Nacelle incorporating an element for connecting a lip and an acoustic attenuation panel together

Patent metadata

Field	Value
Publication number	US-9352844-B2
Application number	US-201013518041-A
Country	US
Kind code	B2
Filing date	Dec 21, 2010
Priority date	Dec 22, 2009
Publication date	May 31, 2016
Grant date	May 31, 2016

Abstract

An aircraft nacelle includes a first subassembly consisting of a pipe ( 112 ) channeling an airflow in the direction of an engine having a covering or panel ( 118 ) for acoustic treatment, including, from the inside to the outside, a reflecting layer ( 120 ), at least one cellular structure ( 122 ), and at least one acoustically resistive structure ( 124 ) forming the aerodynamic surface of the pipe ( 112 ), as well as a second subassembly consisting of a lip ( 116 ) and a front frame ( 126 ), characterized in that it includes at least one connection element ( 134 ) which is separate from the two subassemblies and connected to a portion of the pipe ( 112 ) and to a portion of the lip forming an extension of the portion of the pipe at different points so as to be capable of enabling a relative movement between the two subassemblies.

First claim

The invention claimed is:

1. An aircraft nacelle comprising:
a first subassembly formed from a pipe that channels an air flow in a direction of a power plant;
a covering or panel for the first subassembly configured for acoustic treatment that comprises, from inside to outside:
a reflective layer,
at least one honeycomb structure, and
at least one acoustically resistive structure that forms an aerodynamic surface of the pipe;

a second subassembly formed from:
a lip, and
a front frame; and

a deformable junction element that is independent from the two subassemblies, connected to a portion of the pipe, and connected to a portion of the lip that is arranged in said portion of the pipe at different points so as to permit the deformable junction element to deform to absorb a portion of impact energy in accordance with an elongation coefficient of the deformable junction element, the deformable junction element comprising:
a first cylindrical part flattened and attached to an inside surface of a flange of the second subassembly, and
a second cylindrical part flattened and attached to an outside surface of an extension of the pipe,
wherein said first and second cylindrical parts are connected by a conical portion.

2. The aircraft nacelle according to claim 1 , further comprising:
a first connector attaching the first cylindrical part to the inside surface of the flange of the front frame; and
a second connector attaching the second cylindrical part to the outside surface of the extension at the end of the pipe.

3. The aircraft nacelle according to claim 1 , wherein the deformable junction element is formed from titanium.

4. An aircraft nacelle comprising:
a first subassembly formed from a pipe that channels an air flow in a direction of a power plant;
a covering or panel for the first subassembly configured for acoustic treatment that comprises, from inside to outside:
a reflective layer,
at least one honeycomb structure, and
at least one acoustically resistive structure that forms an aerodynamic surface of the pipe;

a second subassembly formed from:
a lip, and
a front frame; and

a deformable junction element that is independent from the two subassemblies, connected to a portion of the pipe, and connected to a portion of the lip that is arranged in said portion of the pipe at different points so as to permit the deformable junction element to deform to absorb a portion of impact energy in accordance with an elongation coefficient of the deformable junction element, the deformable junction element comprising:
a first cylindrical part connected to the second subassembly, and
a second cylindrical part connected to the portion of the pipe,
wherein said first and second cylindrical parts are connected by a cylindrical or conical portion, and
wherein the interconnecting cylindrical or conical portion comprises a rupture line.

Assignees

• Porte Alain
• Lalane Jacques
• Airbus Operations Sas

Inventors

• Porte Alain
• Lalane Jacques

Classifications

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• B64D2033/0206

  comprising noise reduction means, e.g. acoustic liners · CPC title

• B64C7/02

  Nacelles · CPC title

• B64D33/02 Primary

  of combustion air intakes · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title