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Patent Agency Ranking
公开(公告)号：US12253048B2
公开(公告)日：2025-03-18
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：US12196157B2
公开(公告)日：2025-01-14
申请号：US18250964
申请日：2021-10-29
Applicant: SAFRAN CERAMICS
Inventor： Eric Conete , Benoit Carrere , Thomas Vandellos
IPC: 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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公开(公告)号：US11821387B2
公开(公告)日：2023-11-21
申请号：US17640992
申请日：2020-09-02
Applicant: SAFRAN CERAMICS
Inventor： Eric Conete , Benoit Carrere
CPC classification number: F02K1/04 , F02K1/80 , F02K1/827 , F05D2220/323 , F05D2230/232 , F05D2240/1281 , F05D2260/31 , F05D2260/601 , F05D2260/96 , F05D2300/6033
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).-
公开(公告)号：US11519361B2
公开(公告)日：2022-12-06
申请号：US17267361
申请日：2019-08-09
Applicant: SAFRAN CERAMICS
Inventor： Eric Conete , Benoit Carrere
Abstract: An assembly for an aircraft turbojet engine is described. The assembly includes a central gas-exhaust element and a connecting flange interposed between, upstream, a metallic outlet of a turbojet engine and, downstream, the central element. The connecting flange consists of an annular part and flexible lugs having axially: a first end where the lug is connected to the annular part, and a second free end, projecting radially outwards from the first end and towards which the lug is fixed with the central element.
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公开(公告)号：US20210293201A1
公开(公告)日：2021-09-23
申请号：US17267361
申请日：2019-08-09
Applicant: SAFRAN CERAMICS
Inventor： Eric Conete , Benoit Carrere
Abstract: An assembly for an aircraft turbojet engine is described. The assembly includes a central gas-exhaust element and a connecting flange interposed between, upstream, a metallic outlet of a turbojet engine and, downstream, the central element. The connecting flange consists of an annular part and flexible lugs having axially: a first end where the lug is connected to the annular part, and a second free end, projecting radially outwards from the first end and towards which the lug is fixed with the central element.
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