公开(公告)号：US20160146051A1

公开(公告)日：2016-05-26

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: F01D25/24 ,  F01D25/30 ,  F01D9/02

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.

Abstract translation: 本发明涉及一种涡轮发动机外壳（尤其是涡轮喷气发动机排气罩），其包括至少部分地限定所述环箍（2）的一端的至少一个箍（2）和至少一个凸缘（3,4） ，以及至少一个至少部分地定位在所述箍（2）的外表面上的帽（5），所述帽（5）包括孔（6），所述孔能够容纳用于将所述壳体（1）紧固到支架 所述凸缘包括与所述至少一个盖（5）的所述孔（6）基本上同轴的进入切口（7a），所述进入切口（7a）能够进入所述孔（6），所述进入切口 （7a）设置在比凸缘（3,4）更宽的释放切口（7b）处，并且构成在所述释放切口（7b）上的凹部。 本发明还涉及一种包括壳体（1）和根据本发明的用于加工后者的方法的涡轮发动机。