Patent ID: 9061769
Filing Date: 2015-06-23
Classification: B64D,F02C,Y10T

Abstract:
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 from an upstream edge of said inner envelope over a distance L of between 20% and 90% of the mean axial span of said inner envelope and having a circumferential span a of between 60° and 150° about a longitudinal axis of said air inlet.