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

Claim 7:
8. A propulsion unit for aircraft comprising a double-flow aircraft turbomachine, as well as a mounting strut of the turbomachine intended to fasten it on a wing element of the aircraft,
the turbomachine including an inter-flow compartment arranged between a primary flow and a secondary flow of the turbomachine, as well as an arm that extends radially across the secondary flow and communicating with the inter-flow compartment, the latter being partly radially delimited towards the outside by an upstream ring connected to the arm with the aid of two connecting cowlings respectively arranged on either side of an upstream end of the mounting strut, in a transverse direction of the propulsion unit,
the upstream end of the mounting strut comprising two lateral faces, as well as a peripheral bearing surface following the contour of a base of this upstream strut end,
wherein the propulsion unit also comprises, associated with at least one of the two connecting cowlings, a fire resistance device according to claim 1, placed between the upstream end of the mounting strut and the connecting cowling to which the device is fastened.