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Matches 1 - 50 out of 20,983

Document Document Title
WO/2017/137709A1
The invention relates to a ceramic core (10) used for the production of a hollow turbine blade for a turbomachine, using the lost-wax foundry technique, said blade comprising calibrated dust-removal holes extending from an apex of at lea...  
WO/2017/138795A1
The present invention relates to a power generation cycle system comprising: a pump module for allowing working fluid to flow; a first heat exchange module for receiving the working fluid from the rear end of the pump module and heating ...  
WO/2017/138982A1
A coupling assembly arranged between an input shaft and a rotor shaft of a supercharger includes a first hub, a second hub, a first side coupling assembly, a second side coupling assembly, a central hub and a plurality of coupler pins. T...  
WO/2017/137701A1
The invention relates to a system for rotating a fan (2) of a turbojet engine (1) about a first rotation axis (Ω), including a reduction gear (3) made up of a planetary gearset placed at the centre of the fan (2), which includes: a cent...  
WO/2017/133872A1
The invention relates to a method for compensating for the axial force of a rotor (2) of a gas turbine (1), having the following steps: - detecting a measurement value in order to characterize the axial thrust of the rotor (2) of the gas...  
WO/2017/136625A1
System and method for cooling an expander (100) rotor assembly. The system may include an annular body (148) disposed on a rotor disc (128) of the rotor assembly (118). The rotor disc (128) may also include a plurality of rotor blades (1...  
WO/2017/135187A1
This linear friction bonding device is for bonding, by frictional heat, a blade-side bonding surface of a blade and a disc-side bonding surface of a disc protrusion provided on the outer circumferential surface of a disc. The linear fric...  
WO/2017/130144A1
The invention relates to equipment for implementing a method for depositing a vapor-phase metal coating onto turbine engine parts such as, for example, blades (14). Said equipment comprises at least one basket (2) defining a chamber (9),...  
WO/2017/129455A1
A rotor disc (36) for a gas turbine (10) comprises: - at least a root cavity (75) for coupling with a blade (38, 60) of the gas turbine, - a disc cooling hole (70) for connecting the root cavity (75) with a source of a cooling gas. The d...  
WO/2017/125662A1
The invention relates to a centrifugal or mixed-flow compressor impeller comprising a hub (10) centred on an axis (XX'), a disk (11) extending radially from the hub (10), and a plurality of blades (16) carried by said disk (11), each bla...  
WO/2017/125671A1
The invention relates to a twisting torque sensor, comprising a transmission shaft (12) subjected to the torque to be measured, a reference shaft (14), and a device for measuring an angular deformation representing the torque to be measu...  
WO/2017/125344A1
A rotary machine (3) is disclosed, which comprises comprising: a rotary shaft (7) having a rotation axis (A-A), a first shaft end (7A), and a second shaft end (7B); a first bearing arrangement (10) at the first shaft end (7A); a second b...  
WO/2017/125289A1
An aerofoil (100) for a gas turbine (10) comprises: - an external surface (128) extending along a first axial direction between a leading edge (133) and a trailing edge (135) and extending along a second radial direction between a base (...  
WO/2017/126757A1
The present invention relates to a gas turbine rotor assembly having a torque pin, the assembly comprising: a plurality of rotor discs, each of which has a protrusion plate portion protruding along a circumferential direction from opposi...  
WO/2017/123207A1
An airfoil (30) for a turbine (10) wherein the airfoil (30) includes a core support structure (34) having a core outer surface (44) and a high heat resistant outer shell (32) having leading (36) and trailing (38) edges and high (40) and ...  
WO/2017/121689A1
An aerofoil (100, 101, 102) for a gas turbine (10) comprises: an external surface (128) axially extending between a leading edge (133) and a trailing edge (135) and radially extending between a base (134) and a tip (136); an internal pas...  
WO/2017/121765A1
The invention relates to a coating system for turbine components, for example a gas turbine vane and/or a gas turbine blade, in particular a component which is made of a ceramic composite material "CMC" (Ceramic Matrix Component), wherei...  
WO/2017/123206A1
A flexible damper (24) for turbine blades (10) includes a plurality of segments (32) positioned together in a substantially linear pattern, each segment (32) having a first side (46), a second side (48), a top side (50), a bottom side (5...  
WO/2017/123524A1
Methods for mounting a turbine sub-component (100) to a turbine component (102) are disclosed, including positioning a retaining portion (104) of the turbine sub-component (100) along a positioning path (108) into association with an emp...  
WO/2017/119898A1
A blade (20) for a turbine engine that includes a squealer tip (10) formed from at least one outer pressure side rib (12), at least one inner pressure side rib (14), and at least one outer suction side rib (16) extending radially outward...  
WO/2017/120029A1
A compressor wheel (213) for a turbocharger (119) includes first, second and third pluralities of blades (308) formed around a central hub (302). Each of the second plurality of blades (308) is disposed between adjacent blades (308) from...  
WO/2017/120031A1
A turbocharger (119) for use with an internal combustion engine (100) includes a compressor wheel (213) having a central hub (302) having a centerline, a root portion and an end portion. A plurality of blades (308) is formed around the c...  
WO/2017/119358A1
A removal device is provided with a base (101), a push bar (130), a bar movement mechanism (150), and a bar guide (140). The base (101) is restrained so as to be immovable in a first direction (Z). The push bar (130) can protrude to the ...  
WO/2017/120030A1
A compressor (136) for a turbocharger (119) for use with an internal combustion engine (100) includes a compressor wheel (213) having a central hub (302) having a centerline, a root portion, and an end portion. A plurality of blades (308...  
WO/2017/118806A1
A method for manufacturing a workpiece by additive manufacturing making it possible to save certain particularly sensitive surfaces of the workpiece and, in particular, the surfaces influencing the aerodynamics of the end workpiece, the ...  
WO/2017/120032A1
A compressor (136) in a turbocharger (119) for an internal combustion engine (100) includes a compressor wheel (213) that includes a central hub (302) having a centerline, a root portion and an end portion. A plurality of blades (308) is...  
WO/2017/114644A1
The invention relates to a method for producing turbine rotor blades or the base bodies (30) thereof, the frequency property of which can be adapted particularly easily to the required boundary conditions. To this end, recesses (50) are ...  
WO/2017/115642A1
Before subjecting a turbine rotor blade to a heat treatment for removing residual stress, an adhesion cleaning step (scale cleaning step) is executed, wherein an ultrasonic cleaning process (steps S22, S25), in which the turbine rotor bl...  
WO/2017/115643A1
After a bonding coat layer removal step wherein a bonding coat layer (first coating layer) is removed by a chemical process, and a cleaning step wherein a turbine blade is cleaned by blast processing, an adhesion cleaning step (blast par...  
WO/2017/113258A1
A sealing cover (20) used for a gas turbine (100). The gas turbine (100) comprises at least one turbine disk (143), and the sealing cover (20) is used to cover the turbine disk (143). A side wall (22a) of the sealing cover (20) is provid...  
WO/2017/114712A1
The invention relates to a rotor device (10A) of an aircraft engine, comprising a disc wheel and at least two rotor blades (14, 15) which are arranged on the disc wheel, which adjoin each other, and each of which comprises a blade platfo...  
WO/2017/108661A1
The invention relates to a turbine blade (10) for a thermal turbomachine, having a blade airfoil (20) around which a hot gas can be made to flow and which comprises a suction-side and a pressure-side side wall (22, 24). The blade airfoil...  
WO/2017/109408A1
The invention relates to a blade which comprises a blade body (30) made of anisotropic material and a leading edge shield (32) made of a material having better resistance to isolated impacts assembled on the blade body and including two ...  
WO/2017/112610A1
A component has an edge extending in a first direction. The component includes a filler disposed in the component. The filler has at least a first portion and a second portion. The first portion extends in a second direction from the edg...  
WO/2017/109404A1
The invention relates to the field of turbomachine blades, and more specifically to a leading edge shield (32) for a turbomachine blade (16), which comprises a lower canopy fin (34) and an upper canopy fin (36), each extending in the hei...  
WO/2017/110894A1
The present invention prevents decreases in cycle efficiency in a combined cycle plant without requiring a separate power source and improves the durability of a nozzle stationary blade. This steam turbine includes a high-pressure steam ...  
WO/2017/109407A1
The invention relates to the field of turbomachine blades, and more specifically to a leading edge shield (32) for a turbomachine blade (16), said leading edge shield (32) comprising a lower canopy fin (34) and an upper canopy fin (36). ...  
WO/2017/109406A1
The invention relates to the field of turbomachine blades, and more specifically to a leading edge shield (32) for a turbomachine blade (16), extending in the direction of its height from a lower end (40) to an upper end (41), having an ...  
WO/2017/110039A1
The present invention is a turbine rotor disc repairing method for removing a defective part generated in an outer peripheral portion of a turbine rotor disc having a blade groove in the outer peripheral portion and for reforming the bla...  
WO/2017/105259A1
A nozzle has an airfoil, and the nozzle is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent nozzles, at which adjacent nozzles extend across the pa...  
WO/2017/105260A1
A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathwa...  
WO/2017/100911A1
The present invention relates to a conditioning method of gas turbine engine components (e.g. compressor blades and vanes) for increasing fuel efficiency. The gas turbine engine components are plasma treated in a high vacuum environment ...  
WO/2017/103650A1
New exemplary heat exchange configurations that incorporate internal or external surfaces equipped with perturbators, for changing the thermal behavior of the system, or for modulating the surface temperature distribution of the flow sur...  
WO/2017/105380A1
An airfoil (30) for a turbine (10), wherein the airfoil (30) includes leading (36) and trailing (38) edges and high (40) and low (42) pressure surfaces. The airfoil (30) includes a core support structure (34) having first (46) and second...  
WO/2017/105379A1
A turbine airfoil (10) includes a flow blocking structure (26) positioned in an airfoil interior (11), for displacing a coolant flow toward a pressure side (16) and a suction side (18) of an airfoil outer wall (14). The flow blocking str...  
WO/2017/104916A1
The present invention relates to a reaction-type steam turbine. More specifically, the present invention relates to a reaction-type steam turbine that has guide blades mounted on a turbine shaft located between disk blades and a steam in...  
WO/2017/102254A1
The invention relates to a rotor for a turbomachine, comprising a plurality of axially adjacently arranged rotor segments which are each provided with a central opening, an individual tie rod extending through the openings of the rotor s...  
WO/2017/098959A1
Provided are a seal structure, a turbomachine, and a method for producing a seal fin with which an excellent leak-preventing effect can be achieved and leak loss in a turbomachine can be reduced while suppressing an increase in productio...  
WO/2017/098960A1
Provided are a step seal, a seal structure, a turbomachine, and a method for producing a step seal with which an excellent leak-preventing effect can be achieved stably and leak loss in a turbomachine can be reduced stably. Disclosed is ...  
WO/2017/094292A1
A sliding component (10) provided with a wear-resistant coating comprises: a sliding component (12); and a wear-resistant coating (14) provided on a sliding surface (12a) of the sliding component (12) and formed of a cobalt alloy that co...  

Matches 1 - 50 out of 20,983