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公开(公告)号：US09631495B2
公开(公告)日：2017-04-25
申请号：US14349484
申请日：2012-10-10
Applicant: SNECMA
Inventor： Emmanuel Da Costa , Alain Dominique Gendraud , Renaud Martet , Josselin Sicard , Bruno Andre Jean Varin
CPC classification number: F01D5/081 , Y02E10/721 , Y02T50/673 , Y02T50/676
Abstract: A turbomachine assembly in which a foil is configured to cover mainly one of bulbs of a disc and to be held, radially with respect to the disc, by the bulb of the disc and a pocket for a blade that can collaborate therewith, when these two are effectively collaborating, and the bulb of the disc includes at least one longitudinal cavity configured to form, with the foil, when the foil is covering the bulb of the disc, a secondary passage through which a secondary cooling air flow can pass.
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公开(公告)号：US20140105732A1
公开(公告)日：2014-04-17
申请号：US14134405
申请日：2013-12-19
Applicant: SNECMA
Inventor： Florent Pierre Antoine LUNEAU , Alain Dominique Gendraud , Patrick Joseph Marie Girard , Sebastien Jean Laurent Prestel
IPC: F01D11/12
CPC classification number: F01D11/122 , F01D11/001 , F05D2250/283
Abstract: A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal.
Abstract translation: 一种用于燃气涡轮发动机的涡轮机，包括至少一个涡轮机定子和一个涡轮机转子，所述涡轮机定子包括至少一个内部环形平台，所述内部平台包括限定所述涡轮机定子和所述涡轮机转子之间的至少一个空腔的径向壁， 其中所述涡轮转子包括至少一个细长元件，所述至少一个细长元件基本上轴向地定位并且在所述空腔中限定密封挡板，并且所述涡轮机定子包括由可磨损材料制成的至少一个元件，所述可磨损材料设计成与所述涡轮转子的所述细长元件接合， 形成迷宫密封。
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公开(公告)号：US20150118035A1
公开(公告)日：2015-04-30
申请号：US14394355
申请日：2013-04-17
Applicant: SNECMA
Inventor： Alain Dominique Gendraud , Alberto Martin-Matos , Vincent Millier , Sebastien Jean Laurent Prestel
CPC classification number: F01D25/246 , F01D9/04 , F01D9/041 , F01D9/042 , F01D11/005 , F05D2230/60 , F05D2240/10 , F05D2240/128 , F05D2240/91
Abstract: A turbine stage for a turbine engine, the stage including a nozzle and a wheel mounted inside a sectorized ring carried by a casing. The nozzle is attached to the casing and is retained axially downstream by bearing against an annular split ring. Each ring sector includes at its upstream end a member of C-shaped section that is engaged on the casing rail and that holds the split ring radially. A radially inner wall of the C-shaped member of each ring sector extends inside the split ring over an entire axial dimension thereof and its upstream end portion is engaged in at least one recess of the nozzle.
Abstract translation: 一种用于涡轮发动机的涡轮级，该级包括一个喷嘴和一个安装在由壳体承载的扇形环内的轮。 喷嘴连接到壳体并且通过承受环形裂环而轴向保持在下游。 每个环形扇区在其上游端包括C形截面的构件，其接合在壳体轨道上并且径向保持开口环。 每个环形扇形体的C形构件的径向内壁在整个轴向尺寸上在开口环的内部延伸，并且其上游端部接合在喷嘴的至少一个凹部中。
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Patent Agency Ranking
公开(公告)号：US20140308133A1
公开(公告)日：2014-10-16
申请号：US14357113
申请日：2012-11-12
Applicant: SNECMA
IPC: F01D11/00
CPC classification number: F01D11/006 , F01D5/3007 , F01D5/3015 , F01D5/326 , F01D11/001 , F05D2240/55 , F05D2250/231 , F05D2250/232 , F05D2260/30 , Y02T50/672
Abstract: A rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades.
Abstract translation: 用于诸如飞机涡轮螺旋桨或涡轮喷气发动机的涡轮发动机的转子轮，转子轮包括转子盘，转子盘在其外周边包括齿，其限定用于轴向安装并径向保持叶片根部的槽。 环形唇缘包括从径向保持机构的轴向下游并径向向内延伸的环形边缘，该径向保持机构形成为从盘的上游面轴向突出，并且密封机构径向设置在环形唇缘的径向内部和平台的上游端 刀片。
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公开(公告)号：US20140294597A1
公开(公告)日：2014-10-02
申请号：US14349484
申请日：2012-10-10
Applicant: SNECMA
Inventor： Emmanuel Da Costa , Alain Dominique Gendraud , Renaud Martet , Josselin Sicard , Bruno Andre, Jean Varin
IPC: F01D5/08
CPC classification number: F01D5/081 , Y02E10/721 , Y02T50/673 , Y02T50/676
Abstract: A turbomachine assembly in which a foil is configured to cover mainly one of bulbs of a disc and to be held, radially with respect to the disc, by the bulb of the disc and a pocket for a blade that can collaborate therewith, when these two are effectively collaborating, and the bulb of the disc includes at least one longitudinal cavity configured to form, with the foil, when the foil is covering the bulb of the disc, a secondary passage through which a secondary cooling air flow can pass.
Abstract translation: 一种涡轮机组件，其中箔被构造成主要覆盖盘的一个灯泡并且相对于盘径向地由盘的灯泡和用于与其协作的刀片的口袋保持，当这两个 并且所述盘的灯泡包括至少一个纵向空腔，所述至少一个纵向腔被配置为当所述箔覆盖所述盘的灯泡时形成所述箔，所述次级通道可以通过所述第二冷却空气流。
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公开(公告)号：US09726033B2
公开(公告)日：2017-08-08
申请号：US14357113
申请日：2012-11-12
Applicant: SNECMA
CPC classification number: F01D11/006 , F01D5/3007 , F01D5/3015 , F01D5/326 , F01D11/001 , F05D2240/55 , F05D2250/231 , F05D2250/232 , F05D2260/30 , Y02T50/672
Abstract: A rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades.
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公开(公告)号：US09683452B2
公开(公告)日：2017-06-20
申请号：US14134405
申请日：2013-12-19
Applicant: SNECMA
Inventor： Florent Pierre Antoine Luneau , Alain Dominique Gendraud , Patrick Joseph Marie Girard , Sebastien Jean Laurent Prestel
CPC classification number: F01D11/122 , F01D11/001 , F05D2250/283
Abstract: A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal.
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公开(公告)号：US09957841B2
公开(公告)日：2018-05-01
申请号：US14394355
申请日：2013-04-17
Applicant: SNECMA
Inventor： Alain Dominique Gendraud , Alberto Martin-Matos , Vincent Millier , Sebastien Jean Laurent Prestel
CPC classification number: F01D25/246 , F01D9/04 , F01D9/041 , F01D9/042 , F01D11/005 , F05D2230/60 , F05D2240/10 , F05D2240/128 , F05D2240/91
Abstract: A turbine stage for a turbine engine, the stage including a nozzle and a wheel mounted inside a sectorized ring carried by a casing. The nozzle is attached to the casing and is retained axially downstream by bearing against an annular split ring. Each ring sector includes at its upstream end a member of C-shaped section that is engaged on the casing rail and that holds the split ring radially. A radially inner wall of the C-shaped member of each ring sector extends inside the split ring over an entire axial dimension thereof and its upstream end portion is engaged in at least one recess of the nozzle.
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