Safran Nacelles

Safran Ceramics

Vincent Devanlay

Jean-Philippe Joret

Fabien Bravin

Thomas Vandellos

Marc Versaevel

Clément Marie Benoît Roussille

Boualem Merabet

Tony Miossec

Marine Ollivier

Guillaume Levieux

Valentin Simeon

An assembly for an ejection cone of an aircraft turbomachine, including a first annular wall and a plurality of first partitions and of second partitions extending substantially perpendicularly from the first wall, the first partitions additionally extending wholly in the axial direction and the second partitions extending wholly in a circumferential direction between the adjacent pairs of first partitions and being curved partitions including at least one arcuate portion in the axial direction upstream or downstream, the first wall, the first partitions and the second partitions additionally defining between them a plurality of acoustic boxes distributed around the first wall.

Assembly for an ejection cone of an aircraft turbomachine

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.

Fastening of an exhaust cone in a turbomachine turbine

The invention relates to an assembly for a turbine of a turbomachine with a longitudinal axis (X) comprising:

Fastening of an exhaust cone in a turbomachine nozzle

The invention relates to an assembly for a turbomachine, comprising an exhaust cone () and an exhaust case having an annular inner shell, the exhaust cone () and the exhaust case extending about an axis (X), the exhaust cone () having a radially outer skin () extending in the projection of said inner shell and a radially inner skin () defining a chamber () with the outer skin (), the upstream end () of the cone () being fastened to the inner shell () via connecting lugs (), the assembly comprising an annular fairing () located radially outside said lugs () and extending axially between the inner shell () of the exhaust case () and the outer skin () of the exhaust cone (), said fairing () extending in the projection of said inner shell () and of the outer skin (), the assembly being characterized in that the fairing () is segmented and consists of multiple angular segments () arranged circumferentially end to end.

Exhaust cone for a turbomachine

An assembly for a turbomachine nozzle having a longitudinal axis (X) includes an exhaust cone with an annular outer wall for guiding a primary air flow and an annular chamber placed radially inside said annular outer wall. The annular chamber includes an annular inner wall placed radially inside the annular outer wall of the exhaust cone. An exhaust case is placed upstream of the ejection cone. A connecting member is interposed longitudinally between the exhaust case and the exhaust cone and fastened to the exhaust case and to the annular inner wall. The assembly further includes elastic means configured to deform radially and prestressed radially between the annular outer wall and the connecting member.

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MOISSY-CRAMAYEL, France

Vincent Devanlay