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公开(公告)号：US20230126667A1
公开(公告)日：2023-04-27
申请号：US17914676
申请日：2021-03-22
Applicant: SAFRAN CERAMICS
Inventor： Matthieu Arnaud GIMAT , Eric BOUILLON , Maxime François Roger CARLIN
Abstract: A turbine stator blade made of ceramic matrix composite material includes a hollow blade profile and has a trailing edge and a leading edge, the blade including a first portion including an extrados face and a second portion distinct from the first portion including an intrados face, the first and second portions being connected to one another by a connection interface present at least on the trailing edge or leading edge, the connecting interface including a region of overlap between the first and second portions present on at least one longitudinal end of the blade profile and intended to be present outside a flow path of a gas stream of the turbine, the blade also including a platform present at a longitudinal end of the blade profile and that includes a first portion integral with the extrados face and a second part integral with the intrados face.
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2.发明公开公开(公告)号：US20240263560A1
公开(公告)日：2024-08-08
申请号：US18699150
申请日：2022-09-30
Applicant: SAFRAN AIRCRAFT ENGINES , SAFRAN CERAMICS
Inventor： Patrick Joseph Marie GIRARD , Didier René André ESCURE , Matthieu Arnaud GIMAT , Sébastien Serge Francis CONGRATEL , Arthur DE CASTRO
CPC classification number: F01D5/3084 , F01D5/141 , F01D9/041 , F05D2300/6033
Abstract: Blade of a turbomachine turbine including a airfoil extending along a first direction between an internal end and an external end, a base secured to said internal end, and a root secured to said external end and extending, along a second direction perpendicular to said first direction, between an upstream edge, and a downstream edge and, along a third direction orthogonal to the first and second directions, between first and second lateral edges, the first side edge having, in a plane including the second and third directions, a shape complementary to that of the second lateral edge. The first lateral edge includes a first portion extending from the upstream edge, and a second portion externally protruding along the third direction at an acute angle with the first portion.
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公开(公告)号：US20240133306A1
公开(公告)日：2024-04-25
申请号：US18546169
申请日：2022-02-08
Applicant: SAFRAN AIRCRAFT ENGINES , SAFRAN CERAMICS
Inventor： Sébastien Serge Francis CONGRATEL , Aurélien GAILLARD , Matthieu Arnaud GIMAT , Clément JARROSSAY , David René Pierre LE CAIR
IPC: F01D9/04
CPC classification number: F01D9/042 , F01D9/041 , F05D2250/71 , F05D2260/38 , F05D2300/6033
Abstract: A turbine engine nozzle extending about an axis and including a vane assembly mounted between an outer shroud and an inner shroud; and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress on the vane assembly towards the outer shroud. The contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device.
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公开(公告)号：US20230340883A1
公开(公告)日：2023-10-26
申请号：US18254071
申请日：2021-11-08
Applicant: SAFRAN CERAMICS
IPC: F01D5/28 , D03D25/00 , D03D1/00 , D03D15/242 , D03D15/275 , C04B35/80 , F01D5/18
CPC classification number: F01D5/282 , D03D25/005 , D03D1/00 , D03D15/242 , D03D15/275 , C04B35/80 , F01D5/18 , D10B2505/02 , D10B2101/16 , C04B2235/5256 , F05D2300/6033 , F05D2230/50 , F05D2260/20
Abstract: A woven fibrous preform of a hollow aerodynamic profile of a turbomachine vane or blade, has a non-interlinked trailing edge and a draping of two 3D woven fibrous textures.
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Patent Agency Ranking
公开(公告)号：US20230323776A1
公开(公告)日：2023-10-12
申请号：US18043484
申请日：2021-08-26
Applicant: SAFRAN AIRCRAFT ENGINES , SAFRAN CERAMICS
Inventor： Lucien Henri Jacques QUENNEHEN , Sébastien Serge Francis CONGRATEL , Matthieu Arnaud GIMAT
CPC classification number: F01D5/282 , F01D9/04 , C04B37/003 , F05D2300/603 , F05D2230/237 , C04B2237/38 , C04B2237/60 , C04B2237/64
Abstract: A turbomachine part of an annular assembly includes a structural body and a connecting edge integral with the structural body. Each connecting edge includes at least one groove intended to receive a sealing tab. Each connecting edge is made of composite material including a fibrous reinforcement consisting of randomly-oriented short fibres, the reinforcement being densified by a ceramic matrix.
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公开(公告)号：US20240229662A9
公开(公告)日：2024-07-11
申请号：US18546169
申请日：2022-02-08
Applicant: SAFRAN AIRCRAFT ENGINES , SAFRAN CERAMICS
Inventor： Sébastien Serge Francis CONGRATEL , Aurélien GAILLARD , Matthieu Arnaud GIMAT , Clément JARROSSAY , David René Pierre LE CAIR
IPC: F01D9/04
CPC classification number: F01D9/042 , F01D9/041 , F05D2250/71 , F05D2260/38 , F05D2300/6033
Abstract: A turbine engine nozzle extending about an axis and including a vane assembly mounted between an outer shroud and an inner shroud; and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress on the vane assembly towards the outer shroud. The contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device.
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公开(公告)号：US20230191746A1
公开(公告)日：2023-06-22
申请号：US18012149
申请日：2021-06-23
Applicant: SAFRAN CERAMICS
CPC classification number: B32B7/04 , B32B3/06 , B32B5/024 , B32B37/0038
Abstract: A method for manufacturing a turbine nozzle vane made of ceramic matrix composite material, wherein the vane is manufactured using a first fibrous preform including a hollow central section intended to form a fibrous reinforcement of an airfoil of the vane to be obtained, and a pair of second fibrous preforms each having an opening with a shape of the airfoil of the vane to be obtained.
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8.发明公开公开(公告)号：US20230313695A1
公开(公告)日：2023-10-05
申请号：US17766711
申请日：2020-10-01
Applicant: SAFRAN AIRCRAFT ENGINES , SAFRAN CERAMICS
Inventor： Clément JARROSSAY , Sébastien Serge Francis CONGRATEL , Aurélien GAILLARD , David René Pierre LE CAIR , Matthieu Arnaud GIMAT
CPC classification number: F01D9/042 , F01D9/041 , F01D9/065 , F01D11/003 , F05D2240/128 , F05D2240/55 , F05D2300/6033 , F05D2300/614
Abstract: A nozzle for a turbomachine turbine. The nozzle includes blades made of ceramic matrix composite material, and at least one metal liner passing through a respective blade. The liner is connected in a sealed manner to a metal internal shroud so as to guide a ventilation fluid through the blade. The nozzle can be configured to maintain effective sealing in spite of the different thermal expansions of the blade and of the internal shroud.
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公开(公告)号：US20230212952A1
公开(公告)日：2023-07-06
申请号：US17997628
申请日：2021-04-28
Applicant: SAFRAN AIRCRAFT ENGINES , SAFRAN CERAMICS
Inventor： Antoine Claude Michel Etienne DANIS , Clément JARROSSAY , Lucien Henri Jacques QUENNEHEN , Nicolas Paul TABLEAU , Matthieu Arnaud GIMAT
CPC classification number: F01D9/06 , F01D5/284 , F01D25/12 , F05D2220/32 , F05D2220/323 , F05D2240/128 , F05D2260/202 , F05D2300/20
Abstract: A turbomachine turbine nozzle extending around a central axis, including at least one radially outer shroud, at least one radially inner shroud, and at least one blade made of ceramic matrix composite material, distinct from the radially inner shroud and from the radially outer shroud, and extending radially between the radially inner shroud and the radially outer shroud, the blade being hollow and including a cavity opening at a radially inner end and at a radially outer end of the blade, the nozzle including at least one tubular mast arranged in the cavity of the blade and allowing routing the ventilation air passing through the cavity of the blade, the mast including a radially outer end attached to the radially outer shroud, and a radially inner end cooperating with a radial flange for positioning the radially inner shroud.
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