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公开(公告)号：US20230407814A1
公开(公告)日：2023-12-21
申请号：US18251965
申请日：2021-11-04
Applicant: SAFRAN CERAMICS
Inventor： Thomas VANDELLOS , Benoit CARRERE , Eric CONETE , Jean-Philippe JORET , Vincent DEVANLAY , Clément Marie Benoît ROUSSILLE
Abstract: An assembly for a turbomachine with a longitudinal axis having an exhaust cone with an outer annular wall for the flow of a primary airflow and an annular box arranged radially inside the outer annular wall, an exhaust casing arranged upstream of and connected to the exhaust cone. One end of the outer annular wall or one end of the annular box may be free to move relative to and have no mechanical connection with the exhaust cone or the exhaust casing.
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公开(公告)号：US20230407816A1
公开(公告)日：2023-12-21
申请号：US18250964
申请日：2021-10-29
Applicant: SAFRAN CERAMICS
Inventor： Eric CONETE , Benoit CARRERE , Thomas VANDELLOS
IPC: F02K1/80
CPC classification number: F02K1/80
Abstract: A turbomachine turbine assembly having a longitudinal axis and including an exhaust casing, an ejection cone arranged downstream of the exhaust casing, the ejection cone having an outer annular wall for the flow of a primary air stream and an acoustic box arranged radially inside said outer annular wall. The acoustic box can include a radially inner annular wall and a connection member interposed longitudinally between the exhaust casing and the inner annular wall of the ejection cone. The connection member can be fastened to the exhaust casing and to the inner annular wall. The upstream end of the outer annular wall can be connected to the connection member with a degree of freedom in the radial direction and a degree of freedom in the longitudinal direction.
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Patent Agency Ranking
公开(公告)号：US20240417339A1
公开(公告)日：2024-12-19
申请号：US18722026
申请日：2022-12-13
Applicant: SAFRAN CERAMICS , SAFRAN
Inventor： Eric CONETE , Lisa PIN , Ioannis STASINOPOULOS
Abstract: A part includes a substrate made of ceramic matrix composite material, the substrate being coated with a multilayer stack including at least, and in this order, starting from the substrate a tie layer including silicon; an insulation layer including a rare earth disilicate or silica; a barrier layer including a rare earth disilicate; the part further including at least one thermocouple inserted between the insulation layer and the barrier layer.
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4.发明申请公开(公告)号：US20220252022A1
公开(公告)日：2022-08-11
申请号：US17631281
申请日：2020-08-12
Applicant: SAFRAN CERAMICS
Inventor： Eric BOUILLON , Eric CONETE
IPC: F02K1/82
Abstract: An annular or semi-annular acoustic attenuation structure includes an inner skin and an outer skin, defining between them an annular or semi-annular volume, and a plurality of partitions extending in the space in a radial direction perpendicular to the inner and outer skins and in a circumferential direction. The inner and outer skins and the partitions are made of composite material including a fibrous reinforcement densified by a matrix. The fibrous reinforcement of each partition includes yarns or fibers extending into the fibrous reinforcement of at least one of the inner or outer skins.
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公开(公告)号：US20230406780A1
公开(公告)日：2023-12-21
申请号：US18250275
申请日：2021-10-27
Applicant: SAFRAN CERAMICS
Inventor： Eric CONETE
CPC classification number: C04B35/80 , F01D5/282 , C04B2235/5256 , C04B2235/612 , F05D2230/10 , F05D2300/6033
Abstract: Method for manufacturing a turbomachine blade made of ceramic-matrix composite material comprising an airfoil and a platform, producing a first fibrous preform, the first fibrous preform forming an airfoil preform, producing a second fibrous preform comprising a housing, the second fibrous preform forming a platform preform, producing a strand of ceramic fibers, consolidating the fibrous preforms and the strand of ceramic fibers to form consolidated preforms and a consolidated strand, assembling the consolidated preforms by engagement and cooperation of the first consolidated preform in the housing, the consolidated strand being interposed between the first consolidated preform and the second consolidated perform, co-densifying the assembly to form the turbomachine blade.
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公开(公告)号：US20220341373A1
公开(公告)日：2022-10-27
申请号：US17640992
申请日：2020-09-02
Applicant: SAFRAN CERAMICS
Inventor： Eric CONETE , Benoit CARRERE
Abstract: The invention relates to an assembly for an aircraft turbomachine, comprising a central element (1) for the ejection of gas, and a connecting flange (9) interposed between, upstream, a gas outlet (22a) made of metal for a turbomachine, and, at the downstream end, the central element (1). The connecting flange comprises an annular portion (9a) and flexible tabs (11) having axially: a first end (111a) where the tab is connected to the said annular portion, and a second free end (111b), projecting radially inwardly with respect to the first end and to which said tab is attached with the central element (1).
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公开(公告)号：US20240044497A1
公开(公告)日：2024-02-08
申请号：US18546205
申请日：2022-02-14
Applicant: SAFRAN CERAMICS
Inventor： Patrick Olivier DUCHAINE , Amaury Benoit Jacques PAILLARD , Eric CONETE , Benjamin LACOMBE
IPC: F23R3/60
CPC classification number: F23R3/60 , F23R2900/00017
Abstract: A turbomachine subassembly including a first component forming a portion of a wall of a combustion chamber of the turbomachine and a second component forming a connecting member connecting the first component to a structural element of the combustion chamber, wherein the two components are made from materials having different coefficients of expansion, and wherein the two components are elements of revolution coaxial with a main axis A of the subassembly, and each including an annular radial wall, the radial walls facing one another and bearing against one another axially in a first direction, wherein the second component includes a plurality of clamping tabs, with the clamping tabs collaborating with the first component in order to produce an axial force causing the radial walls to bear against one another.
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