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WO/2020/169499A1 |
Disclosed is a stator wheel of a turbomachine intended to be mounted in an aircraft, the turbomachine extending along an axis X, the turbomachine comprising a primary flow path for a first flow of air and a secondary flow path for a seco...
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WO/2020/169938A1 |
Method for repairing a blade (10) of a turbomachine rotor, particularly a turbomachine fan, this blade comprising a vane (12) made from an organic-matrix composite and a metallic shield (14) bonded to a leading edge of the vane, the meta...
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WO/2020/172493A1 |
In an aspect, a method of filling a plurality of cooling holes (12) in an airfoil component (10), the method comprises injecting a curable composition into a fill channel (8) such that the curable composition flows through the fill chann...
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WO/2020/165096A1 |
The invention relates to a rotor blade (1) for a thermal rotary machine, said rotor blade comprising: at least one blade region (3) forming an airfoil (2); and a blade root region (4) designed to fasten the rotor blade (1) to a rotor. Th...
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WO/2020/165527A1 |
The invention relates to a turbomachine blade (54) comprising a body (60) that extends mainly in a plane defined by a main axis B and a longitudinal direction, which is defined by a lower surface wall (66), an upper surface wall (68), a ...
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WO/2020/164214A1 |
Disclosed is an aero-engine turbine blade, comprising a front end (1), a pressure surface (2), a suction surface (3), and a tail end (4), wherein the front end (1), the pressure surface (2), the suction surface (3), and the tail end (4) ...
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WO/2020/167598A1 |
A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing tru...
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WO/2020/164979A1 |
There is disclosed a method of manufacturing a composite blade (100), and the composite blade. The method comprises a lay-up operation comprising laying up fibre reinforcement material (138) on an untwisted lay-up surface (134) to make a...
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WO/2020/167635A1 |
A method of controlling an extent of a thermal barrier coating (TBC) sheet spall and a hot gas path (HGP) component are disclosed. The method provides an HGP component having a body with an exterior surface. Controlling the extent of the...
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WO/2020/161943A1 |
Provided are a method for designing a blade with which it is possible to reduce a peak in a secondary flow loss appearing locally in a secondary flow region, and a blade obtained by means of said design. This method for designing a bla...
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WO/2020/159432A1 |
A system (50) and method (200) for repairing one or more components (70) using an additive manufacturing process includes securing the components (70) in a tooling assembly (52) such that a repair surface (72) of each component (70) is p...
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WO/2020/157406A1 |
The invention relates to a nickel-based superalloy comprising, in weight percentages, 5.9 to 6.5% of aluminum, 9.5 to 10.5% of cobalt, 4 to 5% of chromium, 0.1 to 0.2% of hafnium, 0.3 to 0.7% of molybdenum, 3.7 to 4.5% of rhenium, 7.5 to...
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WO/2020/158221A1 |
The present invention provides an overlay welding method with which it is possible for deformation to be adequately suppressed, even with a thin metal overlay layer or base material. More specifically, the present invention provides an o...
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WO/2020/156839A1 |
The invention relates to a method for capturing a coating (12) of a component (10), which component has at least one first subregion (14) and at least one second subregion (16), which adjoins the first subregion (14) and in which the mai...
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WO/2020/148504A1 |
The invention relates to a nickel-based superalloy comprising, in weight percentages, 4 to 6% of aluminum, 5 to 8% of cobalt, 6 to 9% of chromium, 0.1 to 0.9% of hafnium, 2 to 4% of molybdenum, 5 to 7% of rhenium, 5 to 7% of tantalum, 2 ...
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WO/2020/148490A1 |
A blade comprising a fibre reinforcement (200) having a three-dimensional weave densified by a matrix, the fibre reinforcement (200) comprising, in a single woven piece, a root part (212) and an aerodynamic profile part (211) extending i...
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WO/2020/148512A2 |
A lattice (6) formed of entwined links (9) in a cavity (5) encased by the external skin (4) of a blade (3) and (5) provided with parts of low mechanical strength (10) referred to as breakable, which are capable of rupturing when sufficie...
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WO/2020/148503A1 |
The invention relates to a nickel-based superalloy comprising, in weight percentages, 6 to 8% of aluminum, 12 to 15% of cobalt, 4 to 8% of chromium, 0 to 0.2% of hafnium, 0.5 to 4% of molybdenum, 3.5 to 6% of rhenium, 4 to 6% of tantalum...
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WO/2020/149854A1 |
A pre-swirler (14) for a gas turbine engine (10) is presented. The pre-swirler (14) includes a hole (26) drilled through a component (11, 12) of the gas turbine engine (10). The pre-swirler (14) includes a pre-swirler plug (16) that is p...
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WO/2020/148493A1 |
The invention relates to an aerodynamic arm (100) for an aircraft turbine engine casing, characterised in that it comprises: - a tubular outer shell (110) having a generally elongate shape extending substantially along an axis (A-A), the...
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WO/2020/148981A1 |
A turbine moving blade is provided with a leading edge part on which a plurality of cooling holes are formed. The plurality of cooling holes include m (where m is an integer of two or more) arranged in a first range in a blade height dir...
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WO/2020/106343A9 |
A novel mechanism for reducing boundary layer friction and inhibiting the effects of uncontrolled fluid turbulence and turbulent layer separation, thus reducing the body drag, kinetic energy losses and lowering engine and pump fuel consu...
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WO/2020/145971A1 |
There is provided a process for joining two opposed superalloy surfaces (104, 106) comprising positioning a plug (110) within a gap (108) between a first (104) and a second superalloy surface (106), the plug (110) comprising a superalloy...
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WO/2020/142113A1 |
A platform seal and damper assembly for turbomachinery (100), such as fluidized catalytic cracking (FCC) expanders or gas turbine engines; and methodologies for forming such assembly are provided. An axially-extending groove (160) is arr...
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WO/2020/140159A1 |
The invention relates to a hydrokinetic turbine for producing kinetic energy and transforming it into electrical energy by means of pressure flow and water volume, the turbine having highly efficient rotation speed, low noise and vibrati...
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WO/2020/137599A1 |
A rotor blade (15) embedded in a disc (17) of a rotating body (1) wherein, in a transverse section, a blade root (21) of the rotor blade has at least one stage of protruding parts (23), which protrude on both sides in a direction that in...
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WO/2020/136524A1 |
Axial turbine (100) with two supply levels for the expansion phase of a working fluid in a thermodynamic vapor cycle or in an organic Rankine cycle comprising a shaft (2), a plurality of rotor blade arrays (R1-Rn) and corresponding suppo...
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WO/2020/136020A1 |
The present invention refers to a coolable component for a streaming engine providing an improved cooling. Furthermore, the present invention refers to a streaming engine containing such coolable component. Additionally, the present inve...
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WO/2020/128384A1 |
The invention relates to a turbomachine assembly (1) comprising a fan (2) and a booster drum-type part (3), the fan (2) comprising: - blades (20) comprising an airfoil (23) and an extension (30) mounted on and attached to the trailing ed...
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WO/2020/128367A1 |
The invention concerns a part (10) for a turbomachine (1) made from composite material comprising a fibrous reinforcement (11) having a three-dimensional weave that comprises a first set of yarns (12) made from a first material, characte...
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WO/2020/128201A1 |
The invention relates to a bladed disc (1) for masking a moving disc of a jet engine, comprising blades (2), each blade (2) comprising a pressure-side wall (Pi) and a suction-side wall (Pe) that meet at a leading-edge (3) and at a traili...
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WO/2020/128398A1 |
The invention concerns a method for coating a core (1) for producing a turbomachine part (2) by isostatic compacting, for example a leading-edge shield of a blade, the coating method comprising the steps of: - S1: covering the core (1) b...
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WO/2020/127551A1 |
The present invention concerns a metal reinforcement for a turbomachine blade comprising an aerodynamic surface which extends between a leading edge and a trailing edge, the reinforcement comprising a base (21) forming its leading edge (...
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WO/2020/131030A1 |
A gas turbine engine comprises a first passage, a second passage and a bypass channel. The first passage transmits a first leakage flow (335) from a bypass channel chamber to a pre-swirl supporting structure (310) and through an inner se...
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WO/2020/129390A1 |
A turbine blade is provided with: a blade shape part having a pressure surface and a negative pressure surface that extend between a front edge and a rear edge thereof; and a platform including an end wall to which a base end of the blad...
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WO/2020/125862A1 |
The invention relates to a rotor for a turbocharger, comprising a hub (1) and a plurality of rotor blades (9) which are fastened to the hub and are arranged on the hub (1) such that a medium flowing through the turbocharger (24) can flow...
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WO/2020/128394A1 |
The present invention concerns a turbine part comprising a substrate made of nickel-based monocrystalline superalloy, comprising chromium and at least one element chosen among rhenium and ruthenium, the substrate having a γ-γ' phase, a...
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WO/2020/126258A1 |
The invention relates to a ceramic material which contains yttrium oxide as stabilizers and at least one of the materials erbium oxide or ytterbium oxide provides a phase having sintering stability for a ceramic material for ceramic laye...
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WO/2020/131062A1 |
A bladed rotor system (10) for a turbomachine includes a circumferential row of blades (14) mounted on a rotor disc (12), and includes a plurality of under-platform dampers (30). Each damper (30) is located between adjacent blade platfor...
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WO/2020/128401A1 |
The invention relates to an aeronautical part, such as, for example, a turbine blade or a distributor vane, which is used in aeronautics, comprising at least one reactive layer adapted to react with at least one CMAS compound, the reacti...
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WO/2020/128402A1 |
The present invention relates to a turbine part, comprising a substrate, an environmental barrier comprising at least one layer selected from a thermally insulating layer, a sub-layer adapted to promote adhesion between the substrate and...
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WO/2020/120898A1 |
The invention relates to a turbomachine rotor blade which is characterized in that: - the ratio between the maximum thickness and the chord at 30% of the height of the blade is between 20% and 42% of the ratio between the maximum thickne...
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WO/2020/122885A1 |
A unit cell (26) for use in a damping system (24) includes: an impacting structure (34); a cavity (32) encapsulating the impacting structure (34), the cavity (32) including a first hemisphere (32A) and a second hemisphere (32B), the cavi...
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WO/2020/120921A1 |
The invention relates to a fan blade (1) comprising: - an aerofoil (8) made of a composite material comprising a fibrous reinforcement densified by a polymer matrix, a leading edge (4) and a trailing edge (5), and - a structural shield (...
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WO/2020/120897A1 |
The invention relates to a turbomachine rotor blade comprising a plurality of blade sections stacked along an axis between a blade root and a blade head defining between them the height of the blade, each blade section comprising a chord...
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WO/2020/122886A1 |
A nested lattice structure 29 for use in a damping system includes a first lattice structure 26 including: a first outer passage 30 including a hollow interior 45; a second outer passage 32 including a hollow interior; and an outer node ...
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WO/2020/120862A1 |
The invention concerns a turbine blade (11) comprising a root (P) carrying an impeller (12) terminated by a tip (S) in the form of a squealer tip (B). This impeller (12) also comprises a serpentine median circuit (28), including a first ...
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WO/2020/120962A1 |
A seal assembly for use in a turbomachine, the seal assembly comprising an oil seal plate; a rotatable component which defines a central axis and is received in a central aperture of the oil seal plate; and an annular seal which comprise...
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WO/2020/120902A1 |
A method for repairing a part (11) made of an organic matrix composite (100) covered with at least one layer of paint (102) comprises the following steps: a) removing the paint from a damaged zone of the part (11), b) removing the compos...
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WO/2020/115410A1 |
The invention relates to a turbine or a compressor for a gas turbine engine, comprising a plurality of blades (16) surrounded by an external ring (8) defining an external flow line (8a) for a gas stream to flow, each blade, on one hand, ...
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