公开(公告)号：US11753947B2

公开(公告)日：2023-09-12

申请号：US16649329

申请日：2018-09-13

申请人： Safran Ceramics

发明人： Maxime François Roger Carlin ,  Nicolas Eberling-Fux ,  Eddy Goullianne ,  Thierry Guy Xavier Tesson

IPC分类号： C04B35/80 ,  F01D5/28 ,  C04B35/628 ,  C04B41/00 ,  F23R3/00 ,  C04B35/56 ,  C04B35/563 ,  C04B35/573 ,  C04B35/58 ,  C04B35/583 ,  C04B35/584

CPC分类号： F01D5/282 ,  C04B35/563 ,  C04B35/5611 ,  C04B35/5622 ,  C04B35/573 ,  C04B35/583 ,  C04B35/584 ,  C04B35/58092 ,  C04B35/62844 ,  C04B35/80 ,  C04B41/009 ,  F01D5/284 ,  F23R3/002 ,  C04B2235/5256 ,  C04B2235/606 ,  C04B2235/612 ,  C04B2235/616

摘要： 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).

公开(公告)号：US11332411B2

公开(公告)日：2022-05-17

申请号：US16491766

申请日：2018-03-05

申请人： SAFRAN CERAMICS ,  SAFRAN

发明人： Thierry Guy Xavier Tesson ,  Maxime François Roger Carlin ,  Simon Thibaud ,  Rémy Dupont ,  Ramzi Bohli

IPC分类号： C04B35/80 ,  C23C16/04 ,  B28B1/52 ,  C04B35/52 ,  C04B35/565 ,  C04B35/583 ,  C04B35/584 ,  C04B35/628 ,  C23C16/02 ,  C04B35/14 ,  C04B35/18 ,  C04B35/573

摘要： 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.

公开(公告)号：US12065985B2

公开(公告)日：2024-08-20

申请号：US18030151

申请日：2021-10-04

申请人： SAFRAN CERAMICS

发明人： Thierry Guy Xavier Tesson ,  Christophe Jean François Thorel ,  Christophe Paul Aupetit ,  Thierry Jacques Albert Le Docte ,  Philippe Avenel

IPC分类号： F01D25/30 ,  F02K1/04 ,  F02K1/80 ,  F02K1/82

CPC分类号： F02K1/04 ,  F01D25/30 ,  F02K1/805 ,  F02K1/827 ,  F05D2240/55 ,  F05D2260/96

摘要： 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).

公开(公告)号：US11738521B2

公开(公告)日：2023-08-29

申请号：US17625233

申请日：2020-07-01

申请人： SAFRAN CERAMICS

发明人： Thierry Guy Xavier Tesson ,  Marie Lefebvre ,  David Mathieu Paul Marsal

IPC分类号： B29C70/48 ,  B29C70/10 ,  B29C70/24 ,  B29B11/12 ,  B29B11/16 ,  B29K105/08 ,  B29L31/08

CPC分类号： B29C70/24 ,  B29B11/12 ,  B29B11/16 ,  B29C70/48 ,  B29K2105/089 ,  B29L2031/082

摘要： 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.

公开(公告)号：US11591924B2

公开(公告)日：2023-02-28

申请号：US17435685

申请日：2020-02-26

申请人： SAFRAN CERAMICS

发明人： Christophe Paul Aupetit ,  Thierry Guy Xavier Tesson ,  Clément Marie Benoît Roussille ,  Cécile Marie Emilienne Chevalier

IPC分类号： F01D11/08 ,  F01D11/12 ,  F01D25/24

摘要： An assembly for a turbomachine turbine includes 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) including at least one radial bearing surface of an oblong hole capable of cooperating with support pins (13, 14) of the housing (1), at least one of the sides (17, 18) including means (23) for the circumferential positioning of the sector (2) with respect to the housing (1), wherein each radial bearing surface is cylindrical relative to axis X and is capable of bearing on a complementary cylindrical surface relative to axis X of a support pin.

公开(公告)号：US10590803B2

公开(公告)日：2020-03-17

申请号：US15558856

申请日：2016-03-15

申请人： SAFRAN AIRCRAFT ENGINES ,  SAFRAN CERAMICS

发明人： Lucien Henri Jacques Quennehen ,  Gaël Frédéric Claude Cyrille Evain ,  David Mathieu Paul Marsal ,  Thierry Guy Xavier Tesson

IPC分类号： F01D25/28 ,  F01D25/24 ,  F01D11/12 ,  F01D9/04 ,  F01D11/02 ,  F01D11/18

摘要： 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 π 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.