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WO/2020/233925A1 |
The invention relates to a method for optimizing energy conversion installation service measures.
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WO/2020/236329A1 |
A nozzle segment (451) for a gas turbine engine (100) with turbine airflow (15) passing through the gas turbine engine. The nozzle segment including an upper shroud (452) and an inner hub (456). The nozzle segment including a first airfo...
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WO/2020/234796A1 |
Airfoils, gas turbine engine assemblies including such airfoils, and methods of manufacturing the same. The airfoil includes multiple cooling channels proximate a leading edge of the airfoil, each of the cooling channels including an inl...
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WO/2020/234572A1 |
The present invention describes a ring fastener (10) comprising a discontinuous band (11) having a first end (14) and a second end (16). The first end (14) comprises a pair of spaced-apart elongate finger members (15a,15b) (having a firs...
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WO/2020/231835A1 |
A wind turbine blade including a shell structure defining a leading edge and a trailing edge, and an upwind shell and a downwind shell joined along at least one of the leading edge or the trailing edge. The shell structure includes an as...
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WO/2020/232018A1 |
The present invention is an automated wind turbine servicing system that includes a rover, and uses an active electro-mechanical gripping roller system to attach to the horizontally positioned airfoil and navigate along it in order to cl...
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WO/2020/229056A1 |
The invention relates to an aircraft turbine engine module (60, 110) comprising a ventilation device configured to circulate a flow of cooling air through the turbine engine module, the ventilation device comprising an air outlet, sealin...
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WO/2020/224689A1 |
The present invention relates to a turbine blade (10) with a blade airfoil (12) for flow deflection, a blade root (11) for fastening in a groove (21), at least one cavity (13), and at least one channel (14), which is connected to the cav...
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WO/2020/227501A1 |
An airfoil for a gas turbine engine includes an airfoil body extending between leading and trailing edges in a chordwise direction and extending from a root section in a spanwise direction, and the airfoil body defining pressure and suct...
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WO/2020/224995A1 |
The invention relates to a turbine vane comprising a root carrying a blade terminated by a tip in the form of a squealer tip, the blade having an intrados wall and an extrados wall, as well as a leading edge, a trailing edge, and a tip w...
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WO/2020/225508A1 |
The invention relates to a part made of silicon-based ceramic material or silicon-based ceramic matrix composite (CMC) comprising an environmental barrier coating (EBC), the coating (12, 13) comprising a bonding layer (12) arranged on th...
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WO/2020/220498A1 |
A low-pressure turbine blade having a wavy suction surface, applicable to reducing profile loss of a high-load low-pressure turbine blade and an ultra-high-load low-pressure turbine blade on an aero engine. The low-pressure turbine blade...
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WO/2020/221624A1 |
The present invention relates to a method for coating an aircraft turbomachine component (1) with an erosion resistant coating, the method comprising: - depositing the erosion resistant coating by hot powder coating onto an aircraft turb...
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WO/2020/218209A1 |
A polyamide resin composition containing a semi-aromatic polyamide (A) having a melting point of 290-330°C and a fibrous reinforcing material (B), wherein the polyamide resin composition is characterized in that the creep strain in the ...
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WO/2020/217006A1 |
The invention relates to a method for repairing a vane (1) made of composite material, which extends along a so-called axial direction (X), said vane (1) comprising a root (2) and a blade (3), wherein the axial end thereof, opposite the ...
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WO/2020/211887A1 |
The invention relates to layer building process for the additive manufacture of at least one wall region (12) of a component (14). The layer building process comprises at least the steps a) applying at least one powder layer of a materia...
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WO/2020/214514A1 |
A casing component is configured to form part of a flow path in a turbine. The casing component includes a base (12) made of nodular cast iron, and a repaired region (14) in the base. The repaired region includes a butter layer (32) appl...
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WO/2020/207909A1 |
The invention relates to a contra-rotating turbine (C) of a turbine engine (10) extending about an axis (X) and comprising an inner rotor configured to rotate about the axis of rotation (X), and comprising an inner drum to which an inner...
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WO/2020/209847A1 |
A component (68) fabricated from a three dimensional (3D) ceramic matrix composite (CMC) material (142). The component includes an outer wall (100) and an inner wall (104) spaced apart from the outer wall to form a cooling channel (110) ...
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WO/2020/203868A1 |
A turbine wheel (10) for a supercharger is equipped with: a shaft (12) formed from a Ni alloy; and a plurality of blades (14) provided around the shaft (12) and formed from a columnar crystal or single crystal of a Ni alloy, with the cry...
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WO/2020/205733A1 |
A method for protecting a coating on a surface of a component is provided. The method includes a coating step that coats at least a portion of the component with a ceramic slurry. A projecting step projects a pattern of light onto the co...
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WO/2020/199370A1 |
An aero-engine turbine blade having a cooling structure, comprising a leading end (1), a pressure surface (2), a suction surface (3) and a trailing end (4); the leading end (1), the pressure surface (2), the suction surface (3) and the t...
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WO/2020/204872A1 |
The present invention relates to a method for repairing a tip portion (22) of a turbine blade (10) having a structural defect. The method includes removing a damaged section with a structural defect in a tip portion (22) and the provisio...
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WO/2020/201653A1 |
Blade (13) for a turbine engine intended to be arranged about an axis (X) extending radially between a radially outer end (16) and a radially inner end (18), the blade comprising at least one cooling cavity (24, 26) opening on the radial...
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WO/2020/205328A1 |
A method for protecting a coating on a surface of a component is provided. The method includes a coating step for coating at least a portion of the component with a ceramic slurry. A projecting step is used for projecting a pattern of li...
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WO/2020/205713A1 |
A method for protecting a coating on a surface of a component is provided. The method includes a coating step for coating at least a portion of the component with a ceramic slurry. A projecting step is used for projecting a pattern of li...
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WO/2020/201642A1 |
Variable-pitch stator blade (3) comprising an airfoil (4) including a central portion (10) which has a first skeleton line delimited by a leading edge (9) and a trailing edge (12), and a first rope; an end portion (14,15) having a second...
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WO/2020/193913A1 |
The invention relates to a turbine engine blade (20) comprising: - an airfoil (21) with a pressure-side wall and a suction-side wall which are connected upstream by a leading edge (26) and downstream by a trailing edge (27), - a cooling ...
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WO/2020/193043A1 |
The present invention relates to a seal system for gas turbine, the seal comprising a stator (4) and a blade (3) with a blade tip (25) facing the stator (4). The blade comprises a protective ceramic coating (21) having an inner ceramic l...
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WO/2020/193899A1 |
Aircraft turbomachine blade (102), said blade comprising at least one inner cavity (100) for circulating a ventilation air flow, said cavity comprising a wall (104) which comprises first projecting elements (106) oriented in a first dire...
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WO/2020/193912A1 |
The invention relates to a turbine engine vane (20) comprising a blade (21) extending along a radial axis and a first cooling circuit (28) arranged inside the blade, the first cooling circuit (28) comprising a first cavity (34) and a sec...
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WO/2020/188212A1 |
The invention relates to a tubular ventilation sleeve (1) for a turbomachine distributor, in particular for an aircraft, the sleeve having a generally elongate shape along an axis (A-A) and comprising a perforated tubular wall (1a) aroun...
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WO/2020/190280A1 |
A turbine (10) includes a disk (25) having a plurality of protrusions (120) arranged such that any two adjacent protrusions (120) define an axial entry fir tree space (125), each protrusion (120) defining an outermost lobe (165) having a...
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WO/2020/189237A1 |
A turbine blade and a gas turbine are provided with: an airfoil portion (41) internally including a cooling air passage (60); a platform (42) provided in a blade base end portion (55) in a blade height direction (Dh) of the airfoil porti...
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WO/2020/183075A1 |
In order to master the consequences of a decoupling event on an axial toothed coupling mechanism (47) of an assembly of rotary elements (33, 35) of a gas turbine, and in a situation of initiation of axial decoupling, an excrescence (51) ...
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WO/2020/182349A1 |
A blade for fluid catalytic cracking (FCC) flue hot gas expander with a layer of hard abrasive material localized on the blade tip that contributes to reducing the accumulation of FCC catalyst residuals in the expander.
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WO/2020/183840A1 |
This method passes through: a measuring step of carrying out position measurement, in a cord length direction, by means of a touch probe 4 at a plurality of predetermined measuring points a to h from a blade root to a blade tip along a l...
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WO/2020/183109A1 |
The invention relates to a portion of a turbofan (1) extending about a longitudinal axis (A), comprising: - an outer wall (Pe) and an inner wall (Pi), defining a secondary duct portion (Vs), - a cascade of guide vanes (OGV), each guide v...
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WO/2020/184092A1 |
The present invention provides a turbine rotor blade and the like with which it is possible to improve durability of a contact surface and enhance blade reliability. This turbine rotor blade is equipped with a blade body and a tip shroud...
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WO/2020/178295A1 |
The present invention relates to a method for producing an engine component (1) having a cooling duct arrangement (200) which has a plurality of cooling ducts (2), each having an inflow opening (20a, 20b, 20c), the inflow openings being ...
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WO/2020/178300A1 |
An aircraft turbomachine rotor (2) comprising a rotor disc (20) extending transversely with respect to a longitudinal axis X, a plurality of blades (21) and a damping device (1) comprising: a support ring (7) configured to extend transve...
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WO/2020/180325A1 |
A bond coating material providing unexpectedly high thermal cyclic fatigue resistance and sulfidation resistance, and unexpectedly prolonged thermal cycle life in high temperature environments of gas turbine engine components with and wi...
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WO/2020/177929A1 |
The turbomachine comprises a casing arrangement and a shaft supported for rotation therein. The shaft is rotatingly supported by a first and second bearing unit. First and second compressor sections are provided in the casing arrangement...
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WO/2020/178510A1 |
The invention relates to a method for assembling a body (71) and a cover (72) of a vane (7) by polymerisation of a resin. The cover (72) is positioned on a junction face of the body (71) covered with this resin. According to the inventio...
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WO/2020/176841A1 |
An exemplary embodiment provides a method of predicting a geometry of a turbine blade, comprising: obtaining a point cloud of the turbine blade, the point cloud comprising a plurality of points corresponding to locations on an external c...
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WO/2020/176339A1 |
A compressor according to an exemplary aspect of the present disclosure includes, among other things, a rotor configured to rotate with respect to a stator, the stator having an abradable portion. At least one labyrinth seal is between t...
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WO/2020/174163A1 |
The invention relates to a method of assembling a member (71) and a cap (72) of a vane (7) using a tool (9) which allows the application of a pressing force of the cap (72) against the member (71) during a step of polymerisation by heati...
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WO/2020/171282A1 |
The present invention relates to a blade protection device. A blade protection device, according to one embodiment of the present invention, is a blade protection device which is connected to a blade of a gas turbine engine and protects ...
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WO/2020/169918A1 |
The invention relates to a method for manufacturing a compressor impeller or rotor comprising a hub (21) that carries blades (26), involving a step of manufacturing a hub (21) which comprises all or some of the blades (22), and a step of...
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WO/2020/172016A1 |
Various embodiments include a dense abradable coating, a method of reducing rub damage to a turbine engine part by applying the dense abradable coating thereto, and a turbine engine part having the abradable coating thereon. Particular e...
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