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WO/2021/163760A1 |
There is provided a compact turbine-compressor assembly 25. The turbine-compressor assembly 25 includes a turbine wheel 39 with one or more turbine blades 41 and a compressor wheel 47 that includes one or more compressor blades 49. The c...
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WO/2021/164958A1 |
There is disclosed a fixing apparatus (10) for fixing a secondary component (14) to a fan blade, the fixing apparatus comprising: a first clamp part (16) comprising a first inner surface (20) and a second clamp part (18) comprising a sec...
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WO/2021/166395A1 |
A bearing structure (100) according to the present disclosure includes a rotation shaft (11), a dynamic bearing (12) that has a foil (22) disposed in the periphery of the rotation shaft (11) and configuring a bearing face and a foil hold...
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WO/2021/165598A1 |
Device for distributing oil from a rolling bearing (8) for an aircraft turbine engine, comprising: - a rolling bearing (8), - a body (5) for distributing oil, which body is configured to be mounted on a turbine engine shaft (4), said bod...
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WO/2021/165606A1 |
Dual flow turbine engine (10) comprising: - at least one lubricant tank (40) located in an annular space of the turbine engine body, - at least one hatch (46) which is provided on an external cowling (32) of a nacelle, for filling the ta...
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WO/2021/167001A1 |
A flange cooling structure for a gas turbine engine, wherein one flange among a first flange and a second flange is a high-pressure-side flange facing a first region, the other flange among the first flange and the second flange is a low...
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WO/2021/167082A1 |
This information processing device is provided with: a storage unit which, having as reference detection values at least one of multiple detection values in one set, stores correction information for correcting detection times of multipl...
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WO/2021/166710A1 |
This exit seal is for connecting an exit flange of a combustor and a shroud in a stator blade of a turbine. The exit seal is equipped with: a seal body that extends in a circumferential direction; and a lid member disposed at a circumfer...
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WO/2021/165605A1 |
The invention relates to a turbine comprising a rotor (27) surrounded by a stator, a first movable stage comprising a set of rotary blades, a second movable stage comprising a second set of rotary blades, nozzle guide vanes (33) includin...
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WO/2021/162091A1 |
A gas turbine engine according to an embodiment of the present invention is provided with an oil tank for storing lubricating oil, a compressor, a combustor, and a cylindrical external case accommodating a turbine, wherein the oil tank i...
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WO/2021/162092A1 |
According to one embodiment of the present invention, a gas turbine engine comprises: a compressor that compresses air that has been taken in; a combustor that sprays fuel into the air compressed by the compressor and combusts the fuel; ...
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WO/2021/155962A1 |
The present invention relates to a method for modifying an existing single shaft combined cycle power plant (1) comprising a steam turbine part (3) and a gas turbine part (2) which are connected to each other rigidly by an intermediate s...
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WO/2021/151703A1 |
The invention relates to an oil system (42) of a gas turbine engine (10), comprising a first oil circuit (43) and at least one second oil circuit (45). By means of the oil circuits (43, 45), oil can be supplied to at least one hydraulic ...
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WO/2021/153556A1 |
This turbine is provided with: a rotor which comprises a rotary shaft capable of rotating on a shaft line and a moving blade row provided to the outer circumferential surface of the rotary shaft; a casing which covers the rotor from the ...
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WO/2021/154198A1 |
A low-cost low-pressure steam turbine consisting of a housing (1) and blades (4). Provided on the side surface of the housing (1) are two supply pipes (5), and provided in the radial part of the housing (1) of the steam turbine is a disc...
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WO/2021/152243A1 |
The invention relates to a casing (3) of an aircraft turbomachine, said casing comprising: - an annular shell (9) extending around an axis A and made of a composite material comprising fibres which are woven and embedded in a resin, - an...
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WO/2021/150375A1 |
A circumferential seal assembly (87) suitable for forming a thin film between a rotatable runner (15, 35, 67) and a sealing ring (3, 4, 23, 24) is presented. The assembly (87) includes an annular seal housing (2, 22), a rotatable runner ...
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WO/2021/149351A1 |
In the present invention, the vertical movement of a compartment is suppressed. This rotating machine support device is provided to a steam turbine (rotating machine) that includes: a rotor (rotating body) in which the center axis thereo...
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WO/2021/148740A1 |
The invention relates to a rotor for an aircraft turbine engine, comprising at least one mobile disk (63) supporting moving blades (64), the mobile disk (63) comprising a plurality of cells (632), into which feet (642) of the moving blad...
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WO/2021/148756A1 |
The present invention relates to a fluid recovery assembly (40) for a turbine (25), such as a low-pressure turbine, of a turbine engine comprising an annular wall (46) comprising a first opening and a second opening spaced apart angularl...
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WO/2021/148077A1 |
The invention relates to a sealing-air apparatus (10) for a turbomachine (100), comprising a sealing device (20) for sealing a sealing gap (50) between two components (30, 40) of the sealing-air apparatus (10) with respect to a sealing-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/2021/144144A1 |
The integrated expander and motor-compressor assembly (2) comprises a compression section (9) mounted between the two radial bearings (15, 16) on a transmission shaft (10), an expander (30) cantilevered at a free end of the transmission ...
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WO/2021/144791A1 |
A novel structural arrangement for the various components of an Ultra-Micro Gas Turbine Generator, based on a single part impeller element which comprises the compressor, the turbine and the electrical generator core in a single annular ...
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WO/2021/146513A1 |
A gas microturbine that includes a closed-loop oil distribution system that includes an oil reservoir, an oil- supply circuit, an oil-scavenge circuit, and a pump. The oil reservoir is configured to contain a provision of oil. The oil-su...
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WO/2021/144002A1 |
A rotational component comprising: a monolithic compressor component for rotation about a rotor axis defining proximal and distal directions, the monolithic compressor component comprising a compressor shaft defining a rotor core and a c...
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WO/2021/139939A1 |
The invention relates to a guide vane ring (1) which is divided into an upper and into a lower guide vane ring half, with an inner ring (2) which is split at least in two, has a substantially U-shaped cross section, and forms a radially ...
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WO/2021/140294A1 |
The invention relates to an assembly between an aircraft pylon (30) and a turbomachine (20) of longitudinal axis (X), the pylon (30) and the turbomachine (20) each comprising front and rear longitudinal regions, the assembly comprising a...
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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/2021/139985A1 |
A turbocharging assembly (100) is described. The turbocharging assembly (100) includes a housing (130) having a first housing part (130A) for enclosing a first stage (110), particularly a low-pressure stage, comprising a first turbine (1...
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WO/2021/129425A1 |
An air bearing, comprising: a bearing body (220), a bearing housing (230), a bearing end cover (240), and an anti-rotation component (250). The bearing body (220) is sleeved on a rotating shaft (110), and maintains a predetermined gap wi...
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WO/2021/131167A1 |
The purpose of the present invention is to provide a Co-based alloy product having equivalent or higher mechanical properties to or than those of a precipitation strengthened Ni-based alloy material. The Co-based alloy product according ...
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WO/2021/131647A1 |
A rotating machine (100) according to the present disclosure comprises: a bearing (10); a rotating shaft (20) comprising a hollow part (21) contained inside a portion (20s) supported by the bearing (10); a fluid element (30) attached to ...
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WO/2021/131403A1 |
A plant monitoring device (20) is provided with: a detection value acquisition unit (211) that acquires a bundle of detection values; a first Mahalanobis distance calculation unit (212) that calculates a first Mahalanobis distance by usi...
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WO/2021/124086A1 |
Compressor device (2) provided with at least one compressor element (3) and a drive (4) for the compressor element (3), characterized in that all bearings (6) of at least one shaft in the compressor device (1) configured to carry static ...
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WO/2021/123146A1 |
The invention relates to a turbomachine compressor module (47), comprising an annular row of structural arms (46) defining inter-arm spaces (56) between two circumferentially adjacent arms (46, 48); and an annular row of stator vanes (39...
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WO/2021/123657A1 |
Turbogenerator (1) for an aircraft (2) comprising: - a turboshaft engine (3); - an electric generator (4) comprising a rotor (5) driven mechanically by the turboshaft engine (3) and a stator (6) supported by a housing (7) of the electric...
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WO/2021/121976A1 |
The invention relates to a gas turbine engine (1) of an aircraft, comprising an inner engine region (27) and an outer engine region (28), which delimit a flow cross-section (2) and are operatively interconnected by means of braces (22, 2...
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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/2021/115510A1 |
The invention relates to a rotor (10) for a turbomachine (100), having at least one blade and having at least one rotor main part (20) which has at least one recess (22) in which a blade root (40) of the at least one blade is interlockin...
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WO/2021/116600A1 |
Turbomachine (10) having a contrarotating turbine for aircraft, the turbomachine comprising a contrarotating turbine (22) of which a first rotor (22a) is configured to rotate in a first direction of rotation and is connected to a first t...
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WO/2021/115626A1 |
The composite seal structure includes a carrier ring (33) and a seal element (35) housed in an annular groove formed between a circumferential outer wall and two side walls of the carrier ring (33). The seal element has a first region in...
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WO/2021/117883A1 |
This turbine stator vane extends in the radial direction which intersects the flow direction of steam, and includes a middle surface facing the upstream side in the flow direction, and a back surface facing the downstream side in the flo...
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WO/2021/116556A1 |
Disclosed is a turbomachine (10) with counter-rotating turbine for an aircraft, comprising: - a high-pressure body, - a low-pressure counter-rotating turbine (22), - a planetary-type mechanical epicyclic reduction gear (42), - guide bear...
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WO/2021/116570A1 |
Disclosed is a hydraulic equipment plate (40) for an aeronautical turbomachine comprising channels for fluids to flow into and out of each of the pieces of hydraulic equipment (44, 46, 48, 50, 52), further comprising a part supporting a ...
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WO/2021/116620A1 |
The present invention relates to an aeronautical propulsion system (1) comprising a reduction mechanism (12) that couples a drive shaft (10) and a fan shaft (13) comprising two reduction stages (27, 32) and including: - a sun gear (33), ...
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WO/2021/116578A1 |
Turbomachine (10) with a counter-rotating turbine for an aircraft, the turbomachine comprising a counter-rotating turbine (22) and a mechanical reduction gear (42) with an epicyclic, planetary-type gear train which comprises a planet car...
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WO/2021/116557A1 |
Aircraft turbine engine (10), comprising: - at least one first turbine rotor (22a) connected to a first turbine shaft (36) and comprising rotor blades located in a stream (V), - an annular exhaust casing (28) supporting at least one bear...
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WO/2021/116566A1 |
The invention relates to a blade pivot (2) with adjustable orientation for a turbomachine fan hub, comprising a stud (4) having means (10) for retaining a fan blade root and coupling means for transmitting a torque, a roller bearing (14)...
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WO/2021/116622A1 |
The present invention relates to an aeronautical propulsion system (1) comprising: - a reduction mechanism (12) coupling a drive shaft (10) and a fan shaft (13) and comprising two reduction stages (27, 32) comprising: a sun gear (33), a ...
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