Patent ID: 11920519
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Transport (Mechanical engineering)
Classification: CPC F  B | IPC B  F

Claim 0:
1. A fire resistance device intended to be placed between an upstream end of a mounting strut of a double-flow aircraft turbomachine, and a connecting cowling equipping said turbomachine, said connecting cowling being intended to connect an upstream ring radially delimiting towards the outside a portion of an inter-flow compartment, to an arm that extends radially across a secondary flow of the turbomachine, wherein the device comprises:
a contact structure comprising a first contacting lip, and defining a first contact end extending along a first line, the contact structure also comprising, at one of the longitudinal ends of the first contacting lip, an end section, wherein the end section comprises an open end which forms a continuation of the first contacting lip, wherein the end section further comprises a blocked end, wherein said open end and said blocked end are spaced relative to each other along said first line;
a support portion; and
a second contacting lip supported by the support portion via a junction area that supports the end section of the contact structure, the second contacting lip having a second contact end extending along a second line different from the first line, the second contacting lip having at one of its ends a blocking portion protruding according to the second line, the blocking portion being located at a distance from and facing the blocked end of the end section.