TURBINE ENGINE, SUCH AS A TURBOJET OR A TURBOPROP ENGINE

摘要

The invention relates to a turbomachine, such as an airplane turbojet or turboprop, comprising an annular combustion chamber delimited by an internal ferrule (3) and an external ferrule (4), a turbine distributor (2) arranged in downstream of the combustion chamber (1), the downstream end of the outer shroud (4) and / or of the inner shroud (3) of the chamber comprising a radial rim (7) disposed opposite a radial rim ( 14) from the upstream end of the distributor (2), sealing means comprising at least one strip (17) extending between said flanges (7, 4) so as to seal between the combustion chamber ( 1) and the distributor (2). The sealing strip (17) extends axially and 1 circumferentially between said flanges (7, 14) and bears sealingly on the free ends of said flanges (7, 14).