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Matches 1 - 50 out of 22,962

Document Document Title
WO/2019/214925A1
A rotor balancing method for a gas turbine is provided. The method comprises providing a rotor (100) comprising a first correction plane (152) and a second correction plane (154), wherein a first balancing weight (W1) is attached to the ...  
WO/2019/214923A1
There is provided a rotor balancing method for a gas turbine. The method comprises providing a rotor (100) comprising: a first bearing (140) and a second bearing (142), and a plurality of correction planes (150) comprising a first correc...  
WO/2019/214915A1
The invention relates to a turbine engine extending longitudinally along an X axis and including a main duct (V) in which an air stream (F) flows, the turbine engine including at least one upstream compressor disc (1A), at least one down...  
WO/2019/211427A1
The invention relates to an aerofoil (16) for a turbine blade, comprising a leading edge (18) onto which a hot gas (S) can flow and from which a suction-side wall (17) and a pressure-side wall (19) extend to a trailing edge (20) of the a...  
WO/2019/212479A1
The present disclosure is directed to methods for manufacturing wind turbine rotor blades and components thereof, e.g. using 3D printing. In one embodiment, the method includes forming a rotor blade structure having a first surface and a...  
WO/2019/212456A1
The present disclosure is directed to vortex generators for wind turbine rotor blades having noise-reducing features. For example, the vortex generators are mounted within a laminar flow region on either the pressure side or the suction ...  
WO/2019/210997A1
The present invention provides an in-situ boroblending tool (1) for the computer-assisted (automated) blend repair of an airfoil of a turbomachine. The tool (1) comprises a flexible borescope line (2) which is connected to a robotic head...  
WO/2019/212529A1
A weld filler is proposed which significantly improves the weldability of some nickel-based superalloys and includes the following constituents (in wt%): 11.2% - 15.6% chromium (Cr), 9.6% - 11.4% cobalt (Co) 2.4% - 5.0%, molybdenum (Mo) ...  
WO/2019/211091A1
The invention relates to a rotor for a gas turbine having a rotor disk (01) on which there are a plurality of rotor components (11) distributed around the circumference. The rotor disk (11) has a circumferential securing shoulder (04) wi...  
WO/2019/212533A1
A repaired gas turbine blade includes a blade root, a platform coupled to the root, an airfoil portion that extends from the platform and includes a leading edge that extends from the platform, and a damaged portion, and a replacement pi...  
WO/2019/211082A1
The invention relates to a component wall (10) of a hot gas component for a gas turbine, which in a double-walled design, comprises an outer wall (12) which is hotter during operation and an inner wall (14) which is cooler during operati...  
WO/2019/212530A1
A method of forming alloy welding consumables for use in welding a base material includes providing a plurality of first welding consumables having a first diameter and a first chemical composition that closely matches the base material ...  
WO/2019/212384A1
The group of inventions relates to the field of gas turbine engines and steam turbines, particularly to designs for fans, axial compressors, and gas or steam turbines. The technical result of the inventions consists in creating a working...  
WO/2019/212478A1
The present invention relates to a tip section (30) for a turbine blade (1) including a tip cap (32) and at least one squealer tip wall (34, 36) extending radially outward from the tip cap (32). A plurality of cooling channels (50, 60, 7...  
WO/2019/209401A1
Using the systems and methods discussed herein, CMAS corrosion is inhibited via CMAS interception in an engine environment and/or is prevented or reduced by the formation of a metal oxide protective coating on a hot engine section compon...  
WO/2019/209267A1
There is provided a component (110) comprising a plurality of ceramic matrix composite members (111) stacked on one another to define an airfoil (116). The airfoil (116) has a radial axis (130) extending therethrough and a horizontal axi...  
WO/2019/206747A1
A compressor aerofoil (70) for a turbine engine. The compressor aerofoil (70) comprises a tip portion (100) which extends in a first direction R b from a main body portion (102). The main body portion (102) is defined by a suction surfac...  
WO/2019/204493A1
Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational ...  
WO/2019/203826A1
A turbine blade (10) includes a root (15), a platform (20) coupled to the root (15), and an airfoil coupled to the platform (20). The root (15), the platform (20), and the airfoil are formed as one continuous piece from a Ceramic Matrix ...  
WO/2019/201889A1
The invention relates to a coating composition for coating turbomachine components or compressor components, which are subjected to the fluid flow of the turbomachine. The invention furthermore relates to a component of a turbomachine or...  
WO/2019/202259A2
Turbine (1) for a turbomachine, comprising a casing (4) and a turbine nozzle diaphragm stage (2), the nozzle diaphragm stage (2) of the turbine (1) comprising an outer metallic ferrule (9) firmly joined to the casing (4), an inner metall...  
WO/2019/203819A1
A locking spacer assembly (200) for filling a final spacer slot (144) in a disk groove (142) between platforms (122) of adjacent blades (120) of a blade assembly (100) in an industrial gas turbine engine is presented. The locking spacer ...  
WO/2019/202281A1
The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surface extending between a leading edge and ...  
WO/2019/204265A1
A separation assembly comprises a housing, a jet that expels a fluid within the housing, and a turbine assembly positioned within the housing and positioned so as to be contacted by the fluid expelled from the jet. The fluid causes the t...  
WO/2019/201519A1
A rotor shaft cap (300) for a gas turbine, comprising: a disk-shaped body (310) defining: a first axial face (312), a second axial face (314), and an outer radial face (316), the disk-shaped body (310) comprising: a first annular jaw (33...  
WO/2019/203158A1
This turbine blade is provided with: a blade body; a cooling passage extending along a blade height direction inside the blade body; and a plurality of turbulators provided to an inner wall surface of the cooling passage and arrayed alon...  
WO/2019/202249A2
A turbine (1) of a turbomachine comprises a case (4) and a distributor stage (2) having an outer metallic collar (9) secured to the case (4), an inner metallic collar (5), and a plurality of segments (20) of a ring which are made of a ce...  
WO/2019/199320A1
A bladed rotor system (1) includes first and second sets (H, L) of blades (2) with respective airfoils (10) each having at least one internal cavity (22, 24, 26). The airfoils (10) of both the first and second sets (H, L) of blades (2) h...  
WO/2019/197750A1
The invention concerns an aircraft turbomachine, comprising at least one tubular element (12), such as a rotor shaft, and at least one rotor wheel extending around said tubular element (12) and comprising a disk (8b) carrying, at the out...  
WO/2019/198793A1
This valve opening degree determining device determines the valve opening degree of a cooling air adjustment valve for controlling the supply of cooling air to a disk cavity, the valve opening degree determining device being provided wit...  
WO/2019/192800A1
An improved oxidation protection for the use at high temperatures is ensured by a corresponding coating, in particular on the basis of aluminum of a product of a MAX phase.  
WO/2019/133112A3
A positioning device (102) is presented. The positioning device (102) includes an articulation assembly (128) including a tubular structure (150) including an aperture at a distal end and a first connector (134, 504) on an outer surface....  
WO/2019/192871A1
The invention relates to a method for designing, constructing and producing the skeleton of turbine-impeller-reactor wheels which employ simultaneously, in the same wheel, the principles of the turbine, the impeller, and the reactor, and...  
WO/2019/194878A2
The present invention relates to a gas turbine blade (1) having a casted metal airfoil (2), said airfoil (2) comprising a main wall defining at least one interior cavity (9), having a first side wall (3) and a second side wall (4), which...  
WO/2019/186220A1
The invention relates to a system for protecting a leading edge on a wind turbine rotor blade, a vacuum sheet for use in the system and a method for, in situ, protecting a part of a leading edge of a wind turbine rotor blade. The system ...  
WO/2019/190802A1
This disclosure provides a cross key anti rotation spacer for use in a gas turbine engine (100). A compressor disk assembly (220) can have a cross key ring (240) having a plurality of keys (241), teeth, or castellations, alternating with...  
WO/2019/185231A1
The invention relates to a turbine blade (1) for the rotor of a gas turbine, which turbine blade comprises a blade airfoil (2), which extends from a blade root (6) in the radial direction and has a blade airfoil main body (3) comprising ...  
WO/2019/187663A1
This heat shielding coating comprises: a bond coat layer that is layered on a parent material; and a ceramic layer that is layered on the bond coat layer, and includes a first layer with 10% to 15% porosity and a second layer with 0.5% t...  
WO/2019/190494A1
A locking spacer assembly (200) for filling a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly, a corresponding blade assembly and a method for installing a locking spacer are presented. The loc...  
WO/2019/185713A1
The invention relates to a turbine rotor blade (10) for a gas turbine, comprising a metal blade airfoil (16), which has a leading edge (18), against which a hot gas (S) can flow and from which a side wall (22) on the suction side and a s...  
WO/2019/186028A1
The invention relates to a turbine shaft (26) of a turbomachine extending along a longitudinal axis (A), comprising a main tubular portion (68) of length L1 and having a given maximum outer main diameter, characterized in that it compris...  
WO/2019/187819A1
Provided is a blade manufacturing method by which a blade of a stable quality can be manufactured. The present invention involves: a shaping process in which a blade is molded by means of metal injection molding by injecting metal powder...  
WO/2019/188780A1
This turbine blade comprises a platform, a blade-shaped part having a pressure surface and a negative-pressure surface that extend in a blade-height direction from the platform and that also extend between a leading edge and a trailing e...  
WO/2019/186144A1
The invention relates to an axial turbine with a rotating outer casing (4) and stationary shaft (8) and a method for manufacturing a rotor section (10) for that turbine. The turbine comprises an axially arranged series of rotor sections ...  
WO/2019/185246A1
The invention relates to a moulded part made oxide composite fibre ceramic, referred to below as a "CMC moulded part", such as can be used, for example, in a turbine component, in a burner and/or in an exhaust gas system, in particular o...  
WO/2019/189355A1
A second outer surface (49ab) of a top plate (49) is recessed from a first outer surface (49aa) of the top plate (49) in the direction away from the inner peripheral surface (34a) of a turbine casing (34) so that a step (50) is formed be...  
WO/2019/187435A1
This gas turbine for an aircraft comprises: a moving blade (24) having a moving blade body (41) extending diametrally outward from a rotor that rotates about an axis, and a fin (43) protruding from an outer peripheral surface (42a) of a ...  
WO/2019/188588A1
This turbine rotor blade is provided with a blade body including a belly-side blade wall and a back-side blade wall. The blade body includes; a serpentine flow passage comprising a cooling flow passage divided into a plurality of portion...  
WO/2019/185914A1
A fixture (1) for use in a coating operation, preferably in the shape of a carousel rotatable around a central axis (L), comprising a support structure (5) to which a shield is fixed, the shield has a number of retainer openings (19), ea...  
WO/2019/185394A1
The invention relates to a CMC moulded part, in particular a CMC moulded part having means for fastening and/or for installation, in particular for fastening in a curved, bent or cylindrical surroundings and a method for production there...  

Matches 1 - 50 out of 22,962