Turbo shaft engine e.g. turbojet engine, for airplane, has strip extending radially between edges of rings to ensure sealing between combustion chamber and nozzle, where edge of downstream end of rings and/or strip comprises convex surface

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.