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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...
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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...
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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-...
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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...
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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 ...
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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...
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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...
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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...
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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, ...
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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...
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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...
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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 ...
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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...
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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 ...
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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 ...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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...
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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...
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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...
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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...
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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...
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WO/2015/189718A1 |
A turbine (1), at least partially centrifugal, for the expansion of a compressible operating fluid, for example gas or steam. At least one group of stages (5), named centrifugal stages, extends in a radial direction with respect to the a...
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WO/2015/191041A1 |
A trailing edge insert (10) for a turbine airfoil (12) of a gas turbine engine (14) usable to increase the durability of the airfoil (12) and to reduce the thickness of the trailing edge, thereby reducing aerodynamic loss, increasing tur...
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WO/2015/191037A1 |
A turbine airfoil (10) usable in a turbine engine and having an internal cooling system (14) with one or more diffusion film cooling holes (16) with an exhaust outlet (18) positioned at the stagnation line (20) at the leading edge (22) a...
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WO/2015/185860A1 |
The invention aims to provide a rotor for a turbine engine comprising: a disc having cavities on the periphery thereof, referred to as primary cavities; a plurality of blades (100) each having a root (110) consisting of, at the bottom po...
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WO/2015/185310A1 |
Disclosed is an assembly for laser cladding (1), said assembly comprising a work surface (5) on which a workpiece to be treated is laid during the laser cladding process. The work surface (5) is supported on springs (6) and is designed t...
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WO/2015/186523A1 |
Provided is a gas turbine which enables the amount of supply of cooling air to be efficiently and easily adjusted. This gas turbine has: a first cavity to which cooling air is supplied, said first cavity being formed inside a stationary ...
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WO/2015/187658A1 |
A protective coating system is described that is characterized by fluid impermeability and a reduced coefficient of friction. The coating system includes a carbide-based thermal spray composition; a low friction layer; and a sealant impr...
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WO/2015/187163A1 |
A cooling system (10) positioned within a turbine airfoil (12) useable in a turbine engine and having cooling channels (16) positioned within a platform (18) of the turbine airfoil (12) with exhaust outlets (20) at the pressure and sucti...
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WO/2015/181488A1 |
The invention concerns a turbine blade (91) comprising a root (P), a vane extending in a spanwise direction (EV), ending at a tip (S) and comprising a leading edge and a trailing edge and a pressure-side wall and a suction-side wall, sai...
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WO/2015/184294A1 |
A structure for disrupting the flow of a fluid, the structure comprising: (a) a first lateral wall and a second lateral wall spaced apart from one another a distance across an X-axis; (b) a turbulator extending between the first lateral ...
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WO/2015/181497A1 |
The invention concerns a turbine blade (51) for a turbomachine such as a turboprop or a turbojet, said blade comprising a root (P), a vane carried by said root (P) and extending in a spanwise direction (EV), ending at a tip (S), said van...
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WO/2015/181482A1 |
The invention concerns a turbine blade (11) for a turbomachine, comprising a vane (12) extending in a spanwise direction between a root and a tip, a first inner side cavity (54) running along the pressure-side wall (21) and a second inne...
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WO/2015/181080A1 |
The method for manufacturing a turbomachine component comprises the following steps: (a) producing by additive manufacturing a plurality of separate segments (1S) of the tubomachine component (1), having a skin surrounding an empty volum...
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WO/2015/181549A1 |
The present invention relates to a platinum group metal-diffused bond coat with single gamma-prime phase of a nickel-based single crystal superalloy, which is suitable for use in thermal barrier coatings to protect components (e.g. turbi...
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WO/2015/183899A1 |
An engine component assembly is provided for impingement cooling including discrete cooling features. An insert is located opposite and adjacent to a cooled surface of the engine component and includes a plurality of angled impingement a...
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WO/2015/180920A1 |
The invention relates to a method for repairing a precision casted turbine blade, which comprises an airfoil (11) with a pressure (22) and a suction side (24) with a wall thickness (w) and internal cooling channels, a tip having a tip cr...
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WO/2015/176923A1 |
The invention relates to a method for repairing an airfoil (9) of an axial turbomachine in which material is deposited onto the airfoil (9) by means of deposition welding, and the airfoil (9) is cooled during the deposition welding. The ...
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WO/2015/177473A1 |
The invention relates to a method for manufacturing a turbine engine vane made of a composite material with fibrous reinforcements compregnated by a matrix and including a blade, a platform located at one longitudinal end of the blade an...
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WO/2015/177429A1 |
The invention relates to a turbine rotor for a gas-turbine engine, said rotor including: an upstream turbine disc (1); a downstream turbine disc (5); an annular flange (b); a first shroud (11) connecting the upstream turbine disc to the ...
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WO/2015/179353A1 |
The invention relates to an exhaust-gas turbocharger (1), preferably for a passenger vehicle, comprising a compressor (2) having a compressor wheel (3), a turbine (4) having a turbine wheel (5) and a turbine housing (6), a shaft (7), whi...
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WO/2015/178974A2 |
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...
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WO/2015/175073A2 |
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...
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WO/2015/173312A1 |
The component of the turbomachine comprises:a body (406) of the component, a bond layer (404) covering a base surface of the body (406), and a top layer (402) covering the bond layer (404) and made of abradable ceramic material; the base...
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WO/2015/173182A1 |
The invention relates to an annular clamping nut (1) which is provided for being placed onto the end of a tie bar (2), in order to brace the latter, and which has in addition to a central recess (3) for receiving the tie bar (2) parallel...
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