公开(公告)号：US20150047356A1

公开(公告)日：2015-02-19

申请号：US14385867

申请日：2013-04-09

Applicant: SNECMA

Inventor： Francois Leglaye ,  Emeric D'Herbigny

IPC: F01D11/00 ,  F23R3/00

CPC classification number: F01D11/005 ,  F01D9/023 ,  F05D2240/57 ,  F05D2250/37 ,  F23R3/002 ,  Y02T50/671 ,  Y02T50/675

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.

Abstract translation: 涡轮发动机，涡轮喷气发动机或涡轮螺旋桨发动机，包括由内壳和外壳限定的环形燃烧室，布置在燃烧室下游的涡轮分配器，外壳的下游端和/ 所述室的内壳包括与所述分配器的上游端的径向边缘相对的径向边缘，密封机构，包括在所述边缘之间延伸的至少一个条，以在所述燃烧室和所述分配器之间提供密封。 密封条在轮缘之间轴向和周向延伸，并且密封地抵靠轮缘的自由端。