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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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.
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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...
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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....
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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: - ...
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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 ...
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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...
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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 ...
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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...
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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...
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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 ...
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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...
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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...
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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)...
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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 ...
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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...
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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...
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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 ...
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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 ...
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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...
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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)...
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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...
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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...
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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...
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