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Patent Searching and Data


Matches 1,251 - 1,300 out of 23,247

Document Document Title
WO/2016/025253A1
A method for forming a coating on a substrate is provided. To an assembly 10 including a substrate 12, a porous matrix 14 on the substrate 12, and an impregnating material 16 on or within the porous matrix 14, the method includes applyin...  
WO/2016/025130A1
A method, including: providing a layer of powder material (106) on a substrate (12) having protruding rib material (26); and traversing an energy beam (100) across the layer of powder material to form a cladding layer (10) around and bon...  
WO/2016/025133A1
A method, including: providing a layer of powder material (156) on a substrate (130); and traversing an energy beam (15) across the layer of powder material to form a cladding layer (10), wherein the cladding layer forms a layer of an ai...  
WO/2016/023850A1
The invention relates to a system for introducing mechanical counter vibrations into a rotating rotor shaft of a turbine, comprising: - at least one measurement unit configured to detect mechanical vibrations of the rotor shaft and to ge...  
WO/2016/024458A1
In the present invention, an axial flow-type turbo machine is provided with: a plurality of blades (12) that form a stationary blade row or a moving blade row; an end wall (30) to which the plurality of blades (12) are fixed and which fo...  
WO/2016/019468A1
A structure adapted to traverse a fluid environment includes an elongate body having a root, a wingtip, a leading edge and a trailing edge; and a plurality of rigid projections each extending from a respective position along the leading ...  
WO/2016/022126A1
A cooling system (10) for a turbine airfoil (12) of a gas turbine engine having a bifurcated mid-chord cooling chamber (16) for cooling the airfoil (26) is disclosed. The bifurcated mid-chord cooling chamber (16) may be formed from a pre...  
WO/2016/022140A1
A component wall (10) includes a substrate (12) having a first surface (14) and an opposed second surface (16), and at least one cooling passage (20) extending through the substrate (12) for delivering cooling fluid (CF) from a chamber (...  
WO/2016/020614A1
The invention relates to a turbomachine turbine blade (1) comprising a suction face (11), a pressure face (12), a leading edge (13) and a trailing edge (14) as well as a squealer (2) at the tip thereof, said squealer tip (2) comprising a...  
WO/2015/183439A3
A coated substrate (100) is provided that can include a substrate defining a surface (103), and an abradable coating (106) on the surface (103) of the substrate. The abradable coating (106) can comprise La2-xAxMo2-y-y'WyByO9-δ forming a...  
WO/2016/018570A1
An article includes a substrate, a substantially hermetic sealing layer disposed on the substrate, and a porous transition layer disposed on the substrate between the sealing layer and the substrate. The article also includes one or more...  
WO/2016/016545A1
The invention relates to a turbomachine element comprising a stator (2), a rotor (1), and a first sealing means (9) for sealing between the rotor (1) and the stator (2) arranged to be active when the rotor is in the operating position of...  
WO/2016/015920A1
A turbine aerofoil (1) comprises: - a leading edge (3), - a trailing edge (5), - an exterior surface including a suction side (7) and a pressure side (9), - at least an internal cavity (11A-11D) for forming a cooling circuit comprising c...  
WO/2015/175043A3
An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defi...  
WO/2016/012399A1
A method for manufacturing a machine component made of metal-based material is described. The method comprises the steps of: providing a powder blend comprising at least one metal-containing powder material and at least one strengthening...  
WO/2016/014056A1
A cooling system (10) for a turbine airfoil (12) of a gas turbine engine is disclosed, whereby the cooling system (10) includes spanwise extending midflow blockers (14) positioned within one or more cooling channels (16) to maintain an i...  
WO/2016/008791A1
Wheel disc arrangement (1) comprising a wheel disc (2), a plurality of blade devices (3) which are fastened along the outer circumference of the wheel disc (2), and a plurality of sealing plates (4) which are held in two radially spaced-...  
WO/2016/008789A1
The invention relates to a wheel disk assembly (1), comprising a wheel disk (2), a plurality of blade devices (3), which are fastened along the outer circumference of the wheel disk (2), and a plurality of sealing plates (4), which are r...  
WO/2015/175058A3
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailin...  
WO/2015/175073A3
A gas turbine engine includes a fan section, a compressor section and a turbine section, one of which includes an airfoil. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inne...  
WO/2016/007116A1
Gas turbine engine blade squealer tips incorporate cooling slots formed in the suction side rail downstream of the leading edge for directing cooling gas flow along an inside edge of the squealer tip pressure side rail. Some embodiments ...  
WO/2015/178974A3
An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a...  
WO/2015/175056A3
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between leading edg...  
WO/2015/175044A3
An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a ...  
WO/2016/004506A1
A vertical axis hydrokinetic turbine apparatus comprises a drive shaft assembly, at least two blade assemblies, and at least two pairs of support arm connection interfaces. The drive shaft assembly comprises a rotatable drive shaft, an u...  
WO/2015/175045A3
An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defi...  
WO/2016/005687A1
The invention relates to a method for mounting vanes (10) in the periphery of a turbine engine disc (12), the disc (12) comprising cavities extending alternately with teeth, the vanes (10) respectively comprising: roots to be inserted in...  
WO/2015/175052A3
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangent...  
WO/2016/007145A1
An internal cooling system (14) including an impingement jet strike channel system (16) for increasing the effectiveness of impingement jets (18) is disclosed. The impingement jet strike channel system (16) may include an impingement jet...  
WO/2015/175051A3
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial ...  
WO/2016/003571A1
A coated substrate is provided that comprises: a substrate; and a barrier coating comprising a compound having the formula: Ln2ABOs, where Ln comprises scandium, yttrium, lanthanum, cerium, praseodymium, neodymium, promethium, samarium, ...  
WO/2016/001343A1
The invention concerns a method for producing a composite material part comprising a fibrous reinforcement densified by a ceramic matrix, the part having an outer surface and being coated on at least one part of the outer surface of same...  
WO/2016/000849A1
The invention relates to an arrangement (19) for the temporary coupling of two rotor blades (9) arranged adjacent to one another on a rotor of a fluid energy machine, in particular a gas turbine, a steam turbine, a compressor or the like...  
WO/2016/001026A1
The invention concerns a part made from composite material comprising a fibrous reinforcement densified by a ceramic matrix, the part having an outer surface and being characterised in that it is coated on at least one part of the outer ...  
WO/2016/001544A1
The invention relates to a method for manufacturing a two-component blade for a gas turbine engine, which comprises consecutively obtaining a blade profile (24) made of ceramic material comprising a hole passing through the blade profile...  
WO/2015/197328A1
A compressor aerofoil for a turbine engine, the compressor aerofoil comprises a suction surface wall and a pressure surface wall meeting at a leading edge and a trailing edge, a tip plate extends between the suction surface wall and the ...  
WO/2015/200158A1
A method for analyzing a three-dimensional stress concentrating feature of a component (60), such as a borehole (62), using a two-dimensional probabilistic technique. A circumferentially-dependent stress concentration profile around the ...  
WO/2015/198840A1
Formed in this rotor blade (50) are blade airflow passages (71) which continuously extend inside a blade body (51) and a platform (61). Formed in the platform (61) are multiple ventral-side passages (72) which extend from the blade airfl...  
WO/2015/199447A1
The present invention relates to a rotary power generation apparatus with the same number of rotary shaft revolutions as a generator rotation rate and, more specifically, to a rotary power generation apparatus with the same number of rot...  
WO/2015/197315A1
The invention relates to a turbocharger (1), comprising a compressor, a turbine (12), a shaft (2), and at least two ball bearings (3, 4), in which the shaft (2) is supported, wherein the shaft (2) is formed of two shaft parts (6, 7), whi...  
WO/2015/198622A1
A turbine rotor blade cascade comprising a plurality of turbine rotor blades arranged along the circumferential direction of a hub, wherein a flow path between the rotor blades has a first cross-sectional shape perpendicular to the radia...  
WO/2015/197980A1
The invention relates to a rotary assembly for turbomachine, comprising: a disk (16) having an external periphery exhibiting an alternation of pockets (22) and of teeth (20), vanes (14) extending radially from the disk (16), the roots (2...  
WO/2015/193068A1
The invention relates to a turbine blade (1) having an internally cooled turbine airfoil (3), which forms at least one cooling air main channel (19) extending in the longitudinal direction (18) of the turbine blade (1) in order to guide ...  
WO/2015/195086A1
A turbine airfoil (10) usable in a turbine engine and having an internal cooling system (14) with a leading edge impingement channel (16) for enhanced cooling of the leading edge (18) of the turbine airfoil (10) without a leading edge fi...  
WO/2015/195088A1
A turbine airfoil (10) usable in a turbine engine and having an internal cooling system (14) with a leading edge impingement channel (16) for enhanced cooling of the leading edge (18) of the turbine airfoil (10) without a leading edge fi...  
WO/2015/193033A1
The invention relates to a rotor (1) of an axial turbomachine, comprising at least one rotor disk (2), a plurality of rotor blades (3), which are arranged along the outer circumference of the rotor disk (2) and which are each fastened to...  
WO/2015/165678A3
The invention relates to a wheel disk assembly (1; 14; 26), comprising a wheel disk (2; 15; 27), a plurality of blade devices (3; 16; 28), which are fastened along the outer circumference of the wheel disk (2; 15; 27), and a plurality of...  
WO/2015/195112A1
A contoured turbine airfoil assembly including an end wall (30a) formed by platforms (30) located circumferentially adjacent to each other, and a row of airfoils (34a, 34b) integrally joined to the end wall (30a) and spaced laterally apa...  
WO/2015/088699A8
An array of components in a gas turbine engine includes first and second structures respectively including first and second surfaces that are arranged adjacent to one another to provide a gap. The first and second surfaces respectively h...  
WO/2015/191330A1
A turbine blisk is provided. The turbine blisk includes an inner rim, a plurality of adjacent rotor blades extending radially outward from said inner rim, a shroud segment integrally coupled to each of the plurality of adjacent rotor bla...  

Matches 1,251 - 1,300 out of 23,247