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Acoustic barrel for aircraft engine nacelle including crack and delamination stoppers

A technology for engine compartments and aircrafts, applied in the field of inner sound boxes, which can solve the problems of lack of multi-segment sound boxes

Active Publication Date: 2013-06-19
ROHR INC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to their one-piece design, the single-piece inner chords lack the damage-stopping add-ons of multi-segment chords

Method used

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  • Acoustic barrel for aircraft engine nacelle including crack and delamination stoppers
  • Acoustic barrel for aircraft engine nacelle including crack and delamination stoppers
  • Acoustic barrel for aircraft engine nacelle including crack and delamination stoppers

Examples

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Embodiment Construction

[0023] figure 1 There is shown an aircraft nacelle 1 comprising an inner acoustic box 10 at the inlet 1 a according to an embodiment of the invention. Such as figure 1 with 2 As shown, the casing 10 is a 360-degree single-piece annular structure. The receiver 10 includes an annular perforated inner panel or skin 12 , an imperforated outer panel or skin 14 radially spaced from the inner skin 12 , and an acoustic honeycomb core 16 disposed between the inner skin 12 and the outer skin 14 . The term "circular" includes along the length L of the nacelle 1 ( figure 1 ) diameter and shape configurations that vary in direction and are not intended to be limited to right cylinders. The inner skin 12, outer skin 14 and honeycomb core 16 may be of composite construction, such as graphite epoxy or the like. The inner skin 12 and outer skin 14 are bonded to the core 16 with an adhesive such as Henkel epoxy adhesive EA9258.1, or another adhesive material with comparable peel and shear ...

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PUM

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Abstract

An acoustic inner barrel (10) for an aircraft engine nacelle (1) inlet is constructed from a composite material and is formed as a single, 360-degree annular segment. The barrel includes an inner skin (12), an outer skin (14), a cellular core (16) disposed between the inner skin and the outer skin, and at least one crack and delamination stopper (50) extending radially from the inner skin to the outer skin.

Description

technical field [0001] The invention relates to an inner sound box for the entrance of an aircraft engine compartment. Background technique [0002] When an aircraft engine experiences a "blades out" event, it is important that the aircraft have the "fly home" capability (i.e., the ability to safely return to the ground in accordance with FAA principles). The ability of the nacelle to resist damage and maintain structural integrity during a "blade out" event is important to the homecoming function of the aircraft. [0003] Some known nacelle inlets include an inner sound box made up of multiple ring segments fastened using add-ons of fasteners. Add-ons serve to limit the propagation of damage through the receiver, in addition to securing the adjacent ring segments of the inner voice box. So, the "damage stop" add-on helps maintain the structural integrity of the inner sound box and, by extension, the entire nacelle in the event of a "blade out" event. An example of a mult...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D29/08
CPCY02T50/672F02C7/045B64D2033/0206B64D33/02Y02T50/60
Inventor 邱颂于佳克劳德·M·休伯特迈克尔·J·莱兰
Owner ROHR INC
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