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WO/2021/152274A1 |
Disclosed is a method for the heat treatment of at least one bar made from titanium aluminide alloy for manufacturing at least one low-pressure turbine blade for a turbomachine, comprising hot isostatic pressing of the bar, characterised...
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WO/2021/148751A1 |
Part or assembly of parts for a turbomachine, comprising at least first and second blades (3I, 3E), and a platform (2) from which the blades extend. The platform (2) has, between the pressure face of the first blade (3I) and the suction ...
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WO/2021/148750A1 |
The present invention relates to a blade (7) comprising: - a composite material structure (17), - a blade root fastening portion (9) further comprising a shoulder (10) extending into the recess from the wall - a base (18) arranged in the...
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WO/2021/148740A1 |
The invention relates to a rotor for an aircraft turbine engine, comprising at least one mobile disk (63) supporting moving blades (64), the mobile disk (63) comprising a plurality of cells (632), into which feet (642) of the moving blad...
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WO/2021/150579A1 |
A method and apparatus for maintaining integrally bladed rotors (IBR) includes using first vibration data from a IBR vibration apparatus of a first IBR to determine a set of values for a corresponding set of inherent vibratory properties...
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WO/2021/148077A1 |
The invention relates to a sealing-air apparatus (10) for a turbomachine (100), comprising a sealing device (20) for sealing a sealing gap (50) between two components (30, 40) of the sealing-air apparatus (10) with respect to a sealing-a...
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WO/2021/150418A1 |
A turbine rotor blade is additively manufactured and includes an airfoil body including a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges. A shank is at a radial inner e...
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WO/2021/148743A1 |
Fan module (20) for an aircraft turbomachine testbed, this module comprising: - a drive shaft (22), - a fan (24) comprising a disc (26) and bearing blades (28) extending substantially radially outward from the disc, and - a thrust balanc...
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WO/2021/144519A1 |
The invention relates to an assembly (1) for a turbine engine extending along an axis, comprising a stator, a low-pressure compressor shaft (4), a low-pressure compressor comprising a rotor comprising a drum (2) rotatably coupled to the ...
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WO/2021/139492A1 |
A turbine blade honeycomb spiral cavity cooling structure, comprising hollow turbine blades (1), honeycomb spiral cavities (3), and spoiler columns (4). A cold air channel (2) is provided inside each hollow turbine blade (1). The cold ai...
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WO/2021/140301A1 |
The invention relates to an assembly for a turbomachine turbine (10) with longitudinal axis (A-A), comprising: - a turbine rotor disc (12) centred on the longitudinal axis, - a turbine shaft (14) centred on the longitudinal axis and rota...
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WO/2021/139956A1 |
The invention relates to a method for repairing damaged blade root receiving grooves (1) of a rotor (2), having the steps of: a) detecting data of damaged areas, in particular cracks, present within one or more blade root receiving groov...
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WO/2021/104002A9 |
A curvilinear exhaust slit structure for a trailing edge of a turbine blade, comprising a hollow turbine blade (1), an inner cavity cooling gas passage (2), trailing edge exhaust slit passages (3) and trailing edge slit ribs (4). The inn...
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WO/2021/123098A1 |
The invention relates to a turbomachine compressor module (47), comprising an annular row of structural arms (46) provided with pivotable flaps (60). The arms (46) can define inter-arm spaces (56) between two circumferentially adjacent a...
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WO/2021/121456A1 |
The present invention relates to a blade for a gas turbine, in particular of an aero engine, having a blade aerofoil (B; V) which has a blade-root-side first profile section (P1B; P1V) and a blade-tip-side second profile section (P2B; P2...
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WO/2021/123594A1 |
Disclosed are a method for manufacturing a blade made of composite material with an attached metal leading edge for a gas turbine aeronautical engine as well as the corresponding blade, wherein the leading edge (200) comprises a first po...
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WO/2021/123577A1 |
The invention relates to a method for manufacturing a metallic turbomachine bladed disk (blisk) reinforced with an insert made of a metallic matrix composite material, said method comprising the following step: - (E1): winding ceramic fi...
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WO/2021/123146A1 |
The invention relates to a turbomachine compressor module (47), comprising an annular row of structural arms (46) defining inter-arm spaces (56) between two circumferentially adjacent arms (46, 48); and an annular row of stator vanes (39...
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WO/2021/121458A1 |
The present invention relates to a guide vane (20) for arrangement in a gas duct (2) of a turbomachine (1), having a guide vane blade (23), which, viewed in a tangential section, has a vane blade profile (24) with a leading edge radius R...
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WO/2021/123576A1 |
The invention concerns a method for manufacturing a one-piece bladed disc for a turbomachine, the method comprising the following step: - (E1): manufacturing a plurality of blades, the blades comprising a root and a profiled portion; cha...
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WO/2021/115510A1 |
The invention relates to a rotor (10) for a turbomachine (100), having at least one blade and having at least one rotor main part (20) which has at least one recess (22) in which a blade root (40) of the at least one blade is interlockin...
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WO/2021/115539A1 |
The invention relates to a device for applying coatings to strongly curved component surfaces. The device comprises a flexible base plate (1) having a toothing (3) on the side, a channel (4) arranged parallel to the toothed side, and a s...
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WO/2021/115914A1 |
A protective coating suitable for a wind turbine blade is described, the protective coating comprising a thermoset polymer and a fibrous macromolecule, wherein at least part of the thermoset polymer is bonded to the at least part of the ...
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WO/2021/118916A1 |
A refrigerant compressor according to an exemplary aspect of the present disclosure includes, among other things, an impeller configured to rotate about an axis, and a shroud. The impeller has a plurality of blades. The shroud is secured...
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WO/2021/115511A1 |
The present invention relates to a method for detecting a first component (21.1) of a turbomachine (1), in which method - a first image (41) of the first component (21.1) is recorded (61); - on the basis of the first recorded image (41),...
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WO/2021/116567A1 |
Turbine rotor wheel (50), in particular a contra-rotating rotor wheel, for an aircraft turbomachine, comprising: - a rotor disk (52), - an annular shroud (54) extending around the disk, and - blades (56) arranged between the disk and the...
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WO/2021/110190A1 |
The invention relates to a method comprising the steps: - first exciting of the object by means of a multi-frequency signal; - detecting a first response signal of the object at one or more measurement points on the object; - transformin...
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WO/2021/110899A1 |
The invention relates to a turbine blade having a blade airfoil (18). A first cooling path (30) for a first coolant stream (M1) and a second cooling path (50) for a second coolant stream (M2) are formed within the blade airfoil (18). The...
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WO/2021/105385A1 |
A method of disassembling a rotor module (30) of a gas turbine engine (10). The gas turbine engine (10) comprising a rotor output shaft (92). The rotor module (30) comprising a centre-bolt (84), a sleeve (90), at least one rotor stage (5...
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WO/2021/104553A1 |
The invention relates to a substrate, in particular a component of a turbomachine, made from a composite material having a ceramic matrix and having a protective layer against environmental influences, the protective layer being arranged...
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WO/2021/105612A1 |
Disclosed is a process for manufacturing a blade (10) made of composite material for a turbomachine, in particular an aircraft turbine engine, said blade comprising an airfoil (12) having a pressure side (14) and a suction side (16) whic...
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WO/2021/105600A1 |
Disclosed is a process for manufacturing a blade (10) made of composite material for a turbomachine, in particular an aircraft turbine engine, said blade comprising an airfoil (12) having a pressure side (14) and a suction side (16) whic...
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WO/2021/102582A1 |
A rim-rotor assembly has an annular structure including a composite rim and a hub. Blades project from the hub, tips of the blades contacting the annular structure, the blades configured to be loaded in compression against the annular st...
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WO/2021/099722A1 |
Disclosed is a method for removing a leading edge (5) attached to a fan blade (4), the fan blade (4) comprising a first material, and the leading edge (5) comprising a second material different from the first material, the method compris...
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WO/2021/099736A1 |
The invention relates to a turbomachine rotary-fan blade (2) having a predetermined breaking zone (5), which extends from the upstream edge (22) along a given length (L) and from the blade-tip edge (27) over a given height (H). According...
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WO/2021/101648A1 |
Embodiments of the present disclosure generally relate to protective coatings on turbine blades, turbine disks, and other aerospace components and methods for depositing the protective coatings. In one or more embodiments, a turbine blad...
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WO/2021/094042A1 |
A direct mechanical machining of a coated component (20) after use removes the need for a coating-removal and selective hollowing step and a selective repair of cracks (7), since a design adaptation leads to a component (20) being engine...
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WO/2021/095695A1 |
This turbine blade is provided with an airfoil portion which extends in a blade height direction and includes a pressure surface and a negative pressure surface that extend between a leading edge and a trailing edge, a shroud portion pos...
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WO/2021/094700A1 |
A modular and autonomous assembly (1) for detecting the angular position of the blades of an impeller intended to be mounted on a turbine engine, the assembly (1) comprising: - at least one electrical power source (711b, 71b, 72b) enabli...
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WO/2021/094026A1 |
The invention relates to a method for the layer-by-layer additive manufacturing of a composite material (V), comprising the selective irradiation of a base material (P) to produce a first, dense material phase (1) and to produce a second...
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WO/2021/095118A1 |
This rotating body balance adjusting method includes: an unbalance acquiring step for acquiring the position and the amount of unbalance of a rotating body, after a first balance correcting step for correcting unbalance of the rotating b...
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WO/2021/084203A1 |
The invention relates to a turbine (1) comprising a casing, an outer metal shroud (9), an inner metal shroud (5) and an annular distributor (2) having a plurality of CMC ring sectors (20), each sector comprising a mast (6), an inner plat...
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WO/2021/084193A1 |
Disclosed is a fibrous preform (100) made of three-dimensional woven fabric for an attached fan platform, comprising a first air flow passage wall skin (110) of the platform, a second, opposite wall skin (120), and a longitudinal stiffen...
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WO/2021/083442A1 |
The present invention relates to a guide vane assembly for a turbomachine, in particular a compressor stage or turbine stage of a gas turbine, comprising at least one guide vane that is adjustable about a rotational axis (D), the vane bl...
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WO/2021/084194A1 |
Disclosed is a three-dimensional fibrous preform (100) of a fan (2) blade (10) comprising a blade root (110) and a blade airfoil (120) between the blade root and a free end (121) of the preform. The airfoil has an area (140) with two ski...
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WO/2021/084192A1 |
A fibrous preform (100) obtained by three-dimensional weaving, comprising a first skin (110), a second skin (120), and a central portion (130) connecting them and forming a stiffening element (4). In a transverse plane, transverse thread...
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WO/2021/083441A1 |
The present invention relates to a rotor blade arrangement for a turbomachine, with a rotor blade which has a sealing tip radially on the outside, and with a seal arrangement, wherein the seal arrangement forms a radially inwardly open c...
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WO/2021/087503A1 |
A turbine blade (1) includes an airfoil section (10), wherein at least one cooling hole (32) is formed a tip floor (30) of the airfoil section (10), which is fluidically connected to an internal coolant cavity (28) of the airfoil section...
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WO/2021/084205A1 |
One aspect of the invention relates to a method for compacting (100) an anti-corrosion coating (110), characterized in that it comprises a step (101) of spraying water-soluble particles (130).
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WO/2021/080675A1 |
An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: at least one coolant feed channel fluidly coupled to a supply of cooling fluid; and an interconnect...
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