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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：US09752506B2
公开(公告)日：2017-09-05
申请号：US14503721
申请日：2014-10-01
Applicant: SNECMA
Inventor： Eric Schwartz , Fabien Garnier , Helene Condat , Renaud Gabriel Constant Royan , Patrick Joseph Marie Girard
CPC classification number: F02C7/20 , F01D9/02 , F01D25/08 , F01D25/243 , F01D25/246 , F05D2220/32 , F05D2240/15 , F05D2240/91 , F05D2260/30 , Y02T50/675
Abstract: A device for connecting a fixed turbine engine portion and a distributor foot of a turbine engine turbine is provided. The device includes a ring-shaped body adapted so as to be connected and secured to the fixed turbine engine portion, and two ring-shaped upstream and downstream brackets secured to the body, both brackets being adapted so as to clamp the foot of the distributor. At least one bracket is interrupted by forming an expansion or retraction slot, the slot allowing an expansion of the bracket tending to close the slot or retraction of the bracket tending to further open the slot, under the effect of a difference in internal temperatures of the device.
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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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