|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64D-033/02 F02C-007/04 F02C-007/045|
|우선권정보||FR-10 60285 (2010-12-09)|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 6|
An air inlet for nacelle of an aircraft propulsion unit comprising an inner envelope provided with a plurality of orifices for passage of fluid passing through the envelope, and a lip connected to the upstream edge of the inner envelope, and having a portion devoid of orifices for passage of fluid with an axial span of between 20% and 90% of the span of the inner envelope, and a circumferential span a of between 60° and 150° about a longitudinal axis of the air inlet. A process for repairing an air inlet comprising cutting out a recess in an upstream edg...
1. An air inlet for the nacelle of an aircraft propulsion unit comprising a substantially annular outer cowling, a substantially annular inner envelope intended to delimit a channel feeding air to a turbojet engine and comprising a plurality of fluid passage orifices passing through said envelope, and a substantially annular lip connected to respective upstream edges of said outer cowling and of said inner envelope so as to form a leading edge of said air inlet, wherein the inner envelope has a portion devoid of fluid passage orifices extending axially f...