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WO/2024/041680A4 |
A turbine assembly according to the present invention has passages formed in a fixing part of a second wheel of the assembly between at least some adjacent blades 1r/1s for draining the working medium that has leaked through a non-contac...
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WO/2024/084221A1 |
A pressure activated non-contact seal for sealing against a rotating cylindrical surface between a high-pressure region and a low-pressure region comprises a seal member carrier spaced from the rotating surface defining a seal member cha...
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WO/2024/080158A1 |
Provided is a cryogenic power generation apparatus which is provided with a thrust bearing device placed on one side in the axial direction of a rotor shaft as compared to a first journal bearing device in the inner circumferential side ...
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WO/2024/069075A1 |
One aspect of the invention relates to a method (2) for monitoring a turbomachine (1) comprising a stator (11), a rotor (12) comprising blades (13), a strain gauge (15) attached to the stator (11) and a position sensor (14) for detecting...
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WO/2024/068224A1 |
The invention relates to a turbomachine (1), in particular for a fuel cell system (100) of a vehicle (200), for example of a utility vehicle, the turbomachine comprising a rotor shaft (19), an expander wheel (15) that is fastened on the ...
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WO/2024/066255A1 |
A high-pressure turbine active clearance control device, comprising a high-pressure turbine casing (1), gas collection casings (2), an impingement heat exchange tube (3) and a fluid oscillator (4). The gas collection casings (2) are disc...
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WO/2024/066426A1 |
An oil and gas dual-effect seal structure for a gas turbine, comprising: a turbine rotor, a fixed sleeve, a supporting ring, a seal ring, a sleeve, an adjusting ring, a bearing, a locking gasket and a nut. The turbine rotor is sleeved wi...
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WO/2024/062189A1 |
The invention relates to a sealing device (1) comprising: a ring (10) that comprises a main sealing lip (12) and a secondary sealing lip (14), the main sealing lip having an inner surface (11), the secondary sealing lip (14) having a rad...
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WO/2024/056958A1 |
The invention relates to a method for producing an abradable ceramic composite coating on a substrate, the method comprising: obtaining (E1) a composition (30) in powder form comprising a matrix powder and a ceramic filler hydrated precu...
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WO/2024/052631A1 |
The invention relates to a guide vane (33B) for attachment to a stator shroud of a gas turbine engine, comprising: - a profiled part (36B) intended to extend in a gas flow in order to guide the gas flow, the profiled part (36B) having a ...
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WO/2024/045240A1 |
A supercritical carbon dioxide radial-inflow turbine structure suitable for gas inlet at 600 ℃, belonging to the technical field of turbines. The present invention aims to solve the problem that sealing of supercritical carbon dioxide ...
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WO/2024/041680A1 |
A turbine assembly according to the present invention has passages formed in a fixing part of a second wheel of the assembly between at least some adjacent blades 1r/1s for draining the working medium that has leaked through a non-contac...
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WO/2024/040418A1 |
A sealing system for a crawler robot. The system comprises a sealing device body (1), wherein the sealing device body (1) is provided with a sealing groove (2), and a pressing plate (3) is provided on the sealing device body (1); a seali...
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WO/2024/040667A1 |
A 15MW supercritical CO2 axial flow back-pressure type turbine having volute casing air inlet, comprising a front bearing box (1), an air cylinder (2), a pressure-balancing pipe (3), a sealing member (4), a rear bearing box (5) and a rot...
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WO/2024/035537A1 |
A gas turbine engine includes an outer casing, an inner casing surrounded by the outer casing, the inner casing and the outer casing defining a casing cavity therebetween. A blower is disposed external of the outer casing and operable to...
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WO/2024/007460A1 |
The present invention relates to the technical field of aeroengines, and disclosed is an air-bleed mechanism for a turbine engine, which solves the problem that existing air-bleed mechanisms for turbine engines can hardly meet the requir...
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WO/2024/003641A1 |
A propulsor fan and drive system having reduced noise emission is disclosed. The propulsor fan includes a blade fan having a plurality of blades. The blades may include a dual pin-root design to secure the blade fan to a hub and a shroud...
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WO/2023/232661A1 |
The invention relates to a sealing ring (01) for sealing off a gap (19), surrounding a rotor shaft (02), between a rear and a front stator unit (14, 15). According to the invention, the sealing ring (01) comprises an upper left-hand seal...
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WO/2023/232168A1 |
Sensors of the rotor vibrations measure a relative distance of a revolving turbine rotor and a stator. A trajectory of eccentric rotor motion is reconstructed by combination of measured distances in an orthogonal coordinate system. The t...
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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/2023/214507A1 |
A plurality of circumferentially-arranged split plates retained by a seal-ring retention ring include a plurality of first split-plate groups that are circumferentially arranged on one circumferential side of the seal-ring retention ring...
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WO/2023/202900A1 |
The invention relates to a seal arrangement (1) comprising a seal (5) having sealing spikes (6), the sealing spikes (6) being arranged in a seal partner (2) and consisting of the material NiCr22Fe18Mo.
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WO/2023/180668A1 |
The invention relates to a turbine engine module, in particular an aircraft turbine engine (10), comprising: - an annular casing (52) having an internal wall (53) forming a channel wall; and - a nozzle (32) surrounded by the casing and c...
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WO/2023/175256A1 |
The invention relates to a method for maintaining a bladed wheel of a high-pressure turbine of a turbomachine, extending along an axis, comprising a disc (11) comprising cavities (15), and blades (12) extending radially and each comprisi...
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WO/2023/157520A1 |
This sealing device comprises: a sealing member provided between a rotating part and a stationary part of a rotating machine in a radial direction of the rotating machine; a holding member for supporting the sealing member movably along ...
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WO/2023/156726A1 |
An assembly for an aircraft turbomachine (10) comprises a plurality of sectors made of CMC and a plurality of sealing tongues (44') which are mounted between the sectors. Each of these tongues (44') comprises a first longitudinal edge (4...
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WO/2023/157519A1 |
This sealing device comprises: a sealing member provided between a rotary part and a stationary part of a rotary machine in the radial direction of the rotary machine; and a holding member which is at least partially accommodated in a gr...
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WO/2023/156752A1 |
The invention relates to a sealing system (21) for a turbomachine bearing enclosure (E1), comprising a stator (22) carrying a rotor (23), this system (21) comprising a seal (25) carried by the stator (22) and surrounding the rotor (23), ...
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WO/2023/148602A1 |
Integrated system (20) including a turbomachine (1) connected to a speed reducer or multiplier (2) in which: - a shaft (3) of the turbomachine (1) is separated from an input shaft (2') of the speed reducer or multiplier (2) and connected...
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WO/2023/141012A1 |
A circumferential seal assembly (30) for use between a higher pressure side (36) and a lower pressure side (37) is presented. The seal assembly (30) includes a primary sealing ring (31), a second sealing ring (32), a third sealing ring (...
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WO/2023/141263A1 |
An apparatus has: a first member (120); a shaft (40; 50) rotatable relative to the first member about an axis; and a seal system (100). The seal system has a seal carrier (150) having: an axially-extending wall (156) having an inner diam...
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WO/2023/135174A1 |
A sealing device (1) for sealing a bearing cover (2) from a bearing housing (3) is described. The sealing device includes a central opening (11) for receiving a rotatable shaft (31) supported in the bearing housing (3) and extending thro...
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WO/2023/134177A1 |
A gas turbine with a gas seal component (200), comprising a rotating shaft (100), a gas compressor (800), a turbine (300), and a combustion chamber (400). The gas compressor (800) and the turbine (300) are sleeved on the rotating shaft (...
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WO/2023/136314A1 |
A sealing device according to some embodiments comprises: a sealing member that is disposed between a rotating member of a rotating machine and a stationary member disposed on the outer side of the rotating member in the radial direction...
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WO/2023/131759A1 |
The invention relates to a turbine for a turbomachine having a longitudinal axis (X1), which turbine comprises an annular outer casing (20) surrounding a ring (30). The ring (30) comprises an annular platform (31) and a downstream annula...
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WO/2023/123860A1 |
The present invention relates to the technical field of gas-turbine engine structures, and in particular to a floating-type ceramic matrix composite turbine outer ring, and an assembly structure and method for same and a casing. The prob...
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WO/2023/126959A1 |
The present disclosure relates to a method for determining an initial clearance of turbomachinery seals. Initially, seal configurations, operating conditions and seal material are determined. Based on operating conditions, centrifugal gr...
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WO/2023/111454A1 |
The present invention relates to a turbine rotor (2) of a turbine engine of an aircraft, the rotor comprising a rotor disc (3) provided at its periphery with a plurality of cavities (30) for receiving the root (42) of a blade (4). This r...
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WO/2023/099850A1 |
The present invention relates to an assembly for lubricating and pressurizing a chamber for a turbomachine comprising at least one lubricated chamber (112) protected by two seals (112-1,112-2), the turbomachine further comprising a prima...
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WO/2023/079239A1 |
The invention relates to a labyrinth-type sealing device for an aircraft turbomachine, this device having: - a rotor comprising at least one external annular lip (12a, 12b), and - a stator comprising an annular coating (16) made of abrad...
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WO/2023/078886A1 |
The invention relates to a seal assembly (42) for an industrial gearbox (10), said seal assembly comprising: a vertically aligned lower power shaft (16) for exchanging torque with the industrial gearbox (10); a gearbox component (40) of ...
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WO/2023/067155A1 |
There is provided a rotation device comprising a rotor, a stator, a target component, and a sealing device. The rotor is arranged to rotate along a rotation axis relative to the stator. The stator is arranged radial outward of the rotor ...
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WO/2023/066566A1 |
The invention relates to a blade (1) for a continuous flow machine, wherein the blade (1) is formed along a radial direction (3) and has a blade tip (4) and a blade cross-sectional profile with a pressure side (5) and a suction side (6),...
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WO/2023/062302A1 |
The invention relates to a tool (20) for forming an abradable coating (18) in an aircraft turbine engine module (40), this module (40) having an annular stator casing (10) and a central rotor (42) which can move inside the casing (10) ab...
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WO/2023/061844A1 |
The invention relates to an element (1) for compensation of tolerances and/or gap widths of a device, having a main body (2) which has at least one annular cross-sectional portion (3), wherein the cross-sectional portion (3) has, in its ...
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WO/2023/062314A1 |
The invention relates to a movable ring assembly for a turbomachine rotor, the movable ring (6) comprising an outer peripheral toothing (7), each tooth of the outer peripheral toothing (7) having an inner face (7a) intended to be positio...
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WO/2023/061674A1 |
The invention relates to a component (1) comprising a substrate (30) of little porosity having a sealing area (4). The sealing area (4), when seen in the axial direction (24), has at least two juxtaposed porous sealing surfaces (7, 10, 1...
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WO/2023/062327A1 |
The present invention relates to a nozzle guide vane (3) for a turbine (2), having an axis (X) of revolution and comprising: - a flange (6) extending radially relative to the axis (X); - a ring seal (12) mounted on the flange and compris...
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WO/2023/047034A1 |
The invention relates to a high-pressure gas turbine for a turbine engine (10), the turbine comprising a nozzle (30), an annular row of moving blades (40) mounted downstream of the nozzle (30), a first recirculation cavity (60), a second...
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WO/2023/044572A1 |
An assembly may include a rim-rotor turbine having a hub adapted to be mounted or connected to a rotating shaft, a rim-rotor, the rim-rotor having a cooling ring defining at least one cooling channel, and a plurality of blades with each ...
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