TURBOMACHINE, TELLE QU'UN TURBOREACTEUR OU UN TURBOPROPULSEUR D'AVION

摘要

The engine has a turbine nozzle arranged downstream of an annular combustion chamber. A downstream end of an external ring (4) and/or an internal ring comprises an edge placed with respect to an edge (14) of an upstream end of the nozzle. A sealing part includes a strip (17) that extends radially between the edges of the rings to ensure sealing between the combustion chamber and the nozzle. The edge of downstream end of the rings and/or the strip comprises a convex surface (7c) that supports the strip on the edge of the downstream end of the rings.