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Patent Searching and Data


Matches 351 - 400 out of 23,247

Document Document Title
WO/2019/036222A1
A turbine blade tip (30) includes a tip cap (32) disposed over a blade airfoil (10) and having a pressure side edge (44) and a suction side edge (46). A notch (50) is formed by a radially inward step adjacent to the suction side edge (46...  
WO/2019/035800A1
A blade tip (30) for a turbine blade (1) includes a tip cap (32) disposed over an airfoil outer wall (12) and at least one squealer tip wall (34, 36) extending radially outward of the tip cap (32) and extending along a chord-wise directi...  
WO/2019/035813A1
A cored filler wire (10) used in a laser metal deposition (LMD) process and method of using the same. The cored filler wire includes an outer shell (12) surrounding an inner filler material (14). The outer shell is formed from a first ma...  
WO/2019/035802A1
A turbine blade tip (30) includes a squealer tip wall (34) having a forward surface (34b) that is continuous with an outer surface (14b) of an airfoil pressure sidewall (14). A plurality of cooling channels (50) are provided spaced apart...  
WO/2019/030314A1
A component (300, 400) for use in a turbomachine is provided. The component (300, 400) comprises a platform (310, 410) having a leading end (312, 412) longitudinally spaced apart from a trailing end (312, 412), an aerofoil portion (320, ...  
WO/2019/032356A1
Systems and methods for monitoring components are provided. A component has an exterior surface. A method includes performing a first analysis of a first image of a surface feature configured on the exterior surface of the component, the...  
WO/2019/030210A1
An iron-based alloy is described. Also described is a component having a surface layer 12 of an iron-based alloy, a method of providing a surface layer of an iron-based alloy on a component, an apparatus arranged to provide a surface lay...  
WO/2019/030201A1
The invention relates to a functional structure (1) for use in an energy converter and/or a turbomachine. The structure (1) comprises a lattice comprising at least one lattice cell (2), comprising lattice nodes (3) and lattice connecting...  
WO/2019/029968A1
Method of additively manufacturing a structure on a pre- existing component out of the powder bed A method of additive manufacturing a structure (1) on a pre- existing component (2) is provided, the method comprising disposing the pre-ex...  
WO/2019/032364A1
A process includes agitating at least one core of a core alloy together with a braze binder to form at least one coated core comprising the at least one core coated with a first layer of the braze binder. The process also includes agitat...  
WO/2019/027661A1
A gas turbine (10) includes a turbine section (24), and a diffuser (30) located downstream of a row of turbine blades (26) of the turbine section (24). The diffuser (30) includes an annular duct (34) extending axially along a diffuser ax...  
WO/2019/028208A1
A turbine component (1) such as a blade or vane includes at least one platform (6) provided with a platform cooling circuit (30). The platform cooling circuit (30) includes an inlet (32) for receiving a coolant (K), and a cooling channel...  
WO/2019/025194A1
A method of manufacturing a test piece (300) for testing a rotor blade design (200) for a turbomachine, the test piece comprising: a plurality of monolithically-formed body portions. There is provided a main body portion (302) correspond...  
WO/2018/236618A3
A repair method (72) for extending a service life of a power turbine disk (12) having corrosion damage, wherein the power turbine (14) includes stages (16, 18, 20, 22) and interstage gaps (26, 28, 30, 32). The method (72) includes conduc...  
WO/2018/215370A3
A rotor disc retention assembly of a gas turbine engine is presented. The assembly includes, a tension bolt, a rotor disc including a hub, a web, a blade retention arrangement, a rotational axis, a first axial side and a second axial sid...  
WO/2019/020287A1
The invention relates to a turbomachine (10), in particular for a fuel cell system (1). The turbomachine (10) comprises an impeller wheel (15) arranged on a shaft (14). The impeller wheel (15) is designed as a radial impeller, and a work...  
WO/2019/020289A1
The invention relates to a turbomachine (10), in particular for a fuel cell system (1). The turbomachine (10) comprises a shaft (14), an impeller wheel (15) and an axial bearing disk (30). The impeller wheel (15) and the axial bearing di...  
WO/2019/018220A1
Systems can be used to harness energy from winds. For example, this document describes scalable systems having multiple wing-like blades that can efficiently convert wind power into electricity and other types of energy.  
WO/2019/010964A1
Disclosed is a recess-film hole cooling structure for cooling turbine blades, the structure comprising a recess (2) provided in an inner wall of a cooling blade (1), and a film hole (3) passing through the cooling blade (1), wherein the ...  
WO/2019/013178A1
The purpose of the present invention is to reduce a loss in motion energy causing rotor blades rotate, the loss being due to interference between a leakage flow at the distal end of the rotor blade and a main flow causing the rotor blade...  
WO/2019/012102A1
Compressor blade (42) for an axial compressor (10), comprising a blade root (19) and a cantilevered airfoil (20) attached to said blade root (19), the airfoil (20, 22) comprising a suction side and a pressure side extending in a span dir...  
WO/2019/012168A1
The invention relates to a system for propelling ships by means of tubes having respective helical mechanisms inside, of different gauges, which propel the water through said tubes in a turbulance-free manner and at great speed, and char...  
WO/2019/011535A1
The invention relates to a method for machining a component (2) by removing material, in particular by removing chips, in particular within a groove (1) provided in the component, in which method: spatially resolved measurement data, whi...  
WO/2019/008724A1
[Problem] To provide a turbine wherein an anti-rotation structure is prevented from being damaged by a high-temperature operating fluid, thereby preventing deterioration in the anti-rotation function. [Solution] A turbine according to an...  
WO/2019/009331A1
This turbine blade comprises: a blade part; a cooling passage that extends along a blade height direction on the inside of the blade part; a plurality of cooling holes that are formed in a trailing edge part of the blade part so that the...  
WO/2019/008656A1
This turbine blade (34) is provided with: a plurality of cooling holes (47) formed in the turbine blade (34), each of the cooling holes (47) having an inflow opening (47a), an outflow opening, and a flow passage (47b) which is formed bet...  
WO/2019/008294A1
The invention concerns an assembly comprising a shaft (12) and an element (16) configured to be coupled on the shaft (12) by shrink-fitting, the shaft (12) comprising an inner cavity (20) in an axial shrink-fitting portion (P12), an inte...  
WO/2019/004272A1
After a free-form surface has been machined on an elongate material 1 in a state in which a protruding portion 3 and a blade 4 are being gripped, the entire elongate material 1 deforms when gripping of the protruding portion 3 is release...  
WO/2019/005425A1
A turbine airfoil (10) includes a trailing edge coolant cavity (40f) located in an airfoil interior (11) between a pressure sidewall (14) and a suction sidewall (16). The trailing edge coolant cavity (40f) is positioned adjacent to and e...  
WO/2019/002274A1
The invention is directed to a turbomachine component (1), particularly an aerofoil (5), more particularly an aerofoil (5) of a blade (38) or a vane (40) for a gas turbine engine (10), the turbomachine component (1) comprising a first ca...  
WO/2019/001980A1
A compressor aerofoil (70) for a turbine engine. The compressor aerofoil (70) comprises a root portion (72) spaced apart from a tip portion (100) by a main body portion (102). The main body portion (102) is defined by : a suction surface...  
WO/2019/001979A1
A compressor aerofoil (70) rotor blade for a turbine engine. The compressor aerofoil (70) comprises: a root portion (72) spaced apart from a tip portion (100) by a main body portion (102). The main body portion (102) is defined by : a su...  
WO/2019/001981A1
The present invention relates to a turbine assembly (10) and a method of assembling such an assembly. The turbine assembly (10) comprises a basically hollow aerofoil (12), an impingement tube (15), and an impingement tube sleeve (200). T...  
WO/2019/003590A1
This turbine blade comprises: a blade part which has a hollow part extending along a blade height direction, and in which is formed a plurality of film-cooling holes aligned along the blade height direction; and an insert which is provid...  
WO/2019/005121A1
The present invention is directed to a component (10) including a substrate (12) of a ceramic matrix composite material (14); a thermal barrier coating layer (18) disposed over the substrate (12); and an intermediate thermal protection a...  
WO/2018/208370A3
The present invention relates to n integrated airfoil and platform cooling system (30) for a turbine rotor blade (10), includes a plurality of serpentine cooling legs (32a, 32c, 42a, 42c) fluidly connected to an inlet (38, 48) and config...  
WO/2018/237101A1
The present invention is generally related to the attachment of ceramic matrix composite high pressure turbine blades to a rotor disk. To improve structural integrity and minimize interlaminar tensile stress, a root attachment (10) havin...  
WO/2018/232539A1
The present invention relates to a high-speed dewatering and pulverising turbine (1) for obtaining solid pulverised particles and separating the water present, which is formed by: a) a stator (6) having circular geometry with a duct (7) ...  
WO/2018/236618A2
A repair method (72) for extending a service life of a power turbine disk (12) having corrosion damage, wherein the power turbine (14) includes stages (16, 18, 20, 22) and interstage gaps (26, 28, 30, 32). The method (72) includes conduc...  
WO/2018/229409A1
A coated turbomachine part comprises a substrate (21) and a layer for protection against the calcium and magnesium aluminosilicates CMAS (24) present on the substrate (21). The layer (24) comprises a first phase (240) of a material for p...  
WO/2018/230411A1
An axial flow rotating machine is provided with: a rotor (20); a plurality of stator vanes (42); and a medium flow modification member (60). The stator vanes (42) include an inner shroud (44) and one or more seal fins (49). A rotor shaft...  
WO/2018/189434A3
The invention relates to an aviation turbine blade (10), characterised in that it comprises at least a first lower surface cavity (C2) and a first upper surface cavity (C3), each adjacent to a first through-cavity (C1) and a second throu...  
WO/2018/189433A3
The invention relates to an aviation turbine blade (10) extending radially from a blade root (14) as far as an upper partition wall (26), said blade (10) comprising a plurality of inner cavities (C1-C10) defining at least one cooling cir...  
WO/2018/229406A1
A coated turbomachine part (20) comprises a substrate (21) and a layer for protection against the calcium and magnesium aluminosilicates CMAS (22) present on the substrate (21). The protective layer (22) comprises a first phase (220) of ...  
WO/2018/185070A3
The invention relates to a turbine blade (12, 30) for a gas turbine, comprising a wall, which can be exposed to a corrosive hot gas during intended use of the turbine blade, is partially made from a cast material and is designed as a bla...  
WO/2018/186921A3
A component for a turbine engine comprises a wall with a surface along which a hot airflow passes, a second surface along which a cooling airflow passes, and an insert mounted to the wall wherein the material used for the insert can have...  
WO/2018/226219A1
Methods (1000) for structural braze repair of damaged industrial machine components, e.g., gas turbine engine components (10). The method includes the step of placing a bilayer braze material (200) onto a surface (12) of the component. T...  
WO/2018/224574A1
The invention relates to a turbine blade (1) for a gas turbine, comprising a blade platform (2) and a blade body (3) which protrudes in a longitudinal direction (L) from the blade platform (2), has a circumferential wall (4) with a sucti...  
WO/2018/222326A1
A blade (10) for a turbine engine that includes an internal cooling system (56) formed from at least one cavity (58) positioned within a generally elongated airfoil (12). A squealer tip (36) and at least one densified oxide dispersion st...  
WO/2018/221597A1
The present invention minimizes decreases in strength in a blade root section when a composite material is used in a moving blade. Provided is a composite material blade (1) that is formed by layering composite material layers in which r...  

Matches 351 - 400 out of 23,247