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Matches 351 - 400 out of 23,842

Document Document Title
WO/2020/020578A1
Turbomachine (100) having a turbo housing (56) and an impeller (1) which is mounted such that it can be moved about a rotational axis (30), which impeller (1) defines an inflow region (8) and an outflow region (9) of a working medium on ...  
WO/2020/021199A1
The invention relates to a turbomachine blade having a turbine blade airfoil (12) extending in a first direction between a leading edge (18) and a trailing edge and in a second direction, which is substantially perpendicular to the first...  
WO/2020/018090A1
The present invention relates to a turbine nozzle (18) that includes a first body (102) of a metal material (104) and a second body (106) of a ceramic matrix composite material (108). A gap (110) is disposed between the first body (102) ...  
WO/2019/066750A3
Instead of cooling the turbine disk blades of the gas turbine engines using a very stressful and expensive method of stealing from the compressor air at a temperature of 650 degrees Celsius, it is possible to provide a much effective coo...  
WO/2020/013863A1
An airfoil (10) for a turbine engine includes an array of pins (30) positioned in an internal cavity (26) of the airfoil (10), such that cooling channels (52, 54) are defined in the interspaces between adjacent pins (30). Each pin (30) e...  
WO/2020/011837A1
Described are a guide vane for a variable turbine geometry and a turbine assembly provided with same. The guide vane is characterised in that it has an outer face that is at least partly concave in design. The inner face on the opposite ...  
WO/2020/011673A1
The invention relates to a method for coating a part comprising a surface that has cooling fluid openings that adjoin cooling fluid ducts inside the part. The invention further relates to a device for analyzing the surface of a part comp...  
WO/2020/007915A1
The present disclosure relates to a method of manufacturing an aerofoil structure for a gas turbine engine, wherein the aerofoil structure comprises a root (202) configured to be received in a rotor disc (240) of the gas turbine engine, ...  
WO/2020/008142A1
The invention relates to a device (10) for attaching a wear strip to at least one contact face of a turbo engine rotor blade, which device comprises heat-generating means (36) for activating a product for attaching the wear strip to the ...  
WO/2020/007916A1
There is disclosed a method of manufacturing a composite component. A preform (140) for the component is laid - up on a lay - up tool (130) so that a first surface of the preform conforms to a lay - up profile (136) of the tool. The pref...  
WO/2019/202259A3
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/2020/001849A1
The invention relates to a method for the additive manufacturing of a structure (10, 10'), in particular by a powder bed method. The method comprises, layer by layer, a) applying a layer (S) of a base material (P), in particular a pulver...  
WO/2019/245546A1
A cooled turbine blade assembly is provided. The cooled turbine blade assembly includes a hollow turbine blade airfoil extending span-wise radially outward from a platform. The turbine blade airfoil includes a leading edge and a trailing...  
WO/2019/244900A1
This turbine rotor blade comprises a blade body and a tip shroud which is disposed at the tip-end of the blade body and inclined in a radially outer direction from the positive pressure surface toward the negative pressure surface in the...  
WO/2019/242854A1
The turbocharger for an internal combustion engine comprises a compressor (1) for pressurizing intake air, the compressor (1) comprising a compressor wheel (3), a turbine (2) for driving the compressor (1), the turbine (2) comprising a t...  
WO/2019/245563A1
A part formed using an metal additive manufacturing process, such as a turbine airfoil with an oversized feature such as an oversized hole, where the oversized hole is filled with a preform having a shape of a normal sized hole and secur...  
WO/2019/245237A1
A gas turbine comprises a hub, a blade, and a heat delivery part. The hub has a coupling slit formed at a preset interval along the outer surface of the hub. The blade comprises: a root having a first space therein and coupled to the cou...  
WO/2019/239074A1
The invention relates to a vane for a turbine engine turbine comprising a blade (34) and at least one platform (39; 41) that radially extends the blade, and a system for reducing vortices comprising at least one circuit (44; 46) includin...  
WO/2019/237720A1
A method for producing a continuous gas film on the surface of a base body, several concave groove body structures being provided on a surface A of the base body, each groove body structure comprises a groove body bottom and two side wal...  
WO/2019/239064A1
The invention relates to a turbine nozzle (22) for an aircraft turbine engine, said nozzle comprising at least one vane (28) and a base (32) having a platform (30). The nozzle (22) is fitted with a passive system (56) for reintroducing b...  
WO/2019/239036A1
The present invention relates to a holding system for the dismantling of a blade wheel, the blade wheel comprising: - a disc (2), - a plurality of blades configured to be mounted circumferentially around the disc (2), the plurality of bl...  
WO/2019/238377A1
Guiding tool for a surface trimming device and trimming arrangement Guiding tool for a surface trimming device (24), comprising a main body (12) with a front side base portion (13) and a backside base portion (14), which are connected by...  
WO/2019/239123A1
A wing tip device comprising a shroud arranged to at least partially surround a wing tip of a wing. The shroud provides a longitudinal air channel, wherein the air channel is substantially parallel to the direction of movement of the win...  
WO/2019/241541A1
A system is provided for performing an operation on a component of an engine. The component includes a first side positioned within an interior of the engine. The system includes a first robotic arm defining a first distal end and includ...  
WO/2019/234345A1
The invention relates to a nickel-based superalloy comprising in weight percentages: 5.0 to 6.0 % of aluminum, 6.0 to 9.5 % of tantalum, 0 to 1.50 % of titanium, 8.0 to 10.0 % of cobalt, 6.0 to 7.0 % of chromium, 0.30 to 0.90 % of molybd...  
WO/2019/234086A1
The present invention relates to thermally sprayed heat insulation layers which have vertical cracks, a method for the production thereof, and a component coated with such a heat insulation layer.  
WO/2019/236770A1
A setter assembly for use in additive manufacturing a binder-jet part includes a base, a first setter component having a first setter portion and a second setter portion that may be removably coupled to the first setter portion and a plu...  
WO/2019/235588A1
This turbine impeller comprises: a base material the main component of which is aluminum; and an anti-erosion coating that covers the surface of the base material. Due to this configuration, even if liquid droplets flow into the rotating...  
WO/2019/236062A1
An arrangement of a last stage of rotating blades and stationary vanes of a turbomachine (10) is provided. The arrangement includes a last stage of rotating blades (60) mounted to a rotor (50), the rotor coaxial with a turbine casing (20...  
WO/2019/228199A1
Disclosed is a turbine, comprising a flared turbine body (2) composed of several spiral tubular gas channels (1) connected to one another and arranged in a circumferential array. A gas inlet (3) of the each of the spiral tubular gas chan...  
WO/2019/228897A1
The invention relates to a low-pressure compressor of an axial turbomachine such as a turbojet. The compressor comprises a row of blades (34) extending radially from an annular surface (42) in a non-axisymmetric form, known as 3D contour...  
WO/2019/231785A1
A system (100) includes a mounting plate (210) having a plurality of reference members (212), an inspection system (130) has a profiler device (230), and an additive manufacturing machine (140) operatively coupled with the inspection sys...  
WO/2019/228864A1
There is disclosed a composite fan blade root 100 comprising an outer region 110 comprising composite material and defining an outer inspection surface 120 of the component; an inner region 108 surrounded by the outer region 110; and an ...  
WO/2019/202249A3
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/2019/224486A1
In order to create a thin trailing edge which will not be deformed by a subsequent material removal operation on a turbomachine blade created by the lost wax casting method and comprising an airfoil having a mutually opposite leading edg...  
WO/2019/224464A1
The invention relates to a disc (40) that is able to support platforms (30) and blades (20) of a fan (2) and has an external surface (40a) having a series of grooves (42) for receiving the fan blades and teeth (44) interposed between the...  
WO/2019/224496A1
The invention concerns a fan blade (1) for a turbomachine, comprising: - a leading edge (4) and a pressure-side wall (6), - a structural shield (10), said shield (10) being attached and fixed to the leading edge (4) of the blade (1) and ...  
WO/2019/164683A3
The present invention relates to a method of processing a component, wherein the component comprises at least one opening in a surface thereof, the method comprising: placing the component in an electrophoretic fluid comprising particles...  
WO/2019/226163A1
Systems and methods for additively manufacturing or repairing a component using forge welding. The system includes a build platform (10) with support (12). Additive materials (26) are fed to a deposit location (14) on the build platform ...  
WO/2019/226277A1
This disclosure provides a devices and systems for securing a gas turbine nozzle segment and sealing one or more cooling cavities (469) of the gas turbine nozzle segment (451) during manufacturing. The device (480, 700, 800, 900) can hav...  
WO/2019/194878A3
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/2019/220042A1
Turbomachine stator element (50), extending around a longitudinal axis, the element comprising at least one first stator vane (1) and at least one second stator vane (1') circumferentially adjacent to the first stator vane (1), each firs...  
WO/2019/219473A1
A turbine wheel is disclosed. The turbine wheel includes a plurality of first dovetail slots (300) and a plurality of second dovetail slots (100). The plurality of first dovetail slots and the plurality of second dovetail slots are alter...  
WO/2019/220057A1
The present invention relates to a method for manufacturing a ceramic matrix composite part (115), comprising at least: - the coating of an outer surface (S) of a porous preform (100) with a layer of a fugitive material (102) in order to...  
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 ...  

Matches 351 - 400 out of 23,842