JP-2021529122-A5 -

Dates

Publication Date

20230529

Application Date

20190625

Description

Furthermore, mounting struts for securing turbomachines to aircraft wing elements may have upstream ends close to the junction between the arm passing through the fan flow stream and the upstream ring of the interflow compartment. This raises fire resistance issues, as it is required to prevent the propagation of flames generated within the interflow compartment, particularly to prevent these flames from reaching the upstream zone of nearby mounting struts. (Prior art document) (Patent Document) (Patent Document 1) International Publication No. 2017/013356 The integral component configuration is made possible by the simple shape of the apparatus according to the present invention, particularly by the use of contact lips. Furthermore, unlike the use of tubular contact zones, such as beads or molding contact zones, these do not require the use of inserts during the manufacture of the apparatus. Moreover, the lips are usually easily deformable and therefore do not require any specific prestressing operations after assembly. Any deformation necessary to ensure its fire-resistant function may simply be the result of support from surrounding elements, such as the support of a movable cover seal of a nacelle designed to be compressed within the zone. Preferably, the second contact lip is constrained between the lateral surface of the upstream end of the mounting strut and the movable cover seal of the nacelle . 1: Aircraft twin-spool turbomachine 7: Upstream end 8a: Interflow compartment 9: Mounting strut 10: Upstream ring 22: Arm 26: Fan flow stream 30: Connecting cowling 40: Seal 42: Side view 44: Base 50: Fire protection device 50': Complementary fire protection device 52a: First contact lip 52b: Second contact lip 54: Mounting element 56: Mounting portion 60: Support portion 62: Second joint 70a: First contact end 70b: Second contact end 71: Bead segment 71': Bead seal 72a: First curve, curved line 72b: Second line 73, 73': Contact structure 75a, 75b: Longitudinal end 76: Through hole 77a: Axial end 82: Movable cover of nacelle 88: Hole 90: Elongated mounting element 99: Elastomer material 100: Aircraft propulsion unit 110: Fibrous layer 112': Connecting pin S1: Approximately planar contact surface