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Matches 51 - 100 out of 22,128

Document Document Title
WO/2018/110827A1
The present invention provides a partial admission operation turbine apparatus comprising: a rotor portion rotatably coupled to a rotary shaft of a turbine and including a plurality of rotor blades; a nozzle portion fixedly coupled to th...  
WO/2018/110584A1
This gas turbine disassembling/assembling method comprises a seal plate restriction state switching step for switching between a seal plate unrestricted state where a seal plate movement restriction part does not restrict radial movement...  
WO/2018/103990A1
Intermediate bond-coat layer for improvement of adherence of a thermal barrier coating on a ceramic matrix composite substrate By application of aluminum or aluminum alloy (7') in an intermediate step a good ceramic coating (7) in an adh...  
WO/2018/104678A1
The invention proposes a method for simulating the distribution of blades on a turbomachine disc, the method comprising the steps of:â‹…providing a plurality of blade configurations, each blade configuration being associated with a blade...  
WO/2018/103995A1
The invention relates to a method for producing a gas turbine component (1), which, during gas turbine operation in the mounted state as intended, comes into frictional contact with at least one friction partner, wherein the method has t...  
WO/2018/106539A1
A separation assembly comprises a housing, a jet that expels a fluid within the housing, and a turbine positioned within the housing. The fluid causes the turbine to rotate about a center rotational axis within the housing. The turbine c...  
WO/2018/103994A1
The use of magnesium oxide, reactive alumina and aluminium oxide as a base provides for a new erosion-resistant material upon sintering.  
WO/2018/103996A1
Continuous cracks can be optimally repaired using CMT technology by using a fluxed-core wire of solder material with a filling consisting of solder material and base material.  
WO/2018/101632A1
The disclosure relates to a carbon blade for a wind turbine with multiple down conductors, and more particularly, to a carbon blade for a wind turbine with multiple down conductors that includes multiple down conductors disposed thereon ...  
WO/2018/101303A1
This gas turbine high-temperature component is provided with: a body; a porous part through which a cooling gas can pass and which is provided as at least a part of the body or on at least a part of the body; and at least one filter that...  
WO/2018/100160A1
The invention relates to a gas turbine having at least one disk (5), wherein turbine blade elements (1) are connected by a connecting means (2) to the at least one disk (5), characterized in that the connecting means (2) in the interior ...  
WO/2018/101190A1
A high-temperature component (10) for a gas turbine is provided with a main body part (40) and a porous part (42) through which a cooling gas can pass, and is configured such that, in accordance with one or both distributions of a heat l...  
WO/2018/095708A1
By roughening the surface of a CMC substrate with a plasma spray device using the same plasma gun for roughening and coating by adjusting spraying parameters, good adhering and coating of the ceramic layer on a CMC substrate is yielded o...  
WO/2018/094536A1
The present disclosure generally relates to rotary turbomachinery methods and integrated processes requiring high-energy efficiency. In one embodiment, the present invention relates to rim-rotor configurations enabling long-term survival...  
WO/2018/097832A1
The present invention generally relates to high g-field combustion methods and integrated processes requiring high-energy efficiency and low NOx emissions to maximize fuel productivity and integrated process production output. In one emb...  
WO/2018/093808A1
A turbocharger turbine wheel member with stiffener members thereon, together with a method of manufacture therefor are disclosed. The stiffener members are molded integrally on the turbine wheel blade members. The stiffener members, as w...  
WO/2018/093473A1
Various aspects include a turbomachine bucket (20), such as a steam turbine bucket, a corresponding shim (52) and a related turbine rotor. The steam turbine bucket includes a blade (22) having a first end, and a second end opposite the f...  
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/2018/093627A3
An assembly comprises a cooling chamber (102) disposed inside an airfoil (100) of a turbine assembly. The cooling chamber (102) is configured to direct cooling air inside of the airfoil (100). The assembly includes an impingement hole (1...  
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/2018/084902A1
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/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...  

Matches 51 - 100 out of 22,128