EJECTION CONE FOR AN AIRCRAFT TURBINE ENGINE

Abstract: an exhaust cone for an aircraft turbomachine, extending along a longitudinal axis and having a radially internal annular wall and a radially external skin delimiting a primary flow path for hot gases and surrounding the internal annular wall, and partitions mounted radially between the external skin and the internal annular wall and intersecting them in a manner that together with the skin and wall delimits acoustic chambers. the exhaust cone can further include at least one seal arranged between a radial end of one of the partitions and at least one among the internal annular wall and the external skin.

Inventor(s): Tony MIOSSEC, Fabien BRAVIN, Christophe Jean François THOREL, Marc VERSAEVEL, Valentin SIMEON

CPC Classification: F02K1/04 (Mounting of an exhaust cone in the jet pipe)

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