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公开(公告)号：US20200040735A1
公开(公告)日：2020-02-06
申请号：US16339801
申请日：2017-10-06
发明人： Vincent Francois Georges MILLIER , Francois Pierre Michel COMTE , Fabien Stephane GARNIER , Alain Dominique GENDRAUD , Arnaud Lasantha GENILIER
摘要： A movable ring assembly (4) for a turbine engine turbine (10) that is mounted between two successive rotor discs (20a) and (20b) of said turbine (10), said rotor discs (20a) and (20b) being fixed to each other by bolting, characterised in that it comprises:—a fixing ferrule (44) fixed between the upstream (20a) and downstream (20b) discs by the bolting thereof; a part forming a movable ring (42), said part supporting radial sealing members (32) and being fixed between the upstream disc (20a) and the ferrule (44);—and a seal (46) interposed between said part forming the movable ring (42) and the ferrule (44).
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公开(公告)号：US20220213810A1
公开(公告)日：2022-07-07
申请号：US17613451
申请日：2020-05-19
发明人： Rémy Miled Michel HAYNAU , Arnaud Lasantha GENILIER , Nicolas CONTINI , Maria GOOSSENS , Benoit Guillaume SILET
摘要： A turbine for a turbomachine comprising an annular row (20) of moving blades (20a) surrounded by a support ring (26) of abradable material (24) carried by a housing (10) and a distributor (30) mounted downstream of said annular row (20) of moving blades (20a) and comprising a means of attachment to a means of support of the housing (10), the said means of attachment comprising a radially outer spoiler (38) coming to bear radially inwards on a cylindrical wall (12) of said means of support, the said means of support further comprising an annular wall (14) extending radially inwards from the cylindrical wall (12) and engaged at its radially inner end in an annular groove (28) of the ring (26), and in which a free annular space (40) is formed between a radially outer face (26b) of the ring (26) and the cylindrical wall (12) of the means of support.
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3.发明申请公开(公告)号：US20210355830A1
公开(公告)日：2021-11-18
申请号：US17266653
申请日：2019-08-26
摘要： A rotor disc for a turbomachine, the disc extending circumferentially about an axis and including a plurality of cavities configured to receive blade roots, each cavity including a downstream radial wall configured to axially block the blade root in the cavity, each downstream radial wall including a channel of ventilation of the cavity, including an inlet orifice which opens into the cavity and an outlet orifice which opens onto a downstream surface of the disc. An assembly for a turbomachine including such a disc and an upstream retention ring and a turbomachine including such an assembly.
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公开(公告)号：US20190331001A1
公开(公告)日：2019-10-31
申请号：US16395823
申请日：2019-04-26
发明人： Fabien Stéphane GARNIER , François Pierre Michel COMTE , Arnaud Lasantha GENILIER , Vincent François Georges MILLIER
摘要： The invention relates to a lubrication device (1) for a turbo machine, comprising: a rotor (2) rotating around an axis, at least one lubrication chamber (6) formed in the rotor (2), a stator (22) in which the rotor (2) is rotatably mounted, a bearing (11) for rotationally guiding the rotor (2), mounted between the rotor (2) and the stator, lubricating fluid supply means which supply at least the chamber (6) and the bearing (11), the lubricating fluid supply means comprising a nozzle (23) mounted on the stator provided with an ejection nozzle (34) at a free end of the nozzle (23), said nozzle (34) being configured to project the lubricating fluid into the chamber (6), characterized in that the nozzle (23) has a movable part (27) including said ejection nozzle (34), said movable part (27) being movable between a retracted position in which the ejection nozzle (34) is remote from the chamber (6) or at least partially located outside the chamber (6), and an extended position in which the nozzle (34) is closer to the chamber (6) or at least partially located in the chamber (6).
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公开(公告)号：US20230383656A1
公开(公告)日：2023-11-30
申请号：US18247282
申请日：2021-10-01
发明人： Jean Charles Marie COUSSIROU , Nour CHERKAOUI , Arnaud Lasantha GENILIER , Rémi Philippe Oswald OLIVE
CPC分类号： F01D5/14 , F01D11/08 , F05D2240/55 , F05D2230/00
摘要： A turbine blade for a turbine engine, including an aerofoil and a platform. The platform includes an internal channel having a suction opening which opens on a first surface of an upstream portion of the platform, this first surface defining a primary duct. The internal channel includes an ejection opening which opens on a second surface of a downstream portion of the platform, this second surface defining a purge cavity. The internal channel makes it possible to suck in a part of a fluid circulating in the primary duct so as to reduce the intensity of secondary flows which result from friction of the fluid on the first surface.
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公开(公告)号：US20220235672A1
公开(公告)日：2022-07-28
申请号：US17597065
申请日：2020-06-16
发明人： Nicolas OVAERE , Fabien Stéphane GARNIER , Arnaud Lasantha GENILIER , Pierre Jean-Baptiste METGE
摘要： Turbomachine output bearing support extending according to an axial direction, said support being formed by one and the same piece and comprising an annular inner wall having an inner side and an outer side, an annular outer wall and a twist support.
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公开(公告)号：US20200332680A1
公开(公告)日：2020-10-22
申请号：US16849802
申请日：2020-04-15
摘要： A turbomachine exhaust casing extending about an axis including a hub extending about the axis; an external ferrule; arms which extend between the hub and the external ferrule, attachment yokes radially projecting toward the outside of the external ferrule; pockets hollowed into the external ferrule and wherein the yokes are arranged, the pockets extending in a hollow radially projecting toward the inside of the external ferrule; a ring portion which extends radially under the pockets and forms a duct wall by delimiting with the hub a portion of a gas flow duct.
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公开(公告)号：US20200182089A1
公开(公告)日：2020-06-11
申请号：US16623086
申请日：2018-06-04
发明人： Arnaud Lasantha GENILIER , François Pierre Michel COMTE , Fabien Stéphane GARNIER , Vincent François Georges MILLIER
摘要： The invention relates to a device (26) for cooling an annular outer turbine casing (17), the device (26) comprising at least one circumferentially extending tube (27) having an air inlet intended for conveying cooling air, said tube (27) having a radially inner wall provided with cooling air discharge openings and a radially outer wall arranged axially opposite each other, an air inlet manifold (28), the inlet of the tube (27) opening into said manifold (28), characterized in that the tube (27) comprises at least one intermediate wall extending over a circumferential portion of the tube (27) from the air inlet, the intermediate wall being located radially between the radially inner wall and the radially outer wall, the radially inner wall and the intermediate wall forming a first air conveying duct, the radially outer wall and the intermediate wall forming a second air conveying duct extending circumferentially beyond the first air conveying duct, relative to the air inlet.
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