公开(公告)号：US10006307B2

公开(公告)日：2018-06-26

申请号：US14903266

申请日：2014-07-07

Applicant: SNECMA

Inventor： Benoit Debray ,  Gregory Ghosarossian-Prillieux ,  Mario De Sousa ,  Nicolas Pommier ,  Frederic Noel

IPC: F01D25/16 ,  F01D25/24 ,  F01D25/30 ,  F01D9/02 ,  F02C7/20 ,  F02K1/04

CPC classification number: F01D25/243 ,  F01D9/02 ,  F01D25/162 ,  F01D25/30 ,  F02C7/20 ,  F02K1/04 ,  F05D2220/323 ,  F05D2230/10

Abstract: The present invention relates to a turbine engine casing (1), in particular a turbojet exhaust casing, including at least one hoop (2) and at least one flange (3, 4) at least partially defining one end of said hoop (2), and at least one cap (5) positioned at least partially on the outer surface of the hoop (2), said cap (5) including a bore (6) capable of receiving an element for fastening the casing (1) to a bracket, the flange including an access cut-out (7a) substantially coaxial with the bore (6) of said at least one cap (5), said access cut-out (7a) enabling access to the bore (6), the access cut-out (7a) being provided at a release cut-out (7b) which is wider than the flange (3, 4) and constitutes a recess on said release cut-out (7b). The invention also relates to a turbine engine including a casing (1) and to a method for machining the latter according to the present invention.