公开(公告)号：US11585292B2

公开(公告)日：2023-02-21

申请号：US16969228

申请日：2019-02-13

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Bruno Alexandre Didier Jacon ,  Baghdad Achbari ,  Thomas Claude Broage ,  Florent Robert André Godin ,  Joël François Roudil ,  Hervé Simonotti

IPC: F02K1/80 ,  B64D27/10 ,  F02C7/28 ,  F02K3/02

Abstract: An outer shroud of an intermediate casing for a dual flow turbine engine for an aircraft, the shroud including: an annular downstream portion provided with a shroud opening passing through an annular downstream edge of the shroud; a connecting member (50) attached to the annular downstream portion, and intended to attach an arm that passes through a secondary flow path; an air-sealing and fire-resistance device including: a portion including: a pad arranged in a hollow annular area of the annular downstream edge of the shroud; a blade protruding from the pad and clamped between a circumferential end and the radially outer end of the arm, a leaf spring (pressing the pad into the hollow annular area.

公开(公告)号：US11480107B2

公开(公告)日：2022-10-25

申请号：US16970035

申请日：2019-02-14

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Bruno Alexandre Didier Jacon ,  Baghdad Achbari ,  Thomas Claude Broage ,  Hervé Simonotti ,  Soufien Akachkachy ,  Charles Maurice Jean-Louis Cheret ,  Joseph Taglialavore

IPC: F02C7/25 ,  F02C7/28 ,  F01D9/06 ,  F01D25/16 ,  F02K1/80 ,  F02K3/06

Abstract: A fire resistance device is intended to be interposed between an upstream end of an aircraft turbine engine mounting structure and a cowling of the turbine engine delimiting an inter-flow compartment.