Device for de-icing the inlet of a nacelle of an aircraft engine, method for producing such a de-icing device, and aircraft engine nacelle provided with such a de-icing device

Patent metadata

Field	Value
Publication number	US-2016257418-A1
Application number	US-201615153172-A
Country	US
Kind code	A1
Filing date	May 12, 2016
Priority date	Nov 15, 2013
Publication date	Sep 8, 2016
Grant date	—

Abstract

A de-icing device is provided that includes a piccolo tube integrated with a front bulkhead for limiting an inner volume of a perforated front lip. The piccolo tube is in contact with a noise reduction cellular structure provided with perforations and hot air circulation channels delivered by the piccolo tube, the de-icing hot air being diffused through the perforations and channels of the cellular structure, on the perforations facing the front lip.

First claim

What is claimed is:

1 . A device for de-icing an air intake of an aircraft engine nacelle, of a kind comprising a hot air generator connected by at least one duct to a piccolo tube disposed in relation with an inner volume of a front lip of the nacelle, the front lip being provided with perforations for a flow of de-icing hot air and at least one noise reduction cellular structure disposed on at least one portion of the perforated skin of the intake lip, the cellular structure being of a kind having a plurality of channels for circulation of the hot air diffused by the piccolo tube, wherein the piccolo tube has an annular profile integrated to a front bulkhead for limiting the inner volume of the front lip and in that the piccolo tube is provided with a plurality of perforations to carry out diffusion of hot air supplied by one or more duct(s) from the hot air generator through said front bulkhead, in that the cellular structure is at least partially disposed between a portion of the piccolo tube and a portion facing an inner face of the perforated skin for limiting the front lip and in that a portion of the cellular structure facing the piccolo tube serves as a skin for limiting the noise reduction cellular structure.

2 . The de-icing device according to claim 1 , wherein a profile of the piccolo tube is determined depending on the shape of the front lip and/or on the bulkhead so as to improve the efficiency of the de-icing.

3 . The de-icing device according to claim 1 , wherein the piccolo tube is supplied with de-icing hot air by at least one hot air duct connected through an aperture of the bulkhead to the de-icing hot air generator.

4 . The de-icing device according to claim 4 , wherein the de-icing hot air generator is disposed in an area of the nacelle rearward of an intermediate bulkhead rearward of the front bulkhead on which the piccolo tube is integrated and in that the duct passes through apertures of said front bulkhead and of said intermediate bulkhead.

5 . The de-icing device according to claim 1 , wherein hot air channels formed in the cellular structure are made on a portion at least of a height of cells and open onto a collector disposed on a side of a lower skin of the front lip and at a rear of the cellular structure and which is connected by at least one outlet tube opening onto an aperture of an upper face of the front lip and in that the hot air channels are disposed in areas of the cellular structure which are not provided with acoustic perforations, but release points for injecting de-icing air on an upper skin of the cellular structure.

6 . A method for manufacturing a device for de-icing an air intake section of an aircraft engine nacelle comprising:
forming an annular front lip provided with acoustic perforations and a noise reduction cellular structure provided with channels for circulation of de-icing hot air opening into a hot air collector; forming an annular piccolo tube, pierced with perforations for diffusing the de-icing hot air provided by a hot air duct coming from a de-icing hot air generator, the piccolo tube having a profile adapted to a shape of the front lip and to an upper face of said cellular structure; fastening the piccolo tube by its lower edge to a lower face facing the front lip; forming a front bulkhead for closing an inner volume of the front lip and starting from the piccolo tube and in fastening the piccolo tube by its upper and lower edges by attaching to a face facing the front lip, and attaching adapted edges facing the piccolo tube.

7 . The manufacturing method according to claim 6 , further comprising forming the de-icing air circulation channels and/or the excess hot air collector in which the channels open into the cellular structure by at least partially machining cell groups or by partially bonding stacked sheets for making the cells so as to make, by expansion of the stack of sheets, at least one de-icing hot air circulation channel with a determined width and/or the excess hot air collector.

8 . An aircraft engine nacelle manufactured according to claim 6 .

9 . An aircraft engine nacelle having a de-icing device according to claim 1 .

Assignees

• Aircelle Sa

Inventors

• Caruel Pierre

Classifications

• B64D33/02 Primary

  of combustion air intakes · CPC title

• B64D2033/0233

  comprising de-icing means · CPC title

• B64D2033/0206

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

• B64D15/04

  Hot gas application · CPC title

• B64D2033/0286

  for turbofan engines · CPC title