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Patent Searching and Data


Matches 551 - 600 out of 23,220

Document Document Title
WO/2018/093627A2
An assembly comprises a cooling chamber disposed inside an airfoil of a turbine assembly. The cooling chamber is configured to direct cooling air inside of the airfoil. The assembly includes an impingement hole disposed inside the airfoi...  
WO/2018/087808A1
This rotary machine comprises: a pair of radial bearings (102) for supporting a rotating shaft (103) so that the rotating shaft (103) can rotate about a center axis (C); impellers (104) affixed to the rotating shaft (103) at positions se...  
WO/2018/087945A1
A sliding member (10) with an abrasion-resistant coating film is provided with a sliding member (12) and an abrasion-resistant coating film (14) that is provided on the sliding surface of the sliding member (12). The abrasion-resistant c...  
WO/2018/087701A1
The present invention relates to a method for the construction of rotor and stator elements for turbomachinery comprising: preparing a solid (14) of material to be machined; performing cuts (15', 15", 15'", 15"", 22', 22", 22'", 22"") in...  
WO/2018/087452A1
The invention relates to a turbomachine part (30) coated with at least one first thermal barrier layer (33) comprising a ceramic material and first ceramic fibers (34) dispersed in said first layer. The first layer may comprise a gradien...  
WO/2018/087487A1
The invention relates to a process for manufacturing a turbomachine blade (P) of the type having at least one 3D cavity (7), characterized in that said blade is produced by a succession of depositions and selective consolidations of laye...  
WO/2018/087370A1
The invention relates to a turbomachine rotor (10) comprising a radially inner hub element (11), a radially outer cover element (12), and rotor blades (13) which extend between the hub element (11) and the cover element (12) and have rot...  
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/2018/084902A1
A turbofan engine includes a core (30); and a low-pressure turbine (22) configured to drive a fan (46) to produce a fan flow that exits the engine without passing through a turbine. The fan includes a rotor having at least one rotor stag...  
WO/2018/077589A1
The invention relates to a turbine rotor arrangement and to a method of manufacturing a turbine rotor blade. The arrangement comprises a rotor disk (2) and a rotor blade (3) with a blade root (4), the blade root comprising, with respect ...  
WO/2018/080416A1
A turbine airfoil (10) includes a radially extending hollow rib (26) positioned in a radial cavity (40) defined between chord-wise spaced partition walls (24). The hollow rib (26) is spaced from a pressure sidewall (16) and from a suctio...  
WO/2018/080699A1
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/2018/076050A1
A multi-stage axial turbine (typically between 4 and 10 stages) designed to operate more efficiently with partial admission of low temperature steam in each stage except the last one or two stages. Each stage of the subject turbine opera...  
WO/2018/080417A1
Clevis-type pin attachment mounts for ceramic-matric-composite (CMC) blades (50) accommodate varying thermal expansion rates between ceramic blades and the mating engine rotor disc (46). A two-dimensional array of apertures (124, 126, 12...  
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/2017/200648A3
An airfoil (79) for a turbine engine having an engine component including an air supply circuit (124) coupled to a plurality of passages (146) within the outer wall of the engine component where cooling air moves from the air supply circ...  
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/2018/026409A3
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/2018/046423A1
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...  

Matches 551 - 600 out of 23,220