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公开(公告)号：US20170167264A1
公开(公告)日：2017-06-15
申请号：US15312850
申请日：2015-05-07
发明人： Josselin Luc Florent SICARD , Bertrand PELLATON , Hélène Marie BARRET , Benoit Guillaume SILET , Anne-Flore Karine HOULET
摘要： A turbine rotor for a gas turbine engine, includes an upstream turbine disk; a downstream turbine disk; an annular flange; a first ferrule connecting the upstream turbine disk to the annular flange; a second ferrule connecting the downstream turbine disk to the annular flange; an air flow separator device including: a first part, forming a first ring, arranged between the upstream turbine disk and the downstream turbine disk; a second part, forming a second ring, having a first portion facing the downstream turbine disk, and a second portion arranged between the first ferrule and the second ferrule; and a thermal insulation area arranged between the first part and the second part.
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公开(公告)号：US20210222581A1
公开(公告)日：2021-07-22
申请号：US17059738
申请日：2019-05-28
摘要： The invention relates to a device (21) for cooling an annular casing (18) of a turbomachine, comprising a collector housing (22) intended to extend circumferentially around the axis of the casing (18), at least two cooling tubes (23) extending circumferentially and connected to the internal volume of the housing (22), the housing (22) and/or each tube (23) having ejection openings opening radially towards the casing (18), characterised in that connecting portions of the tubes (23) formed in one piece with the housing (22) extend circumferentially projecting from the housing (22), forming between them at least one recessed area (29) of the housing which allows an air passage radially from the inside to the outside of the housing (22).
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公开(公告)号：US20220341347A1
公开(公告)日：2022-10-27
申请号：US17761337
申请日：2020-09-23
发明人： Nicolas CONTINI , Laurent Claude DESCAMPS , Rémy Miled Michel HAYNAU , Maria GOOSSENS , Benoit Guillaume SILET
摘要： An air-jet cooling device for a casing of a turbomachine, in particular a turbine casing, including a cooling air housing having a wall, and a tube having a first end mounted on the wall of the housing so as to put the tube into fluid communication with the housing, orifices being formed in a wall of the tube in order to eject the cooling air coming from the housing on the casing. The tube has a section at the first end with a gradual variation that defines a boss. The boss has a curved surface to be immersed in the cooling air so as to avoid a detachment of a boundary layer of the cooling air at an interface between the first end of the tube and the housing.
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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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公开(公告)号：US20240117750A1
公开(公告)日：2024-04-11
申请号：US18271893
申请日：2022-01-18
CPC分类号： F01D11/122 , F01D5/20 , F05D2250/11 , F05D2250/12
摘要： A rotor of a turbine extending around a longitudinal axis includes a rotor disc bearing at its periphery one or more rotor blades, each blade including an airfoil provided at its radially outer end with a platform equipped with an upstream lip and a downstream lip, the platform having a front lateral edge and a back lateral edge with respect to the normal direction of rotation of the rotor about the longitudinal axis, and a suction face portion which extends from the front lateral edge to the suction face of the airfoil. The upstream lip and the downstream lip each includes sawtooth-shaped cut-outs such as to form a front tooth and a back tooth which are contiguous, in that the back tooth has a cutting edge and in that the front tooth of each lip is disposed on the suction face portion of the platform.
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6.发明公开公开(公告)号：US20240035391A1
公开(公告)日：2024-02-01
申请号：US18256317
申请日：2021-12-01
CPC分类号： F01D11/122 , F01D5/147 , F01D11/10 , B33Y80/00
摘要： A blade and a sealing element forming an assembly for a turbomachine turbine. The blade includes an airfoil and a platform to which the sealing element is connected. An internal channel passes through the platform so as to draw off fluid circulating in a primary duct that it delimits and to inject the thus drawn-off fluid into an inter-lip cavity delimited by the sealing element.
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公开(公告)号：US20230160319A1
公开(公告)日：2023-05-25
申请号：US17919184
申请日：2021-04-13
发明人： Benoit Guillaume SILET , Stéphane Pierre Fuillaume BLANCHARD , Fabien Stéphane GARNIER , Thibaud Louis ZAIA
CPC分类号： F01D25/14 , F01D25/12 , F05D2260/60
摘要： A turbomachine turbine casing that extend around an axis and includes an annular wall and a cooling device. The annular wall is provided with a casing hook which extends in radial protrusion from an inside of the annular wall. The casing hook allows a mounting, on the turbomachine turbine casing, of ring segments disposed circumferentially end to end around the axis. The cooling device includes a collector duct intended to convey cooling air, the collector duct extending circumferentially around the annular wall. The collector duct has a cooling air inlet and a cooling air outlet. The collector duct and the annular wall have a common portion, which delimits the collector duct and from which the corresponding casing hook extends.
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