|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02K-001/00 F02K-001/82 F01D-021/00 F01D-025/04 F02B-077/13 F01N-001/24 E04B-001/82 B64C-001/06 B64C-001/12 B64D-033/02 B64F-001/26|
|미국특허분류(USC)||181/213; 181/204; 181/210; 181/214; 181/222; 181/286; 181/290; 181/292; 181/293; 244/053.0B; 244/131; 244/132; 415/009; 415/119|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 22 인용 특허 : 29|
An acoustic inner barrel for an aircraft engine nacelle inlet is constructed from a composite material and is formed as a single, 360-degree annular segment. The barrel includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially from the inner skin to the outer skin.
We claim: 1. An acoustic inner barrel for an engine nacelle inlet, the acoustic barrel comprising: an annular inner skin; an annular outer skin; an annular acoustic cellular core disposed between the inner skin and the outer skin; and at least two reinforcement members extending radially from the inner skin, through the acoustic cellular core, and to the outer skin, wherein the inner skin, outer skin, acoustic cellular core and the at least two reinforcement members are bonded together to form a 360-degree, one-piece annular structure, wherein each rein...