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Matches 1 - 50 out of 22,733

Document Document Title
WO/2019/137022A1
Provided is a rotor system, comprising a rotating shaft (100), wherein the shaft body of the rotating shaft (100) is an integral structure, and the rotating shaft (100) is horizontally arranged; the rotor system also comprises a motor (2...  
WO/2019/137029A1
A rotor system, comprising: a rotating shaft (100), the shaft body of the rotating shaft (100) being an integrated structure, and the rotating shaft (100) being horizontally or vertically disposed; a generator (200), a compressor (300), ...  
WO/2019/138497A1
A turbine rotor blade (3) of the present invention is linked with a rotating shaft and rotated about an axis (AX). The turbine rotor blade (3) is provided with: a hub (31) having a hub surface (32) which is inclined with respect to the a...  
WO/2019/137757A1
The invention relates to a turbine airfoil (20) that extends along a longitudinal axis (LA) of a turbine blade (100), from a radially inner region to a radially outer region of the turbine blade, the airfoil (20) also comprising an outer...  
WO/2019/137023A1
Disclosed is a rotor system, comprising a rotating shaft (100), a shaft body of the rotating shaft (100) being of an integral structure, and the rotating shaft (100) being disposed vertically; and an electric motor (200), a compressor (3...  
WO/2019/136672A1
Disclosed is a turbine blade flange plate based on a spline curve design, comprising a flange plate body (10) having an upper end face (12) and a lower end face (14), wherein the upper end face is connected to a turbine blade (16) and th...  
WO/2019/136674A1
Provided is a turbine blade, comprising a blade body (10), wherein the blade body (10) has a blade tip (12) and a blade root (14); the blade tip (12) has a blade tip plane (20) at the top end of the blade body (10); a concave cavity (26)...  
WO/2019/129996A1
The invention relates to a turbomachine part comprising a substrate consisting of a metal material, or a composite material, and also comprising a layer of a coating for protection against the infiltration of CMAS-type compounds, at leas...  
WO/2019/129457A1
Crack resistance of such ceramic materials is considerably increased by using erbium oxide-stabilized zirconium oxide.  
WO/2019/122657A1
A guide vane (15) in an outer section of a turbofan engine contains oil cooling cavities which are located on one side of a main bending axis (Iz) of the vane (15) so that the differential thermal expansions compensate for the bending de...  
WO/2019/122607A1
The invention relates to a substrate (1) coated on an external surface (6) thereof with an erosion protection layer (3), said protection layer comprising a resin (5) in which are dispersed fibres (7) having an average length of between 5...  
WO/2019/120885A1
The invention relates to a method for measuring a fir-tree-shaped blade root (2) of a turbine blade (3), in which a blade root (2) to be measured having a fir-tree-shaped profile which has a multiplicity of anchoring teeth (6) extending ...  
WO/2019/122691A1
The invention concerns an assembly (1) for a turbomachine comprising: - a first rotor module (2) comprising a first blade (20), - a second rotor module (3), linked to the first rotor module (2), and comprising a second blade shorter than...  
WO/2019/122740A1
Aircraft turbomachine (1) with reduction gearset, comprising a first shaft (15) and a second shaft (3) having the one same axis of rotation, the second shaft being rotationally driven by the first shaft via a reduction gearset (7), the f...  
WO/2019/122540A1
The invention relates to a turbomachine wheel comprising a plurality of radially extending blades connected at one of the radially inner or outer ends thereof to an annular platform carrying annular lips (42, 44) extending from the platf...  
WO/2019/122541A1
The invention relates to a turbine wheel (34) comprising a plurality of blades connected to an annular platform (24) carrying annular lips (36, 38). According to the invention, either the upstream lip (38, 46) or the downstream lip (36) ...  
WO/2019/122741A1
A shaft assembly (22, 32) for an aircraft turbine engine (1), comprising a first outer shaft (32) and a second inner shaft (22), the first outer shaft being intended to be engaged axially on the second shaft and comprising inner longitud...  
WO/2019/100082A9
A system for wirelessly monitoring temperatures of a gas turbine engine comprising a wireless sensor positioned on or in a component of the engine, one or more interrogating antennas capable of transmitting an RF signal to the wireless s...  
WO/2019/115578A1
The invention relates to a vane (1) for a turbomachine rotor comprising a first blade (2) and a second blade (3) arranged to form two successive blades for a bladed rotor, a platform (4) substantially forming an angular wall sector in an...  
WO/2019/118110A1
A cooled turbine blade (440) is disclosed herein. The cooled turbine blade having a base (442) and an airfoil (441), the base including cooling air inlets (481) and channels (483), and the airfoil including an multi bend heat exchange pa...  
WO/2019/115886A1
A turbomachine rotor, comprising a disk carrying vanes, each vane comprising a blade linked by a platform to a root, recesses being defined between the platforms of the vanes and the disk, and vibration dampers being mounted in at least ...  
WO/2019/117290A1
This rotary machine is provided with a rotary shaft that rotates around an axis, and a blade row that comprises a plurality of blades provided at intervals in the circumferential direction of the axis. Each blade has a fiber laminate (9)...  
WO/2019/117752A1
A guide vane for a wet steam turbine comprises a one-piece body. The vane is provided with internal chambers. A continuous internal chamber on the leading edge side is formed by a cavity in the one-piece body and a concave wall that form...  
WO/2019/115977A1
The invention relates to an assembly (1) for a turbomachine, comprising: • a first rotor module (2) comprising a first blade (20), • a second rotor module (3) connected to the first rotor module (2) and comprising a second blade whic...  
WO/2019/115266A1
The invention relates to a moulded body such as, for example, a turbine component of a gas turbine and/or a component of an exhaust gas tract, which are made at least in part of CMC, that is to say ceramic matrix composite, and/or a CMC/...  
WO/2019/112662A1
There is provided a component (100) a ceramic matrix composite portion (58) having a three dimensional surface (68). The ceramic matrix composite portion (58) further includes a ceramic matrix reinforced with a three-dimensional ceramic ...  
WO/2019/109234A1
A turbine structure and a damping member (14) thereof for reducing turbine vibration. A turbine comprises a disc (10) and a plurality of blades (12) installed at the disc (10). Each blade (12) comprises an edge member (16), a main body (...  
WO/2019/110526A1
Sector (7), made of ceramic matrix composite, of a stator (4) of a turbine (1) of a turbomachine (2) comprising an outer platform (8) and an inner platform (9) that are connected via at least one vane, said outer platform (8) comprising ...  
WO/2019/111108A1
The invention relates to a method for repairing a composite substrate (1) and a protection layer (2) comprising at least one thermoplastic polymer and having at least one area of damage (5), the method comprising defining at least one ar...  
WO/2019/105496A1
The invention relates to a component of a flow machine and to a method for producing a component of a flow machine, in particular a gas turbine or an aircraft engine, wherein the component is formed from a fibre-reinforced material, in p...  
WO/2019/108421A1
A torque converter includes a turbine including a plurality of turbine blades and an inner radial extension radially inward from the turbine blades. The torque converter also includes a stator including a plurality of stator blades and a...  
WO/2019/105742A1
An internally-cooled turbomachine component, comprising a main body (200) comprising a first end wall (210), a second end wall (212) spaced apart from the first end wall (210), and a sidewall (220) which extends between the first end wal...  
WO/2019/105672A1
The invention relates to a rotor blade (10) of a turbomachine, comprising a blade root (11), a blade airfoil (12) which has a flow leading edge (13), a flow trailing edge (14), and flow-guiding surfaces (15) extending between the flow le...  
WO/2019/105743A1
An internally-cooled turbomachine component, comprising: a main body (200) comprising; a first end wall (210), a second end wall (212) spaced apart from the first end wall (210), and a sidewall (220) which extends between the first end w...  
WO/2019/108203A1
There is provided a component that includes a core (14) that includes a first material (16) of a metal material (24) or a ceramic matrix composite material (22). A shell (18) surrounds the core (14). The shell (18) is of a second materia...  
WO/2019/108220A1
There is provided a ceramic matrix composite component (10) having a body (12) comprising a ceramic matrix composite material (14) and a plurality of grooves (24, 25, 26) extending from a top surface (16) of the body (12) and into the bo...  
WO/2019/108216A1
A cooled turbine component in a turbine engine is provided. The cooled turbine component includes a brazed in heat transfer feature, the brazed in heat transfer feature including a thin film including a heat transfer feature incorporated...  
WO/2019/102556A1
Provided are a turbine blade (34) and a turbine, wherein the turbine blade (34) is effectively cooled to increase the efficiency of an electric power generation system. According to an embodiment, the turbine blade (34) has an inlet-side...  
WO/2019/101919A1
The present invention relates to a method for producing a multilayer film comprising aluminum, chromium, oxygen and nitrogen, in a vacuum coating chamber, the multilayer film comprising layers of type A and layers of type B deposited alt...  
WO/2019/102137A1
The invention relates to a method for producing a part of a turbomachine coated with a thermal barrier, characterised in that it comprises the following steps: (E1) producing the part by means of additive manufacturing; (E2) electrophore...  
WO/2019/101439A1
The invention relates to a measuring system (1) for sensing the spatial position of a straight securing pin (26) provided with a centering recess (29) at each end-face free end of said securing pin, in particular a securing pin (26) of t...  
WO/2019/097286A1
A labyrinth seal lip (5) comprises, standing on one of its lateral faces (7), a deflector (13) which channels the flow of gas tangent to the lip (5) towards the facing seal (4) so as to disturb the leakage flow (22) through the gap and d...  
WO/2019/099000A1
A gas turbine engine component (10) is repaired via the removal of the defective portion (12) and then the filling in of the resulting cavity (14) with filler material (16). The filler material (16) fills in the cavity (14) via selective...  
WO/2018/080699A8
A propeller blade (18) spanning radially from a root (32) to a tip (34) and spanning axially from a leading edge (36) to a trailing edge (38) spaced from the leading edge forming an airfoil (39) therebetween where a sweep line (62) can b...  
WO/2019/097162A1
The invention relates to a nickel-based superalloy comprising, in weight percentages, 4.0 to 5.5 % rhenium, 1.0 to 3.0 ruthenium, 2.0 to 14.0 % cobalt, 0.3 to 1.0 % molybdenum, 3.0 to 5.0 % chromium, 2.5 to 4.0 % tungsten, 4.5 to 6.5 % a...  
WO/2019/096757A1
The invention concerns a device (2) for holding a centripetal air sampling member (1) for a rotor assembly comprising at least an upstream rotor disc (42a), an adjacent downstream rotor disc (42b) and a centripetal air sampling member (1...  
WO/2019/100082A1
A system for wirelessly monitoring temperatures of a gas turbine engine comprising a wireless sensor positioned on or in a component of the engine, one or more interrogating antennas capable of transmitting an RF signal to the wireless s...  
WO/2019/099009A1
A clearance control system for controlling a clearance between rotating blades and a boundary adjacent to tips of the rotating blades is provided. Electrical heating circuitry (62) may be embedded within or otherwise disposed onto a vane...  
WO/2019/091965A1
A turbine rear structure for a gas turbine engine which comprises primary and secondary exhaust gas guide vanes and wherein the second set of vanes are offset so as to be closer to one of the primary guide vanes than another.  
WO/2019/092679A1
The present invention relates to a method for the construction of rotor and stator elements of turbomachines, comprising: readying an ingot (1) of material to be machined; performing cuts in the ingot (1) so as to delimit blocks (10) of ...  

Matches 1 - 50 out of 22,733