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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/2021/034359A2 |
A turbine engine includes a duct defining an annular passage, at least two heat exchangers arranged within the annular passage and spaced circumferentially apart, a passage between the at least two heat exchangers, and a forward flow con...
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WO/2021/033564A1 |
A stator blade (50) comprises a blade body (51) and a shroud (60i). The shroud has a gas path surface (64), a leading-end surface (62f), a leading-end corner (66) that is the corner of the gas path surface and the leading-end surface, a ...
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WO/2021/032534A1 |
Disclosed is an air intake (1) of an aircraft turbine engine nacelle comprising a lip (2), a downstream portion (3) and an internal partition (5) separating the lip (2) and the downstream portion (3), the lip (2) delimiting an annular re...
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WO/2021/023713A1 |
The present invention relates to a system for storing and recovering energy by compressed gas, comprising at least one rotodynamic fluid-compression means (1), at least one compressed-gas storage means (3) and at least one means for roto...
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WO/2021/020372A1 |
An acoustic attenuator (61A) comprises a first attenuation unit (71A), a second attenuation unit (63), a welded section (W1), and a communication part (64A). A first acoustic damper (74) is provided on an outer surface of a first acousti...
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WO/2021/020518A1 |
This steam turbine is provided with: a rotary shaft; a plurality of movable blades each of which has a movable blade body (42) and a shroud (43), and which are circumferentially arranged at intervals; a casing (5) that has a recessed sec...
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WO/2021/019163A1 |
The invention relates to a device (20) for driving an integrated generator (16) from an accessories relay box (12) of the turbomachine (10), comprising: - first and second electric motors (30, 40) arranged to transfer electric power from...
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WO/2021/019144A1 |
The invention relates to a turbomachine (10) comprising: - an electric machine (30), - a starter-generator (17) incorporating a second electric machine (40) configured to operate as a starter and a generator, the electric machine and the...
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WO/2021/019190A2 |
The invention relates to a method for detecting a hardware configuration of a piece of equipment located on-board an aircraft, which is able to receive, as input, a setpoint current (lc), and to produce, as output, a response current (I)...
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WO/2021/020170A1 |
A plant monitoring device (20) is provided with: a state quantity acquiring unit (211) which acquires state quantities for each of a plurality of characteristic items relating to a plant; an abnormality degree calculating unit (212) whic...
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WO/2021/015081A1 |
The purpose of the present invention is to suppress leakage of fluid and suppress a decrease in strength. A seal member (30) is disposed between a rotor (12) and a stator (11) to provide a seal between the rotor (12) and the stator (11)....
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WO/2021/014667A1 |
Provided is a system capable of properly cooling a generator arranged in a hot section of a turbo fan engine and a power transmission line connected to the generator irrespective of a rating of the engine. The system is provided with: a ...
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WO/2021/009954A1 |
Provided is a gas turbine system (100) used in a mobile body including a thrust generator that generates thrust by power, the gas turbine system (100) being equipped with: a compressor (10) that compresses external air to generate compre...
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WO/2021/008900A1 |
The invention regards a gas turbine engine for an aircraft that comprises a nacelle (112), a fan (102), an engine core located downstream of the fan, the engine core comprising a turbine and a core shaft (111) coupling the turbine to the...
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WO/2021/009436A1 |
Disclosed is an epicyclic reduction gear (15) for a turbomachine comprising: - a sun gear (16) that is able to rotate about a first axis (A); - a ring gear (17) surrounding the sun gear (16) and able to rotate about the first axis (A), t...
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WO/2021/009457A1 |
Method for producing a casing (3) for an aircraft turbine engine, said casing comprising an annular shell (9) extending about an axis A and made of a composite material, an annular layer (4) comprising an abradable material arranged insi...
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WO/2021/008901A1 |
A shaft connection (50) comprises: a female component (51) with an internal spline toothing system (52), and a male component (55) with an external spline toothing system (56) which can be brought into engagement with the internal spline...
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WO/2021/009952A1 |
Provided is a gas turbine system (100) that is used for a mobile object comprising a thrust generator for generating thrust from electric power, the gas turbine system being provided with: a combustor (20) for causing compressed air gene...
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WO/2021/009435A1 |
The invention relates to an epicyclic reduction gear (15) for a turbomachine, comprising: - a sun wheel (16) that is rotatable about a first axis (A); - a ring gear (17) surrounding the sun wheel (16) and being rotatable about the first ...
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WO/2021/009953A1 |
Provided is a gas turbine system 100 equipped with: a compressor (10) that compresses external air to generate compressed air; a combustor (20) that burns the compressed air generated by the compressor (10) with fuel to generate combusti...
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WO/2021/009430A1 |
One aspect of the invention relates to a seal (26) for sealing a first member, such as a discharge duct (21), to a second member, such as an outer annular shroud, the seal being configured to surround a third turbomachine member, such as...
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WO/2021/006438A1 |
The present invention relates to a supercritical carbon dioxide engine. The supercritical carbon dioxide engine, which uses supercritical carbon dioxide as a working fluid, comprises: an output shaft disposed inside a gear box and provid...
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WO/2021/004735A1 |
The invention relates to a soundproofing coating with a cellular structure consisting of several structures (11) connected in a transverse direction (D2), each formed by connecting a first longitudinal strip (4) with a second longitudina...
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WO/2021/007216A1 |
Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan...
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WO/2021/005416A1 |
A fuel nozzle assembly (350) for a gas turbine combustion chamber includes a housing (351) having a third port (357) connected to a first low calorific gas supply, a second port (355) separate from the third port and connected to a secon...
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WO/2021/002173A1 |
The present invention provides a thermal barrier coated component, monitoring or evaluation of the soundness of which is able to be adequately carried out on the basis of the thermal boundary conditions that are detected by a sensor. A t...
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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/2021/001609A1 |
A pump (12), which can be a gear pump driven by a rotating body of an aircraft turbomachine such as a blower shaft, is always rotated in the same direction, thanks to a transmission comprising an oblique double gear (19) which is formed ...
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