公开(公告)号：US10190430B2

公开(公告)日：2019-01-29

申请号：US14385867

申请日：2013-04-09

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Francois Leglaye ,  Emeric D'Herbigny

IPC: F01D11/00 ,  F01D9/02 ,  F23R3/00

Abstract: A turbine engine, a turbojet, or a turboprop engine, including an annular combustion chamber defined by an inner shell and an outer shell, a turbine distributor arranged downstream of the combustion chamber, with a downstream end of the outer shell and/or of the inner shell of the chamber including a radial rim arranged opposite a radial rim of an upstream end of the distributor, a sealing mechanism including at least one strip extending between the rims to provide a seal between the combustion chamber and the distributor. The sealing strip extends axially and circumferentially between the rims and bears sealingly against free ends of the rims.