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公开(公告)号：US20230340926A1
公开(公告)日：2023-10-26
申请号：US18030151
申请日：2021-10-04
Applicant: SAFRAN CERAMICS
Inventor： Thierry Guy Xavier TESSON , Christophe Jean François THOREL , Christophe Paul AUPETIT , Thierry Jacques Albert LE DOCTE , Philippe AVENEL
CPC classification number: F02K1/04 , F01D25/30 , F02K1/805 , F02K1/827 , F05D2260/96 , F05D2240/55
Abstract: The present invention relates to an assembly for a turbomachine turbine extending along an axis (X), comprising: —an ejection cone (100) comprising a radially outer annular wall (102) defining a flow duct for a flow of hot gases and a sound box radially arranged inside the outer annular wall (102), the sound box comprising a radially inner annular wall (104), —a connecting member (106) intended to be axially inserted between the exhaust housing and the ejection cone (100), the connecting member (106) comprising an upstream annular flange (108) intended to be attached to the exhaust housing and a plurality of downstream securing tabs (110) connected to the inner annular wall (104), —an annular sealing shroud (112) comprising an upstream portion surrounding the securing tabs (110) of the connecting member (106) so as to cover the spaces circumferentially located between the securing tabs (110) and axially located between the upstream annular flange (108) of the connecting member (106) and the radially inner annular wall (104).
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公开(公告)号：US20180073398A1
公开(公告)日：2018-03-15
申请号：US15558856
申请日：2016-03-15
Applicant: SAFRAN AIRCRAFT ENGINES , SAFRAN CERAMICS
Inventor： Lucien Henri Jacques QUENNEHEN , Gaël Frédéric Claude Cyrille EVAIN , David Mathieu Paul MARSAL , Thierry Guy Xavier TESSON
Abstract: A turbine ring assembly includes ring sectors made as a single piece of ceramic matrix composite material and being for mounting on a metal ring support structure, the ring support structure having two tabs extending radially towards a gas flow passage, each ring sector having a first portion forming an annular base with a radially inside face defining the inside face of the turbine ring and an outside face from which there extend two tab-forming portions, the ring sectors having a section that is substantially r shaped. The tabs of each ring sector fit axially over the tabs of the ring support structure with contact between the tabs of the ring support structure and the tabs of each ring sector when cold. The tabs of each ring sector are held to the ring support structure by pegs passing through holes formed in the tabs of each ring sector.
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公开(公告)号：US20220274354A1
公开(公告)日：2022-09-01
申请号：US17625233
申请日：2020-07-01
Applicant: SAFRAN CERAMICS
Inventor： Thierry Guy Xavier TESSON , Marie LEFEBVRE , David Mathieu Paul MARSAL
Abstract: A manufacturing process of a fibrous preform for a composite material includes creating a fibrous texture by three-dimensional or multilayer weaving between a plurality of weft layers and warp layers, the fibrous texture including an extra-thick portion having a sacrificial portion and a useful portion adjacent to the sacrificial portion in the warp direction, the sacrificial portion, placing the fibrous texture in a forming toolset, shaping the fibrous texture so as to obtain a fibrous preform having a sacrificial portion and an adjacent useful portion, removing the sacrificial portion from the fibrous preform. When weaving the fibrous blank, one or more expansion elements are inserted into the weft layers located at the core of the sacrificial portion of the fibrous texture. Each expansion element has a cross-section greater than the cross-section or count of the weft threads or strands present in the useful portion.
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公开(公告)号：US20220235498A1
公开(公告)日：2022-07-28
申请号：US17616604
申请日：2020-06-03
Applicant: SAFRAN CERAMICS
Inventor： Thierry Guy Xavier TESSON , Eric PHILIPPE , Marie LEFEBVRE , Aline PLANCKEEL
Abstract: The invention relates to a three-dimensionally woven multilayer fibrous structure (20) having the same number of warp yarns woven at any level along the warp direction, the fibrous structure (20) comprising, in the warp direction, a first part (22) and a second part (24), the first part (22) having a thickness measured in a direction perpendicular to the warp and weft directions, greater than the second part (24), characterised in that the spacing between two weft planes along the warp direction is greater in the second part than in the first part (22), and in that the number of weft yarns is lower in the second part (24) than in the first part (22).
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公开(公告)号：US20240052863A1
公开(公告)日：2024-02-15
申请号：US18266749
申请日：2021-11-11
Applicant: SAFRAN CERAMICS
Inventor： Gaël BOUCHY , Thomas REVEL , Christophe Paul AUPETIT , Thierry Guy Xavier TESSON
Abstract: An assembly for a turbine engine includes at least a first part and a second part, and at least one bolt including a screw engaging with a nut. The screw extends through respective openings in the first part and in the second part. A bearing element of the bolt has an annular flange mounted between the screw or the nut and the first part. The flange has a bearing surface bearing that is tapered and forms an angle (α) with an additional bearing surface of the first part such that only an outer peripheral area of the flange bearing surface comes into contact with the additional bearing surface of the first part, in a non-tightened state of the bolt, the flange deformable such that when the nut is tightened on the screw, a larger area of the flange bearing surface bears on the additional bearing surface of the first part.
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Patent Agency Ranking
公开(公告)号：US20220154591A1
公开(公告)日：2022-05-19
申请号：US17435685
申请日：2020-02-26
Applicant: SAFRAN CERAMICS
Inventor： Christophe Paul AUPETIT , Thierry Guy Xavier TESSON , Clément Marie Benoit ROUSSILLE , Cécile MarieEmilienne CHEVALIER
Abstract: The invention concerns an assembly for a turbomachine turbine, comprising a housing (1) extending circumferentially about an axis X, sectors (2) intended to form a ring capable of delimiting a gas flow path, each sector (2) comprising a first side (17) and a second side (18) extending radially and circumferentially about the said axis X and spaced axially from each other, each side (17, 18) of the sector (2) comprising at least one radial bearing surface capable of cooperating with radial bearing means (13, 14) of the housing (1), at least one of the sides (17, 18) comprising means (23) for the circumferential positioning of the sector (2) with respect to the housing (1), characterised in that each radial bearing surface is cylindrical of axis X and is capable of bearing on a complementary cylindrical surface of axis X, integral with the housing (1).
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公开(公告)号：US20200255344A1
公开(公告)日：2020-08-13
申请号：US16649329
申请日：2018-09-13
Applicant: Safran Ceramics
Inventor： Maxime François Roger CARLIN , Nicolas EBERLING-FUX , Eddy GOULLIANNE , Thierry Guy Xavier TESSON
IPC: C04B35/80 , C04B35/628 , C04B41/00 , F01D5/28 , F23R3/00
Abstract: Method for manufacturing a CMC, i.e. ceramic matrix composite material, part provided with at least one cutout, as well as to such a CMC part provided with at least one cutout, the method comprising the following steps: providing (E1) a fibrous reinforcement (10), forming (E2′) a cavity in a portion of the fibrous reinforcement (10), injecting (E3) a slip comprising at least a ceramic powder and a solvent, the slip being injected so as to impregnate the fibrous reinforcement (10′) and to fill the cavity of the fibrous reinforcement (10′), drying (E4) the obtained assembly, carrying out a densification (E6) by infiltration of a liquid densification material and solidification of said densification material, machining (E7) at least one cutout in the obtained blank (30) within the volume corresponding to the cavity of the fibrous reinforcement (10).
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公开(公告)号：US20240052759A1
公开(公告)日：2024-02-15
申请号：US18266761
申请日：2021-11-25
Applicant: SAFRAN CERAMICS
Inventor： Thierry Guy Xavier TESSON , Thomas REVEL , Christophe Paul AUPETIT , Denis Jean Armel BUSQUET
CPC classification number: F01D25/243 , F01D25/28 , F05D2300/6033 , F05D2260/31
Abstract: An assembly for a turbomachine includes at least a first part and a second part, and at least one bolt including a screw engaging with a nut. The screw extends through respective openings in the first part and in the second part. The bolt includes a support member having an annular collar mounted between the screw or the nut, and the first part. The collar has a support surface abutting, at least partially, on a complementary support surface of the first part. The collar also includes a recessed annular groove extending at the inner periphery of the collar.
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公开(公告)号：US20230399268A1
公开(公告)日：2023-12-14
申请号：US17799739
申请日：2021-02-10
Applicant: SAFRAN CERAMICS
Inventor： Stéphane Roger André GOUJARD , Adrien DELCAMP , Cédric DESCAMPS , Thierry Guy Xavier TESSON , Charles LELEU
CPC classification number: C04B41/457 , C04B41/4529 , B28B11/08 , C04B2235/614
Abstract: A method of consolidation includes placing a fibrous preform in the shaping recess of a shaping tool, and supplying the shaping tool with a gas phase to obtain a deposit in the fibrous preform, the shaping tool for the vapor phase chemical infiltration including first and second portions, having respectively first and second shaping zones surrounded by a first and second edge zones, the first and the second shaping zone defining a shaping recess to receive the fibrous preform. A gas injection port is present at least partially in the first or second edge zone and a gas outlet port is present at least partially in the first or second edge zone, the gas injection port and the gas outlet port placing the shaping recess in fluid communication with the outside of the shaping tool. Outer faces of the first and second portion are impermeable to gas.
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公开(公告)号：US20200370170A1
公开(公告)日：2020-11-26
申请号：US16491766
申请日：2018-03-05
Applicant: SAFRAN CERAMICS , SAFRAN
Inventor： Thierry Guy Xavier TESSON , Maxime François Roger CARLIN , Simon THIBAUD , Rémy DUPONT , Ramzi BOHLI
IPC: C23C16/02 , B28B1/52 , C23C16/04 , C04B35/565 , C04B35/584 , C04B35/80 , C04B35/628 , C04B35/52 , C04B35/583
Abstract: A method for producing a consolidated fiber preform intended for the manufacture of a part made of composite material, includes shaping a fiber texture in a heated metal mold, the texture being pre-impregnated with a transient or fugitive material, or shaping a fiber texture in a metal mold and injecting a transient or fugitive material into the fiber texture held in shape in the metal mold, cooling the mold, removing the set fiber preform from the mold, coating the fiber preform with a slurry containing a powder of ceramic or carbon particles, heat-treating the coated fiber preform so as to form a porous shell around the fiber preform by consolidation of the slurry and so as to remove the transient or fugitive material present in the fiber preform, consolidating the fiber preform by gas-phase chemical infiltration.
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