A rear assembly for a turbojet engine nacelle, comprising at least one composite wall (20) separating a cold portion (8) from a hot portion (12) comprising an element (23) to be cooled, said composite wall (20) comprising first and second skin layers (30, 32) extending respectively facing said cold portion (8) and said hot portion (12) and separated from each other by an intermediate assembly (34), the intermediate assembly includes cells delimited by an inner wall (42). According to the invention, the first skin (30) comprises a plurality of through-openings (48) connecting the cold portion (8) and the cells, the inner wall (42) comprises through-openings (44) connecting the cells to each other, and the second skin (32) comprises through-openings (52) having their mouth facing the elements (23) to be cooled.
一种用于涡轮喷气发动机短舱的后部组件,其包括将冷部分(8)与包括待冷却元件(23)的热部分(12)隔开的至少一个复合壁(20),所述复合壁(20)包括第一和第二表层(30,32),所述第一和第二表层分别面向所述冷部分(8)和所述热部分(12)延伸且通过中间组件(34)彼此隔开,所述中间组件包括由内壁(42)定界的单元。所述第一表层(30)包括连接所述冷部分(8)与所述单元的多个穿通开口(48),所述内壁(42)包括将所述单元彼此连接的穿通开口(44),并且所述第二表层(32)包括穿通开口(52),所述穿通开口具有其面向所述待冷却元件(23)的口部。
Rear assembly for turbojet engine nacelle
用于涡轮喷气发动机短舱的后部组件
2024-06-07
Patent
Electronic Resource
Chinese
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