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Patent Searching and Data


Matches 151 - 200 out of 22,241

Document Document Title
WO/2018/065739A1
A movable ring assembly (4) for a turbine engine turbine (10) that is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b) being fixed to each other by bolting, characterised i...  
WO/2018/066392A1
This method for producing turbine vane comprises: a step for forming, on the surface of the substrate of a turbine vane formed using a Ni alloy material, an undercoat using a metal material having a higher oxidation resistance than the s...  
WO/2018/060200A1
Cooled machine component, particularly a turbomachine component, comprising a body (2) with at least one integrated cooling channel (40) for guiding a cooling fluid through an interior of the body, the cooling channel comprising a lattic...  
WO/2018/060030A1
A rotating device for a compressor of a gas turbine is presented. The rotating device, connectible with the compressor, includes a first shaft, a second shaft, rotatable blades, a bearing assembly, an external drive and an input port for...  
WO/2018/060068A1
The invention relates to an impeller (14) for a continuous-flow machine (10), in particular a radial continuous-flow machine. The impeller (14) has a number of blades (16), which are received spaced apart from each other on the circumfer...  
WO/2018/060627A1
Aeronautical turbine blade (10) comprising pressure-face-side cavities and suction-face-side cavities extending radially, and at least one central cavity situated in the central part of the blade (10) and surrounded by pressure-face-side...  
WO/2018/063353A1
A squealer tip (30) for a turbine blade (1) includes a tip cap (32) disposed over an airfoil outer wall (12), a pressure side tip wall (34) extending radially from the tip cap (32) and aligned with an outer surface (14a) of an airfoil pr...  
WO/2018/060782A1
A system for increasing the efficiency of low pressure axial fans, includes, a low pressure axial fan including multiple first blades, and, a vortex generator operably coupled to the low pressure axial fan via a shaft. In use, the vortex...  
WO/2018/063885A1
The present disclosure is directed to a method for scaling an airfoil (200) for placement in a turbomachine. The method disclosed herein includes radially scaling a master airfoil (200) to form a scaled airfoil (202). The method may also...  
WO/2018/055403A1
The invention relates to an axial turbine with a rotating casing (2, 4) and stationary shaft (6, 8), sections for the assembly thereof, and materials for the manufacture thereof.  
WO/2018/055375A1
A mixed-flow turbine wheel (214) is proposed which, compared to existing mixed-flow turbine wheels, has reduced mass and moment of inertia because radially-outer portions of existing mixed-flow turbine wheels are omitted. In a first poss...  
WO/2018/054631A1
By using a water-based liquid mixture (13) containing amino acids, the cavities (10) of a hollow component (1) can be filled very easily and very quickly, while nevertheless providing the internal structure (22) with adequate protection....  
WO/2018/057414A1
A method includes masking at least one hole of an article with a paste, wherein the hole opens onto a surface of the article, applying a coating to the surface of the article, and removing the paste including contacting the paste with wa...  
WO/2018/050467A1
A method for low-speed balancing of a rotor having at least one compressor stage blades assembly is presented. The assembly has a row of blades circumferentially arranged and includes a circumferential clearance. Two or more blades are i...  
WO/2018/046423A1
The invention relates to methods for clear position determination and identification of a turbine blade (11) of a high-pressure turbine stage (10) of a gas turbine (1), particularly an aircraft engine, in the mounted state. The method fo...  
WO/2018/046936A1
A blade or wing element includes a plurality of ribs (20) rotatable and/or slidable with respect to one another whereby to vary the aerodynamic configuration of the blade or wing element by causing a twist thereof. A blade or wing or bla...  
WO/2018/047523A1
Provided is a coating method, a coating film, and a turbine shroud. The present invention includes: a slurry deposition step of depositing a slurry containing a coarsely particulate ceramic and a finely particulate ceramic on a base mate...  
WO/2018/046976A1
Axial airplane airscrew-, fan-, and wind turbine blade of low loading characterised by the fact that the aspect ratio of the airscrew-, fan- and wind turbine blades is low; near to the wide blade ends, but in an appropriate distance an a...  
WO/2018/046182A1
The invention relates to a rotor (1) for a turbine, wherein the rotor (1) consists of a single-piece main body (2). The main body (2) has a shaft (4), a front wall (5), and a rear wall (6). A plurality of blades (7) is arranged on the fr...  
WO/2018/046209A1
The invention relates to a machining device (13) for machining a rotor arranged in a turbine housing which consists of two parts, thereby forming a joint (11), in situ while the upper housing half is removed, comprising the following: - ...  
WO/2018/048486A1
A coating system for a surface of a superalloy component is provided. The coating system includes a MCrAlY coating on the surface of the superalloy component, where M is Ni, Fe, Co, or a combination thereof. The MCrAlY coating generally ...  
WO/2018/045116A1
An airfoil body may include a plurality of tubercles along a leading edge of the airfoil body and a plurality of crenulations along a trailing edge of the airfoil body, wherein at least one of a position, a size, and a shape of the plura...  
WO/2018/045033A1
A turbine rotor blade with a closed loop cooling circuit for an industrial gas turbine engine in which cooling air for the rotor blade is supplied and carried away to and from the rotor blade through the rotor shaft, and where the rotor ...  
WO/2018/041896A1
The invention relates to a method and a system for the production of blades (1) of a machine interacting with a fluid, in particular a fluid-driven machine, in particular a wind turbine, comprising a test device (19) for determining geom...  
WO/2018/040094A1
A rotary inertial impeller comprises a shaft (1) and a blade. An inner end of the blade is connected to the shaft (1). The blade is an ordinary blade or an inertial blade (7). A rotation radius R0 of the inertial blade (7) is greater tha...  
WO/2018/044270A1
A rotor stage (10) of a turbine engine includes a circumferential row of rotor segments (12), each including: first and second endwalls (14, 16) spaced apart radially, and a first and second sidewalls (18, 20) extending radially between ...  
WO/2018/044271A1
A stator stage (10) of a turbine engine includes a circumferential row of flow directing structures (12), each including: an inner endwall (14) and an outer endwall (16) spaced apart radially, and a pressure sidewall (18) and a suction s...  
WO/2018/038507A1
Disclosed is a gas turbine blade. The gas turbine blade according to one embodiment of the present invention comprises: a turbine blade (33) provided in a gas turbine; and cooling units (110), each having a cooling channel (110) for cool...  
WO/2018/036719A1
A turbomachine arrangement with a platform cooling device for a blade of a turbomachine The invention is directed to a turbomachine arrangement comprising a blade (1) of a turbomachine and a platform cooling device (10) for the blade (1)...  
WO/2018/036710A1
The invention relates to a rotor blade (1) for a turbine (2), having a blade region (3), a rotor blade longitudinal axis (4) and a fir-tree root (5), arranged at the blade region (2) and extending along the rotor blade longitudinal axis ...  
WO/2018/038992A1
A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. The rotary component is rotatable with the compressor section and the turbine section. The gas turbine engine additionally in...  
WO/2018/038457A1
Disclosed is a gas turbine blade. The gas turbine blade according to one embodiment of the present invention comprises: a turbine blade provided in a gas turbine; and a plurality of film cooling units from the leading edge to trailing ed...  
WO/2018/038994A1
The present invention is directed to repair compositions for thermal barrier coatings and methods of use thereof. The repair compositions include a ceramic composition, a colloidal solution, an aqueous binder, an aqueous dispersant, and ...  
WO/2018/036818A1
The invention relates to a rotor of a gas turbine, comprising a first rotor disk (01) and a second rotor disk (02), between which a sealing ring formed by sealing segments (31) is arranged. For fastening, according to the invention, the ...  
WO/2018/038151A1
Provided are: a multilayer structure which has achieved a good balance between erosion resistance and fouling resistance; and a component for rotary machines, which has this multilayer structure. A multilayer structure 1 according to the...  
WO/2018/034791A1
An apparatus and method for cooling an engine component such as a turbine engine airfoil, including a wall (120) bounding an interior extending axially between a leading edge and a trailing edge and radially between a root and a tip (98)...  
WO/2018/035021A1
A turbocharger (20) includes a turbine housing (22) defining a turbine housing interior (24), a turbine wheel (26) disposed within the turbine housing interior (24), a shaft (28) coupled to and rotatable by the turbine wheel (26), a comp...  
WO/2018/034790A1
A component for a turbine engine and method for providing a cooling film on a turbine engine component, including an outer wall separating a hot fluid flow from a cooling fluid flow, using the cooling fluid flow to cool the engine compon...  
WO/2018/034778A1
An airfoil (90) for a turbine engine (10) comprises a wall bounding an interior (100) and defining a pressure sidewall and a suction sidewall, extending chord-wise from a leading edge to a trailing edge and span-wise from a root to a tip...  
WO/2018/031032A1
Airfoil outer wall thickness of a gas turbine engine blade is initially increased in a zone that is proximate the trailing edge and blade hub greater than comparable greatest wall thickness anywhere else along the trailing edge from outb...  
WO/2018/029770A1
This steam turbine blade is provided with a blade body (70) that is disposed inside a steam main flow channel formed around a rotor shaft that rotates about an axis so that main steam flows through, the blade body (70) having an airfoil ...  
WO/2018/029060A1
The invention relates to a method for joining materials, comprising: providing a first material (W1) and a second material (W2), providing the first material (W1) with a grid structure (GS) at a joining point (VS), and joining, in partic...  
WO/2018/029408A1
An aspect of the invention relates to a turbo engine rotor disc that has a rotation axis and comprises, at the periphery thereof, a plurality of slots (10) regularly distributed around the rotation axis, the turbo engine rotor disc being...  
WO/2018/026409A3
A processing system having at least one processor operatively coupled to at least one memory. The processor receives sensor data from the at least one sensor indicating one or more characteristics of the asset. The processor generates, u...  
WO/2018/026494A1
An article includes a substrate that is substantially opaque to visible light and a coating disposed on the substrate. The coating includes a coating material having an inherent index of refraction, wherein the coating has an effective i...  
WO/2018/024759A1
The invention relates to a method for producing a channel structure (200) for a turbomachine, comprising the additive production of webs (2) from a first material on a main body (1), wherein the webs (2) are constructed on the main body ...  
WO/2018/026413A3
An apparatus and method for a turbine engine including an engine core having a compressor section, a combustor, and a turbine section, which are arranged to define a stator and rotor. The engine further includes a swirler to increase the...  
WO/2018/026579A1
Provided is a method including obtaining ceramic matrix composite (CMC) with a first matrix portion including a silicon carbide and silicon phase dispersed therewithin, disposing a coating thereupon to form a sealed part, and forming the...  
WO/2018/022055A1
A turbine airfoil (10) includes an elongated hollow body (26) defining a radial cavity (T1, T2) positioned in an airfoil interior (11). A pair of radial flow passes (B,E/C,D) incorporating near-wall cooling (72, 74) channels are formed o...  
WO/2018/022224A3
The present disclosure is directed to an engine component for a gas turbine engine, the engine component including a substrate that includes a composite fiber and defines a surface. An energy harvesting fiber is positioned within the sub...  

Matches 151 - 200 out of 22,241