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WO/2020/260810A1 |
The invention relates to an inter-blade platform (20) of a turbomachine fan (1), comprising: - a base (21) comprising a first surface (22) configured to delimit a flow path in the fan (1) and a second surface (23) on the opposite side fr...
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WO/2020/263394A1 |
An outlet guide vane assembly in a gas turbine engine is presented. The outlet guide vane assembly includes an inner shroud and an outlet guide vane having an inner platform. The inner shroud has a flange arranged at aft side that is bol...
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WO/2020/260835A1 |
Method for manufacturing a housing (3) for an aircraft turbine engine, said housing comprising: • - an annular body (30) extending around an axis A and comprising a securing flange (31, 32) extending radially outwards at each of the ax...
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WO/2020/256678A2 |
The present invention relates to a brush seal (1) which provides sealing between the high pressure regions and the low pressure regions around the shafts which rotate at high speed and particularly provided in turbo machines like airplan...
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WO/2020/244690A1 |
The present invention relates to a cooling system for cooling at least one first turbine stage (1) and at least one downstream second turbine stage (2) of a gas turbine, in particular an aircraft engine gas turbine, wherein the cooling s...
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WO/2020/241782A1 |
This steam turbine is provided with: a rotating shaft which rotates about an axis; moving blades provided on an outer circumferential surface of the rotating shaft; a casing covering the rotating shaft and the moving blades from the oute...
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WO/2020/239732A1 |
The invention relates to a dynamic seal for a turbomachine, comprising a fixed portion (21) provided with at least one abradable wear part (23) and a movable portion comprising at least one lip arranged to interact with the at least one ...
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WO/2020/239559A1 |
A heatshield for a gas turbine engine. The heatshield comprising a main body having a leading edge, a trailing edge, lateral edges, a first surface and a second surface, the first surface being exposed to a hot working gas in use passing...
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WO/2020/240118A1 |
Sealing ring (36, 38) for a wheel (26) of an aircraft turbomachine turbine, said ring comprising an annular body (51) extending around an axis of revolution (A) and comprising an outer surface (51a) and an inner surface (51b) which is co...
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WO/2020/239560A1 |
A heatshield for a gas turbine engine, comprising a main body having a leading edge, a trailing edge, lateral edges, a first surface and a second surface. The first surface being exposed to a hot working gas in use passing through the ga...
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WO/2020/234007A1 |
The invention relates to a device for sealing a gap (57) between two components (4, 6) of a turbine of a gas turbine engine. The device comprises: a turbine vane ring (400) having a plurality of turbine vane segments (4), each turbine va...
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WO/2020/224891A1 |
The invention relates to a turbine ring assembly (2) extending about an axis (X-X), comprising a plurality of ring sectors (10) which are made from a ceramic matrix composite material and form a turbine ring (4) and a ring support struct...
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WO/2020/208224A1 |
The present invention relates to a labyrinth seal for a turbine engine, in particular of an aircraft, comprising a rotor element and a stator element extending around the rotor element, the rotor element being suitable for rotating relat...
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WO/2020/208316A1 |
The invention relates to a method for detecting at least one roughness in a face (10a) of an abradable layer (10) in a fan casing (3). The method comprises a step of applying a first (12) and a second (13) coating covering the first (12)...
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WO/2020/200892A1 |
The invention relates to a device for fastening sealing plates (5) between components of a gas turbine engine. The device comprises a vane ring (400) which comprises a plurality of vane segments (4), wherein each vane segment (4) has an ...
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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/2020/193043A1 |
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/2020/193923A1 |
The invention relates to a fan rotor (1) for a turbomachine, comprising a fan disk (2), fan blades (3) with a leading edge (3a) and a trailing edge (3b), platforms (4) inserted between the blades (3) and fixed to the periphery of the dis...
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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/2020/183933A1 |
This rotating machine is provided with a rotor which rotates about an axis, a stator facing the rotor in the radial direction, and a plurality of sealing fins (70) which project from one of the rotor and the stator toward the other there...
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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/2020/178490A1 |
The invention relates to an assembly for a turbomachine turbine, comprising a casing (1) extending circumferentially about an axis X, and sectors (2) intended to form a ring able to delimit a gas flow duct, each sector (2) comprising a f...
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WO/2020/174801A1 |
This diaphragm for a steam turbine has a diaphragm inner wheel, a diaphragm outer wheel, and a wing section that are integrally formed, wherein: the diaphragm comprises a collector ring that holds a seal fin having a radial spill strip s...
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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/2020/172016A1 |
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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WO/2020/169986A1 |
There is provide a seal assembly (2) comprising: a first component (8) and a second component (10) spaced apart from the first component so as to define a passage (12) for the transfer of fluid from an inlet (14) of the seal assembly to ...
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WO/2020/172034A1 |
Various embodiments include honeycomb structures including an abradable material, and a method of applying such honeycomb structures to steel components of a gas turbine engine in order to reduce rub damage. Particular embodiments includ...
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WO/2020/157405A1 |
A turbomachine stator sector (100) comprises a plurality of vanes (110) extending in a radial direction (DR) between a first end (110a) and a second end (110b) and in an axial direction (DA) between a leading edge (111) and a trailing ed...
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WO/2020/158106A1 |
This rotary machine comprises: a casing 11 that is hollow inside; a rotor 12 rotatably supported inside the casing 11; a moving blade 14 secured to the outer peripheral section of the rotor 12; a stationary blade 13 that is, in the steam...
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WO/2020/158104A1 |
A rotary machine is provided with: a casing 11 that has a hollow shape; a rotor 12 that is rotatably supported inside the casing 11; a stationary blade 13 that is fixed to an inner peripheral part of the casing 11; a moving blade 14 that...
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WO/2020/157438A1 |
The invention concerns a fan casing (10) for an aircraft turbomachine, comprising an annular body (11) extending around an axis and equipped with an annular attachment flange (12a, 12b) at each of its axial ends, and an annular coating (...
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WO/2020/158105A1 |
This rotating machine is provided with: a casing 11 having a hollow shape; a rotor 12 supported with freedom to rotate inside the casing 11; stationary blades 13 fixed to an inner circumferential portion of the casing 11; moving blades 1...
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WO/2020/151925A1 |
A gas (or steam) turbine (200) is disclosed including: a rotor with at least one array of rotor blades (213-1), a stator with a casing (261) and a shroud ring (250); the shroud ring (250) extends around the array of blades rotor (213-1) ...
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WO/2020/151578A1 |
A turbine housing integrated with an active clearance control apparatus comprises a housing (100), a gas inlet pipe (200), a gas collection container (300), and a shunt pipe (400). The housing (100), the gas inlet pipe (200), the gas col...
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WO/2020/149738A1 |
A valve carrier ring (1) for carrying a self-closing dispensing valve is adapted to be assembled with a closure body of a container. The valve carrier ring (1) comprises an annular seat portion (13) comprising a support surface (14) for ...
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WO/2020/148489A1 |
The invention relates to an assembly for a turbomachine, having a stator (1) and a rotor (2) that is able to pivot with respect to the stator (1) about an axis, the rotor (2) having blades that each have an airfoil (3) connected to a rad...
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WO/2020/144435A1 |
Disclosed is a method for assembling/disassembling a turbine ring assembly comprising a turbine ring (1) made of ceramic matrix composite material and a ring support structure (3) made of metal, equipped with a central shroud (31) and at...
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WO/2020/144087A1 |
A device configured to seal a circumferential gap between a first turbomachine component and a second turbomachine component mutually rotatable about a longitudinal axis. The device is provided with a first sealing element connected to t...
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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/2020/141284A1 |
The invention concerns a turbine nozzle, comprising a plurality of angular nozzle sectors (6) each angular sector (6) comprising two inner and outer platform sectors, connected together by a plurality of radial blades (63), each inner pl...
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WO/2020/136374A1 |
A seal system for a bearing chamber (22) of a turbomachine includes the baffle element (70) encircling the axis (25) of the machine. The baffle element is formed with front surface including both a recess (73) which defines acircumferent...
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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/2020/128338A2 |
Turbine ring assembly having indexed flanges. The invention relates to a turbine ring assembly comprising ring segments (10) which form a turbine ring (1) and a ring support structure (3), each ring segment (10) having a part forming an ...
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WO/2020/126519A1 |
The invention relates to a ring-element (SPR) of a shaft seal (SHS) extending circumferentially along a central axis (X), - wherein said ring-element (SPR) is provided with conducts (RCD) to supply a seal fluid (SFL) from radially outsid...
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WO/2020/131024A1 |
A sealing apparatus (30) for sealing a clearance between a rotatable component (34) and a surrounding stationary component (32) in a gas turbine engine (10), includes a seal shoe (36) positioned proximate to the rotatable component (34) ...
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WO/2020/129234A1 |
A turbomachine according to one embodiment is a turbomachine comprising an impeller having at least one vane and a casing that rotatably accommodates the impeller, wherein when the impeller has stopped, the size of a gap between the tip ...
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WO/2020/128222A1 |
A turbine ring assembly comprising ring sectors (10a, 10b) forming a turbine ring (1) and a ring support structure (3), each sector (10a, 10b) having, on a plane of section defined by an axial direction (DA) and a radial direction (DR) o...
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WO/2020/128397A1 |
The invention relates to a preform (30) with a fibrous reinforcement woven in one piece by three-dimensional weaving to create a fan inter-blade platform which comprises an aerodynamic base (2) and a fixing structure (4) comprising stiff...
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WO/2020/132689A1 |
There is disclosed a labyrinth seal arrangement for gas turboexpanders and the like which reduces process gas losses. The labyrinth seal includes a plurality of axially spaced seal sets with teeth facing a seal member. A plurality of ven...
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WO/2020/119966A1 |
The invention relates to a seal arrangement (01) for sealing a gap between two housing parts (11, 21), the gap being situated between opposite end faces (13, 23) of the housing parts (11, 21). In the first housing part (11), there is a f...
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