公开(公告)号：US20240125283A1

公开(公告)日：2024-04-18

申请号：US18350885

申请日：2023-07-12

Applicant: Safran Nacelles

Inventor： Jean-Baptiste DELARUE ,  Bertrand Léon Marie DESJOYEAUX ,  Moncef M'HASNI

IPC: F02K1/32 ,  B64D29/06

CPC classification number: F02K1/32 ,  B64D29/06 ,  F05D2230/60

Abstract: An assembly including a nacelle panel of an aircraft engine, the nacelle panel including an outer skin, an inner skin and a central layer interposed between the outer skin and the inner skin, and the nacelle panel having a free inner enclosure contiguous with the outer skin, and a member forming a link including one or more degrees of freedom, the member being attached to the nacelle panel solely by one or both of the outer skin and the inner skin, and the member extending facing the free inner enclosure.

公开(公告)号：US20240426260A1

公开(公告)日：2024-12-26

申请号：US18700340

申请日：2022-10-14

Applicant: SAFRAN NACELLES

Inventor： François BELLET ,  Moncef M'HASNI

IPC: F02K1/82 ,  F02K1/68

Abstract: A rear assembly for a turbojet engine nacelle includes at least one composite wall separating a cold portion from a hot portion comprising an element to be cooled, the composite wall having first and second skins which extend facing the cold portion and the hot portion respectively, and which are separated from one another by a middle assembly having cells delimited by internal walls. The first skin includes a plurality of through-openings connecting the cold portion and the cells, the internal walls having through-openings connecting the cells to one another, and the second skin having a through-opening which has its mouth facing the element to be cooled.