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.

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

IPC: F02K1/04 ,  F02K1/80 ,  F02K1/82

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：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

IPC: F02K1/04 ,  F02K1/82

CPC classification number: F02K1/04 ,  F02K1/827

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.