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Structure for an air inlet lip of an electric de-icing pod comprising an acoustic attenuation zone

An air intake and pod technology, which is applied to the combustion of the air intake of the power plant, electrical components, and deicing devices, etc., can solve the problem of not considering the noise reduction area.

Inactive Publication Date: 2013-06-12
AIRCELLE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0012] However, such a solution does not take into account that there may be an anechoic zone associated with the anechoic structure on the air intake structure

Method used

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  • Structure for an air inlet lip of an electric de-icing pod comprising an acoustic attenuation zone
  • Structure for an air inlet lip of an electric de-icing pod comprising an acoustic attenuation zone
  • Structure for an air inlet lip of an electric de-icing pod comprising an acoustic attenuation zone

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Embodiment Construction

[0036] figure 1 The pod 1 according to the invention shown in , constitutes a tubular housing for a turbojet engine (not visible) for guiding the air flow generated by said turbojet engine. The pod 1 is located under the wing 2 and said pod 1 is attached to the wing 2 by brackets 3 . Said nacelle 1 also houses the various components necessary for the operation of the turbojet engine.

[0037] More precisely, the structure of the pod 1 consists of: a front part forming the air intake 4; a central part 5 surrounding the turbojet fan (not visible), and surrounding the turbojet engine and housing the thrust reversal system ( not visible) rear 6.

[0038] The air intake 4 is divided into two parts, namely: on the one hand it comprises an intake flange 4a adapted to optimally capture the turbojet with the air required to supply the internal compressor and fan of the turbojet; on the other hand Also included is a downstream structure 4b to which said flange 4a is fitted and which ...

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Abstract

The structure (7) has a heating electric element (14) connected to a power supply, where the heating electric element is situated between an internal skin (13) and an external skin (12) of the structure. The external skin is directed towards exterior of a lip, and the internal skin is directed towards interior of the lip. A sound attenuation zone presenting perforations (11) that traverse the structure and is associated to a sound attenuation structure provided on the internal skin.

Description

technical field [0001] The invention relates to a structure for a flange of a turbojet engine nacelle air intake, the structure comprising an outer skin designed towards the outside of the flange and an inner skin designed towards the inside of the flange. Background technique [0002] The aircraft is powered by one or more propulsion units including turbojet engines housed in tubular pods. The individual propulsion units are attached to the aircraft by brackets usually located under the wings or on the fuselage. [0003] The structure of the pod generally includes: an air intake located upstream of the motor; a mid-section designed to surround the fan of the turbojet engine; a downstream portion housing the thrust reverser and designed to surround the combustion chamber of the turbojet engine part, and the pod usually ends with an exhaust nozzle whose outlet is located downstream of the turbojet engine. [0004] The air intake comprises, on the one hand, an intake flange...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D15/12B64D33/02F02C7/047
CPCY02T50/672B64D33/02B64D15/12B64D2033/0233H05B3/267F02C7/047Y02T50/60
Inventor 盖伊·贝纳德·沃谢尔
Owner AIRCELLE
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