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Patent Searching and Data


Matches 1,201 - 1,250 out of 23,247

Document Document Title
WO/2016/057107A1
A forward running wind turbine includes a rotor having a hub and at least one blade adapted for attachment to said hub by means of a spacer, said spacer being adapted so as to provide a forward axial orientation of the spacer relative to...  
WO/2016/055350A1
By applying material along parallel welding lines per welding layer and by changing the direction of extension of the welding tracks by 90° for the next welding layer, good results are achieved.  
WO/2016/057110A1
A wind turbine includes a rotor having a hub and at least one blade adapted for attachment to said hub by means of a root so as to provide a forward axial orientation of the root relative to a plane that is normal to the axis of rotation...  
WO/2016/052114A1
A steam corrosion-resistant multilayered film formed on a base material containing a silicon carbide composite material, said steam corrosion-resistant multilayered film being characterized by comprising: an eutectic structure layer cont...  
WO/2016/051054A1
The invention relates to a mobile vane (34) for a turbine engine, comprising a root (41) designed to be inserted into a receiving element (62) of a rotor disk (38) for a turbine engine, a platform (48) carried by the root (41), and a bla...  
WO/2016/051531A1
This turbine is provided with: a housing which includes a shroud section having an inlet (61), an outlet (62), and a shroud surface (6) extending between the inlet and the outlet; and a turbine rotor section which is housed inside the ho...  
WO/2016/025054A3
Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides an array of cooling holes or apertures which are facing the cool side surface of...  
WO/2016/050669A1
The invention relates to a return stage (RS) of a radial turbo fluid energy machine, in particular of a radial turbo compressor (TCO), having an axis of rotation (X), the return stage (RS) comprising an annular flow channel (CH) for feed...  
WO/2016/043743A1
A nano-yarn composite material (10) formed from a base material (12) and at least one nano-yarn (14) positioned within the base material (12) for strengthening the base material (12) is disclosed. In at least one embodiment, the base mat...  
WO/2016/043742A1
A core structure (10) includes a first core element (16) including a leading edge section (30), a tip section (32), and a turn section (34) joining the leading edge and tip sections (30, 32). The first core element (16) is adapted to be ...  
WO/2016/042275A1
The invention relates to the field of rotary blades and more particularly to a method of manufacturing a leading edge shield intended to protect such a blade. This method involves at least the steps of initial plastic deformation of at l...  
WO/2016/041799A1
The invention relates to a device (2, 17) for driving a stator blade (3) into a blade groove (1) which is mounted on a stator blade carrier (4) of a turbine and contains at least one caulking element (5), comprising at least one linear d...  
WO/2016/041957A1
The invention relates to a method for treating a composite part (10) comprising a metal protective duct (12) fixed to a core (11) by means of a binder (14), so as to be able to separate the duct from the core, comprising the steps consis...  
WO/2016/044450A1
A preswirler (470) for a gas turbine engine (100) diaphragm assembly (460) is disclosed herein. In embodiments, the preswirler (470) includes an outer ring (471) and an inner ring (474). The outer ring (471) includes an outer ring face (...  
WO/2016/041761A1
The invention relates to a turbine blade (1) having an internally cooled turbine blade airfoil (3) in which a hollow space (10) is divided by rib elements (11, 12) into at least one cooling duct (13) carrying a coolant, wherein in at lea...  
WO/2016/038280A1
The invention relates to a vane for a turbine engine. The vane (12') has a blade (13') and a root (18') to be inserted into an axial groove of a turbine engine disc. The upstream end (450') of the root is connected to a radially inner en...  
WO/2016/037452A1
Disclosed is a counter-rotation impeller mechanism, comprising at least one positive rotating shaft (1) and at least one negative rotating shaft (2), wherein the difference between the numbers of the positive rotating shaft (1) and the n...  
WO/2016/039714A1
A cooling system (10) positioned within a turbine airfoil (12) and having film cooling channels (16) positioned within inner and outer endwalls (18, 20) of the turbine airfoil (12), with cooling fluids supplied to the cooling channels (1...  
WO/2016/039716A1
An insulating system (10) for a gas turbine engine (12) configured to insulate a surface (14) to reduce thermal gradients within components (18) in the engine (12) is disclosed. The insulating system (10) may include one or more insulati...  
WO/2016/038282A1
The invention relates to a method (40) for repairing an upstream rail (20) of a turbine engine turbine casing (19), said casing (19) including a casing body (21) extending along a longitudinal axis, said upstream rail (20) including: a b...  
WO/2015/135681A3
The invention relates to a steam-turbine unit (1) comprising a steam turbine (6) and an option for cooling said steam turbine by means of forced cooling, whereby cooling air is drawn through the steam turbine (6) via a suction device (11...  
WO/2016/040367A1
A system and method for remanufacturing a turbocharger (100) center housing (106) include performing a machining operation on an original center housing (200) to remove a portion of a parent material from the original center housing (200...  
WO/2016/034796A1
The invention concerns a tubular shaft (8) of a turbomachine, comprising, at the inner periphery of same, a bath (11), substantially perpendicular to said splines (9), characterised in that said bath (11) comprises cavities (17) distribu...  
WO/2016/034487A1
The invention relates to a method for operating a machine plant (1) having a shaft train (2), with the steps of: a) determining, computationally, the harmonic frequency of at least one torsional vibration mode of the shaft train and dete...  
WO/2016/036367A1
An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained therein that forms nearwall cooling channels (20) having ...  
WO/2016/035663A1
 Provided are a method for manufacturing a molded ring by which it is possible to reliably and efficiently fabricate a molded ring having a reduced dead metal region. Also provided is a ring material for use in fabricating the molded r...  
WO/2016/034822A1
The invention relates to a blade having a platform (14) comprising at least one bumper (40) which rises, on the inner face, from a junction to an intermediate area of the blade, located along a longitudinal axis of the blade, between the...  
WO/2016/035664A1
Provided is a manufacturing method for a ring formed body, the method enabling the ring formed body with a reduced dead metal region to be reliably and efficiently manufactured. In this invention, the ring formed body is manufactured in ...  
WO/2016/035618A1
This method for producing a powder for thermal spray is provided with: a preparation step S1 for preparing a mixed powder which contains first particles that are configured of a zirconia-based ceramic containing a first additive and seco...  
WO/2016/036366A1
An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities having an insert (18) contained within an aft cooling cavity (76) to form nearwall cooling cha...  
WO/2015/160404A3
A gas turbine engine component comprises a body extending between two ends and having at least two cooling passages. The body has a first wall and second wall. At least two cooling passages include a first passage that is closer to the f...  
WO/2016/035329A1
In the present invention, different attack angles are set for turbine blades (22) on one side and on the other side in an axial direction in accordance with a relative inflow angle of exhaust gas. In other words, a first attack angle (θ...  
WO/2016/030997A1
A turbocharger (1) is provided with a valve body (10) which is disposed in a suction flow path (C) leading from an inflow port (14) of a housing (4a) covering a turbine rotor blade (6) to a scroll part (15) and composed of a single piece...  
WO/2016/030614A1
The invention relates to a method for repairing an assembly comprising a main body (10) and an old reinforcement, the assembly comprising an initial hole passing through the old reinforcement and at least one part of the main body. The m...  
WO/2016/032506A1
A controlled convergence compressor flowpath (10) configured to better distribute the limited flowpath (10) within compressors (12) in turbine engines (14) is disclosed. The compressor (12) may have a flowpath (10) defined by circumferen...  
WO/2016/031475A1
An axial-direction passage (45), a forced vortex passage (46), a first blade array passage (47), and a second blade array passage (48) are formed in a rotor shaft (32) of a turbine (30). Cooling air from an air extraction port (16) of a ...  
WO/2016/030307A1
The invention relates to a turbine blade (1) with an internally cooled turbine airfoil (3), in which a hollow space (10) is divided by rib elements (11, 12) into at least one cooling channel (13) carrying coolant, wherein at least one of...  
WO/2016/030449A1
The invention relates to a turbine blade (1) with an internally cooled turbine blade airfoil (3), in which a hollow space (10) is divided by rib elements (11, 12) in at least one cooling channel (13) carrying a coolant (14), wherein a re...  
WO/2016/032881A1
A rotor for use with an airborne wind turbine, wherein the rotor comprises a front flange, a can, a rear flange, and a rigid insert comprising a propeller mount, wherein the front flange, can, and rear flange comprise one of carbon fiber...  
WO/2016/032789A1
An article for high temperature service is presented herein. One embodiment is an article including a substrate having a silicon-bearing ceramic matrix composite; and a layer disposed over the substrate, wherein the layer includes silico...  
WO/2016/033465A1
A turbine blade (10) includes an airfoil (12) extending span-wise along a radial direction, and a shroud (26) positioned along a tip (22) of the airfoil (12) extending generally along a circumferential direction, scalloped, across a pres...  
WO/2016/030231A1
The present invention relates to a method for manufacturing a turbine assembly (10) comprising at least one aerofoil unit (12) comprising at least a basically hollow aerofoil (14) with at least one cooling passage (16) for a cooling medi...  
WO/2016/031268A1
A turbocharger (1) is provided with a valve body (10) which is disposed in a suction flow path (Cb) leading from an inflow port (14) of a housing (4a) covering a turbine rotor blade (6) to a scroll flow path (Ca) and composed of a single...  
WO/2016/030613A1
The invention relates to a diffuser vane (2) for a gas turbine engine, comprising a vane assembly (4) made of a composite material having a fibrous reinforcement densified by a matrix, the fibrous reinforcement being obtained from long f...  
WO/2016/030608A1
The invention relates to a guide vane (10) made from composite material for a gas turbine engine, comprising a fibrous reinforcement densified by a matrix, the fibrous reinforcement being formed as a single component by means of three-di...  
WO/2016/030289A1
The invention relates to a turbine blade for a turbomachine comprising a turbine blade wall (1) and a fluid channel (2) having an inlet channel section (2a) on the end region leading to the cold side, an outlet channel section (2b) on th...  
WO/2016/030157A1
The present invention relates to a turbine assembly (10, 10a, 10b) comprising a basically hollow aerofoil (12) having at least a main cavity (14) with at least an impingement tube (16, 16b), which is insertable inside the main cavity (14...  
WO/2016/026814A1
A compressor aerofoil (70) for a turbine engine or an axial process compressor, the compressor aerofoil comprises a suction surface wall (88) having a suction surface (89) and a pressure surface wall (90) having a pressure surface (91), ...  
WO/2016/028543A1
A method, including: replacing an original blade shelf (16) of a gas turbine engine blade (10) with a new blade shelf (64) that is located closer to a base (18) of the blade than the original blade shelf; adding mass to the blade until a...  
WO/2016/028306A1
A modular turbine blade assembly (10) usable in a gas turbine engine (12) and formed from an airfoil (28) and an independent, modular platform (16) supported by one or more clevis arm supports (14) extending radially inward from the modu...  

Matches 1,201 - 1,250 out of 23,247