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Matches 1 - 50 out of 21,916

Document Document Title
WO/2018/072971A1
Throughholes having a high contour accuracy are produced by the multiple use of a nanosecond laser without that the interface (17) between the ceramic layer (7) and the substrate (4) is damaged.  
WO/2018/072866A1
The invention relates to a rotor (12) for a turbomachine, in particular of a motor vehicle. The rotor (12) has at least one shaft (14), at least one impeller wheel (16) arranged on the shaft (14) and connected to the shaft (14) for conjo...  
WO/2018/075268A1
A method of forming a cooling hole structure on a turbine component having a component wall with inner and outer surfaces, wherein a cooling hole passes through the component wall and fluidly connects the inner surface and the outer surf...  
WO/2018/075217A1
A propeller assembly includes a central hub including a first forward-facing end, a second aft- facing end, a hub body extending therebetween, and a plurality of channels spaced circumferentially around the central hub. The propeller ass...  
WO/2018/075166A1
An apparatus and system for a propeller assembly are provided. In one aspect, marine propeller assembly includes a plurality of circumferentially-spaced blades that each include a dovetail having a radially inner surface. The marine prop...  
WO/2018/073538A1
The invention relates to a method for coating at least one surface of a solid substrate with at least one layer comprising at least one ceramic compound by a suspension plasma spraying (SPS) technique, in which at least one suspension of...  
WO/2018/073535A1
The invention relates to a turbine blade of a turbine engine such as a turbojet engine, comprising: a root supporting a blade and extending in a wingspan direction, ending in a vertex, the blade comprising a leading edge (17) and a trail...  
WO/2018/075163A1
A propeller assembly that includes a hub having an outer radial surface and a plurality of wedge retaining members removably coupled to the hub. The plurality of wedge retaining members are spaced circumferentially about the outer radial...  
WO/2018/071174A1
A maintenance apparatus includes a flexible carriage configured to anchor between adjacent airfoils of a turbine assembly. The maintenance apparatus includes a maintenance tool operably coupled with the flexible carriage. The maintenance...  
WO/2018/069552A1
The invention relates to an integrally cast turbomachine assembly (100). The turbomachine assembly comprises a hub element (101) which extends coaxially to a hub element axis (102) of the turbomachine assembly (100). The turbomachine ass...  
WO/2018/071073A1
A component (40) is provided for a turbine engine. The component can include an airfoil defining a surface (101) and an energy absorbing composite (114) positioned on the surface of the airfoil or within the airfoil. The energy absorbing...  
WO/2018/067345A1
A method of assembling an electrified turbocharger comprising assembling a rotor assembly onto a shaft; balancing the shaft and rotor assembly; attaching at least one bearing onto the shaft adjacent the rotor assembly; inserting a stator...  
WO/2018/066643A1
This method for producing turbine vane includes a brazing step in which a turbine vane substrate having a brazing material positioned thereupon is heated to melt the brazing material and bond the same to the substrate, a stabilization st...  
WO/2018/066330A1
To minimize peeling of a thermal barrier coating film in an environment containing sulfates. This thermal barrier coating film (40) has: a bond coating layer (50), which is a metal binding layer formed on a base material (110); a top coa...  
WO/2018/066644A1
This method for producing turbine vane includes a brazing step in which, in a state in which the substrate of a turbine vane having a brazing material positioned thereupon is positioned within a predetermined furnace having a heater, the...  
WO/2018/065159A1
The invention relates to a method for replacing an aircraft part; in particular an aircraft turbine engine; the method comprising the following steps: (a) deciding (100) to replace a part, in particular a faulty part; (b) landing (102) t...  
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 ...  

Matches 1 - 50 out of 21,916