Nacelle for an aircraft turbojet engine with an extended front lip
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United States of America Patent
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-
May 15, 2018
Issued Date -
N/A
app pub date -
Oct 16, 2015
filing date -
Apr 19, 2013
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A nacelle for an aircraft turbojet engine includes: a substantially cylindrical internal envelope, a substantially cylindrical external envelope, a downstream partition wall and an upstream partition wall secured to the cylindrical internal envelope and a front lip disposed forward of the upstream partition wall. The cylindrical internal envelope includes an upstream portion including an acoustic shroud connected, by an attachment flange, to a downstream portion including a fan casing. In particular, the front lip is extended and disposed over the upstream partition wall by presenting a downstream edge between the upstream and downstream partition walls in order to be secured to a homologous edge of the cylindrical external envelope so as to arrange a maintenance access to the attachment flange.
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