[go: up one dir, main page]

WO1992012854A1 - Element structurel alveolaire - Google Patents

Element structurel alveolaire Download PDF

Info

Publication number
WO1992012854A1
WO1992012854A1 PCT/GB1992/000118 GB9200118W WO9212854A1 WO 1992012854 A1 WO1992012854 A1 WO 1992012854A1 GB 9200118 W GB9200118 W GB 9200118W WO 9212854 A1 WO9212854 A1 WO 9212854A1
Authority
WO
WIPO (PCT)
Prior art keywords
cells
component
cellular
face
panel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/GB1992/000118
Other languages
English (en)
Inventor
Robert Samuel Wilson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Short Brothers PLC
Original Assignee
Short Brothers PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Short Brothers PLC filed Critical Short Brothers PLC
Priority to JP4503571A priority Critical patent/JPH06504629A/ja
Priority to BR9205443A priority patent/BR9205443A/pt
Publication of WO1992012854A1 publication Critical patent/WO1992012854A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/12—Layered products comprising a layer of synthetic resin next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/024—Woven fabric
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/16—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by features of a layer formed of particles, e.g. chips, powder or granules
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C2/00—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels
    • E04C2/30—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure
    • E04C2/34—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts
    • E04C2/36—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels
    • G—PHYSICS
    • G10—MUSICAL INSTRUMENTS; ACOUSTICS
    • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
    • G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/172—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/02—Cellular or porous
    • B32B2305/024—Honeycomb
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/10—Properties of the layers or laminate having particular acoustical properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/10—Properties of the layers or laminate having particular acoustical properties
    • B32B2307/102—Insulating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2607/00—Walls, panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0206—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners

Definitions

  • the present invention relates to structural cellular components and is particularly although not exclusively concerned with a structural cellular component for a noise attenuation panel for use in the attenuation of noise in aero engines.
  • a noise attenuation panel having a backing sheet, a facing sheet and a cellular core having a multiplicity of opened ended juxtaposed cells.
  • the backing sheet extends across the open ends of the cells at the rear of the core and the facing sheet extends across the open ends of the cells at the front of the core.
  • the facing sheet is made of a porous permeable thermoplastics material preferably produced by a powder sintering process and the backing sheet is imperforate and impermeable.
  • the noise attenuation panel disclosed in GB-A-2223448 is proposed for use in reducing turbine engine noise and is formed as an integral part of an aero engine structure.
  • the panels form part of a cowling surrounding a turbine engine inlet duct or be placed adjacent a high turbulence region of the fan of a turbofan engine.
  • the cellular core in the panel specifically disclosed in GB2223448A is furthermore formed by cells having wall portions which extend parallel to each other and perpendicular to the backing and facing sheets.
  • a structural cellular component for a noise attenuation panel comprising wall portions which provide bounding surfaces for an array of cells and which terminate at opposite faces of the component, characterised in that the wall portions or predetermined ones of the wall portions forming the cells extend to at least one of the faces of the component at an angle or angles inclined to the normal to that face.
  • a first embodiment of the first aspect of the present invention is characterised in that the wall portions of the cellular component provide bounding surfaces for an array of juxtaposed cells which terminate in open ends at one of the faces of the component with the wall portions extending to that face at angles inclined to the normal to that face.
  • the cells also terminate in open ends at the opposite face of the component with the wall portions extending to the opposite face at angles inclined to the normal to that face.
  • the wall portions extend to the face or faces of the component along lines which are parallel to each other.
  • the angle at which the wall portions are inclined to the normal to the or each face of the component is in excess of 20°.
  • the cells are of constant cross-section with the lateral edges of each cell lying along lines parallel to each other.
  • the cells are of hexagonal cross-section but in alternative embodiments of the invention the cells may conform to an isogrid or orthogrid pattern.
  • the wall portions or predetermined ones of the wall portions extend to the face or each face of the component along lines which are not parallel to each other.
  • the cells may be of pyramidal form or in the form of truncated pyramids.
  • a noise attenuation panel comprising a cellular component part in the form of a component according to the first aspect of the invention, a backing component part extending across one face of the cellular component part at the rear thereof and a facing component part extending across the other face of the cellular component part at the front thereof.
  • the facing component part comprises or includes an outer facing sheet which is made of a porous permeable thermoplastics material.
  • the porous permeable thermoplastics material for the outer facing sheet is produced by powder sintering a thermoplastics material.
  • the facing component part further includes an inner facing sheet made from an open square weave fabric having apertures constituted by the openings between adjacent warp and weft threads of the fabric.
  • the cellular component part comprises an upper cellular element in the form of a component according to the first aspect of the invention, a lower cellular element in the.form of a component according to the first aspect of the invention and positioned beneath the upper cellular element and a septum sheet which extends across the lower cellular element at an upper face thereof and across the upper cellular element at the lower face thereof.
  • the upper and lower cellular elements comprise identical arrays of cells inclined to the normal to the panel.
  • the upper and lower cellular elements are arranged one above the other and the cells of the one are inclined to the normal to the panel in the same direction as the cells of the other.
  • the two cellular elements are so positioned and arranged that the upper open ends of the cells of the upper cellular element are in registration with the open upper ends of the cells of the lower cellular element, whereby the lower open ends of the cells of the upper element are out of registration with the upper open ends of the cells of the lower element.
  • the two cellular elements are so arranged that the lower open ends of the cells of the upper cellular element are in registration with the upper open ends of the cells of the lower cellular element, whereby the cells of the lower cellular element form a continuation of the cells of the upper cellular element.
  • the upper and lower cellular elements are so positioned and arranged one above the other that the cells of the one element are inclined to the normal to the panel in a direction opposite to that of the cells of the other element.
  • the septum sheet may be constructed from a porous permeable thermoplastics material or alternatively made of a stainless steel fabric.
  • the upper cellular element or the lower cellular element or both may be made from an impermeable material or from a porous permeable thermoplastics material.
  • an aero engine having a surface subjected to the passage across it of gaseous flow and a noise attenuation panel according to the second aspect of the invention so positioned that its front face forms the surface or part of the surface subjected to passage of the gaseous flow across it.
  • Fig. 1 is a schematic isometric view from above of a noise attenuation panel embodying a structural cellular component according to a first embodiment of the invention
  • Fig. 2 is a schematic cross section of an end region of the panel shown in Fig. 1, secured to a supporting channel member;
  • Figs. 3, 4 and 5 are schematic cross sectional scrap- views of noise attenuation panels according to three further embodiments of the invention.
  • Fig 6 is a schematic cross-section of an aero engine embodying noise attenuation panels according to the invention.
  • the noise attenuation panel 10 comprises a backing sheet 11, a cellular core 12 and inner and outer facing sheets 13 and 14.
  • the cellular core 12 comprises a multiplicity of open- ended juxtaposed cells 15 of hexagonal cross section to provide a honeycomb configuration in which the lateral edges 16 are (i) parallel to each other, (ii) lie in planes which are perpendicular to the backing sheet 11 and parallel to the edge 111 of the sheet 11 and (iii) lie on lines which are inclined to the normal to the backing sheet, whereby the length of the cells 15 between the backing sheet 11 and the inner facing sheet 13 is greater than the distance of separation of the two sheets 11 and 13.
  • the backing sheet 11 is unperforated and made from an impermeable sheet material, as shown in Fig. 2, and is secured by an epoxy resin adhesive El to the lower face of the cellular core 12.
  • the inner facing sheet 13 is made from an open square weave fabric formed from a carbon fibre/resin matrix composite material and the weave is such as to provide apertures constituted by the openings between adjacent warp and weft threads of the fabric.
  • the fabric is preferably so woven as to produce a proportion of open aperture area relative to the total surface area of the sheet of around 30%. At the same time, the fabric is so woven that a relatively large number of its apertures are contained within the bounds of each cell 15 of the cellular core 12.
  • the outer facing sheet 14 comprises a sheet of a porous permeable thermoplastics material produced by powder sintering the thermoplastic.
  • suitable thermoplastics materials include polyether ketone, polyether ether ketone, polyaromatic ketone, polyphenylene sulphide, polyamide-imide, thermoplastic polyimide, polyether-imide, polyurethane and polyethylene.
  • the outer facing sheet 14 is bonded to the inner facing sheet 13 and the inner facing sheet 13 is, as shown in Fig.2, secured to the upper face of the cellular core 12 by means of an epoxy resin adhesive E2.
  • the inner woven facing sheet 13 in a part cured condition and to bring the outer facing sheet 14 into contact with it during a final curing step so that the resin serves to bond the two sheets together.
  • the combined sheets 13 and 14 may then be secured to the upper face of the cellular core 12 using the epoxy resin adhesive E2.
  • the epoxy adhesives El and E2 may for example be obtained from Ciba-Geigy Plastics & Additives Company Limited of Cambridge, England. Adhesives and resins need not however be epoxy resin adhesives, but could for example be a phenolic, polyimide or thermoplastics resin.
  • the backing sheet 11 is imperforate and made of a non- porous impermeable material and may be made of any of the following materials:-
  • thermoplastic where for example the thermoplastic is polyether ether ketone, the material being automatically tape wound or hand laid.
  • thermoplastic is polyether ether ketone, the material being automatically tape wound or hand laid.
  • carbon/epoxy resin is a carbon/thermoplastic composite where for example the thermoplastic is polyether ether ketone, the material being automatically tape wound or hand laid.
  • the cellular core 12 in the embodiment of the invention illustrated is made from a non-porous impermeable sheet of any of the following materials:-
  • thermoplastic such as polyether ether ketone.
  • NOMEX being a registered trade mark for an aramid fibre paper impregnated with various resins to produce a structural material.
  • aramid is meant an aromatic polya ide polymer.
  • the cellular core 12 may however if desired be made of a porous permeable thermoplastics material and may be in the same form as the outer facing sheet 14.
  • the panel 10 is of arcuate form, possibly of double curvature, and is embodied as a structural part of a duct of a nose cowl of a turbofan aero engine, the panel 10 being one of several arcuate panels disposed just upstream of the fan of the engine. It is, of course, of vital importance that the panel does not deteriorate in use and, in particular, that no part of it becomes detached from its supporting structure.
  • the structure will usually include supporting channel members of which only one member 17 is shown in Fig. 2.
  • the panel 10 is secured to the member 17 by bonding the inner facing sheet 13 to an outer face of a flange 18 of the channel member 17 using a carbon bond 19 and by bonding the backing sheet 11 to the outer face of a flange 20 of the channel member 17 using a carbon to carbon bond 21.
  • the gap between the panel 10 and the base 22 of the channel member 17 may be sealed or closed by use of a mastic 23.
  • a panel having an outer facing sheet 14 made of a porous thermoplastics material as described with reference to Figs. 1 and 2 has been found to give rise to several advantages over the panels of the prior proposals, including the following:-
  • the cellular structure of the facing sheet when produced by the powder sintering technique can be made to meet permeability requirements over a wide range.
  • the cellular structure may be made permeable to gaseous flow over a wide range of tightly controlled flow and resistance requirements which will be engine dependent and non permeable to a wide range of liquids and solid contaminants.
  • thermoplastic component parts do not have the problem of metal corrosion
  • the acoustic absorbing properties of the panel are improved by an appropriate inclining of the cells of the core to the backing and facing sheets, thereby extending the length of the cells without increasing the panel thickness and thereby extending the sound attenuation of the panel to the lower frequencies generated in the large diameter UHB ratio turbofan engines.
  • a panel according to a second embodiment of the invention is illustrated, in which the cellular core 12 of the embodiment of the invention described with reference to Figs. 1 and 2 is replaced by a split cellular core comprising an upper cellular element 121 having a multiplicity of open-ended juxtaposed inclined cells 151, a lower cellular element 122 having a further multiplicity of open-ended juxtaposed inclined cells 152 and a septum sheet 24 which extends across the ends of the cells 152 of the lower cellular element 122 at the upper face thereof and the ends of the cells 151 of the upper cellular element 121 at the lower face thereof.
  • the cells of the two cellular elements 121 and 122 form identical arrays of the inclined cells as described with reference to Fig 1 and are arranged one above the other.
  • the upper open ends of the cells 151 and 152 are arranged one above the other, as a consequence of which the lower open ends of the cells 151 of the upper element 121 are not in alignment with the upper open ends of the cells 152 of the lower element 122.
  • the backing sheet 11, the inner and outer facing sheets 13 and 14 and the upper and lower cellular elements 121 and 122 of the panel shown in Fig. 3 are constructed and bonded together in the same manner as the sheet 11, core 12 and facing sheets 13 and 14 of the embodiment described with reference to Figs. 1 and 2, with the backing sheet 11 being secured to the lower face of the lower cellular element 122 and the inner and outer facing sheets 13 and 14 being secured to the upper face of the upper element 121.
  • the septum sheet 24 is likewise bonded to adjacent faces of the cellular elements 121 and 122. It is constructed from a porous permeable thermoplastics material and may take the same form as that of the outer facing sheet 14 of the panel described with reference to Figs. 1 and 2.
  • the inner facing sheet 13 of the panel described with reference to Figs.l and 2 is omitted and the outer facing sheet 14, which is made of the porous thermoplastics material, is adhered direct to the upper face of the cellular core 12 using adhesive E2.
  • a fourth embodiment of the invention is illustrated which corresponds to the embodiment of the invention described with reference to Fig. 3, except that the cells 151 of the upper cellular element 121 are inclined in one direction and the cells 152 of the lower element 122 are inclined in the opposite direction and except insofar as the inner facing sheet 13 is omitted and the outer facing sheet 14 is adhered direct to the face of the upper cellular element 121 in the manner described for the panel illustrated in Fig. 4.
  • the panel described with reference to Fig. 3 may be modified by making the upper cellular element 121 or the lower cellular element 132 or both of a porous thermoplastics material and may be made 'from any of the materials proposed for the outer facing sheet 14 of the panel described with reference to Figs, l and 2.
  • the septum sheet 24 in the panels illustrated in Figs. 3 and 5 is described as being made of a porous thermoplastics material. It may however if desired be made of a stainless steel fabric or any of the above- mentioned materials which are suitable for the inner facing sheet 13, the requirement of course being that the sheet is either porous and permeable, perforated or apertured.
  • cells 15 of hexagonal cross section have been provided. It will however be appreciated that cells of other cross sections, for example conforming to an isogrid or orthogrid pattern, can alternatively be used.
  • the cells 15 are prismatic in form, that is to say, are of constant cross section with the lateral edges 16 of each cell 15 lying along lines parallel to each other. It will however be appreciated that cells of non-constant cross section may be provided in which the lateral edges or some of the lateral edges of each cell 15 are not equally inclined, as for example where the cells are of pyramidal form or in the form of truncated pyramids, so as to provide cells in which the effective length varies within the cell.
  • an aero engine 25 is schematically illustrated and includes a turbofan power unit 26 mounted within a nacelle 27 suspended from a pylon 32.
  • the nacelle 27 includes a nose cowl 28 having an outer wall 29 and an inner wall 30.
  • the inner wall 30 is in part formed by noise attenuation panels P which may take the form of panels as described and illustrated with reference to Figs. 1 to 5.
  • the panels P are arranged to form part of the inner wall of the nose cowl 28 and serve to reduce noise created by the high speed flow of air passing through the duct 31 into the power unit 26, as well as to reduce noise generated by the fan blades of the unit 26 .
  • the panels in Fig. 6 are not employed to reduce air noise by a reduction of the air speed by passage of the air through the panels, but by contrast acoustic attenuation is achieved without affecting the speed of the air which generates the noise, that is to say, the air does not pass through the noise attenuation panels P.
  • the power unit is carried by the wing mounted pylon 32. It will however be appreciated that the noise attenuation panels according to the present invention may be equally well be employed for reducing noise in other aero engine installations.

Landscapes

  • Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Acoustics & Sound (AREA)
  • Multimedia (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Textile Engineering (AREA)
  • Wood Science & Technology (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
  • Laminated Bodies (AREA)
  • Catalysts (AREA)

Abstract

Un élément structurel alvéolaire (12) destiné à un panneau (10) amortissant le bruit, comprend des parois qui forment des surfaces de délimitation pour un réseau d'alvéoles (15) et qui aboutissent à des faces opposées de l'élément. Les parois délimitant les alvéoles (15) rejoignent au moins l'une des faces de l'élément à un angle ou à des angles oblique(s) par rapport à cette face. Le panneau (10) d'amortissement de bruit se compose de l'élément alvéolaire (12), d'une partie en forme d'élément dorsal (11) qui s'étend sur toute la face arrière de l'élément alvéolaire (12) et d'un élément de revêtement (13, 14) qui s'étend sur toute la face avant de l'élément alvéolaire (12). L'élément de revêtement (13, 14) comprend une feuille de revêtement externe (14) composée d'un matériau thermoplastique perméable et poreux. Le panneau est destiné à être utilisé dans un moteur d'avion, au niveau d'une surface sur laquelle passe un écoulement gazeux, et est placé de telle façon que sa face avant constitue la surface sur laquelle passe l'écoulement gazeux.
PCT/GB1992/000118 1991-01-22 1992-01-21 Element structurel alveolaire Ceased WO1992012854A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
JP4503571A JPH06504629A (ja) 1991-01-22 1992-01-21 構造用セル状構成部材
BR9205443A BR9205443A (pt) 1991-01-22 1992-01-21 Componente celular estrutural para uma painel de atenuacao de ruido,painel de atenuacao de ruidos,e,motor de aviao

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB919101395A GB9101395D0 (en) 1991-01-22 1991-01-22 Structural cellular component
GB9101395.3 1991-01-22

Publications (1)

Publication Number Publication Date
WO1992012854A1 true WO1992012854A1 (fr) 1992-08-06

Family

ID=10688828

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB1992/000118 Ceased WO1992012854A1 (fr) 1991-01-22 1992-01-21 Element structurel alveolaire

Country Status (6)

Country Link
EP (1) EP0568573A1 (fr)
JP (1) JPH06504629A (fr)
AU (1) AU1170792A (fr)
CA (1) CA2092410A1 (fr)
GB (2) GB9101395D0 (fr)
WO (1) WO1992012854A1 (fr)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0747285A1 (fr) * 1995-06-09 1996-12-11 AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE, Société Anonyme Panneau sandwich en matériau composite et procédé de fabrication
US5888610A (en) * 1995-06-08 1999-03-30 Aerospatiale Societe Nationale Industrielle Method for producing a panel or the like with structural and acoustic properties and panel obtained by said method
US6187123B1 (en) 1995-03-29 2001-02-13 Aerospatiale Societe Nationale Industrielle Method for producing a lightened SiC sandwich type structure with a honeycomb-shaped core and structure obtained by said method
US7797809B2 (en) 2004-07-27 2010-09-21 United Technologies Corporation Zero acoustic splice fan case liner
FR2951854A1 (fr) * 2009-10-22 2011-04-29 Onera (Off Nat Aerospatiale) Dispositif d'absorption acoustique
WO2014200499A1 (fr) * 2013-06-13 2014-12-18 The Boeing Company Structure de soudage par diffusion/formation superplastique pour atténuation du bruit provenant du débit d'air
WO2016020623A1 (fr) * 2014-08-06 2016-02-11 Aircelle Procédé pour la fabrication d'un panneau à âme alvéolaire
FR3026045A1 (fr) * 2014-09-24 2016-03-25 Faurecia Automotive Ind Procede de fabrication d'une piece composite a base de resine aqueuse et piece composite issue d'un tel procede
WO2016102894A1 (fr) 2014-12-24 2016-06-30 Aircelle Panneau d'atténuation acoustique pour nacelle de turboréacteur
WO2019027664A1 (fr) * 2017-08-04 2019-02-07 Hexcel Corporation Nid d'abeilles acoustique incliné
US10294815B2 (en) 2012-03-01 2019-05-21 The Boeing Company SPF/DB structure for attenuation of noise from air flow
EP3712390A1 (fr) * 2019-03-19 2020-09-23 Rolls-Royce plc Panneau de chemise acoustique et confinement pour un moteur de turbine à gaz
CN114074753A (zh) * 2020-08-19 2022-02-22 中国航发商用航空发动机有限责任公司 蜂窝件及其制造方法、蜂窝装置、声衬和航空发动机
FR3126334A1 (fr) 2021-08-30 2023-03-03 Safran Nacelles Procédé de fabrication d’un panneau acoustique à cavités obliques
FR3126340A1 (fr) 2021-08-30 2023-03-03 Safran Nacelles Panneau acoustique à cavités obliques

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0016149D0 (en) * 2000-06-30 2000-08-23 Short Brothers Plc A noise attenuation panel
JP5808329B2 (ja) * 2009-09-11 2015-11-10 ストラ エンソ リ−ボード アーベーＳｔｏｒａ Ｅｎｓｏ Ｒｅ−Ｂｏａｒｄ Ａｂ ボードを製造する方法
GB2485165A (en) * 2010-11-03 2012-05-09 Timothy John Sweatman A laminated panel for acoustic insulation
US9096316B2 (en) 2012-02-01 2015-08-04 Textron Innovations Inc. Optimized core for a structural assembly
GB201209658D0 (en) 2012-05-31 2012-07-11 Rolls Royce Plc Acoustic panel
US10184398B2 (en) 2013-10-17 2019-01-22 Rohr, Inc. Acoustic structural panel with slanted core
US9650963B2 (en) 2015-01-29 2017-05-16 Rohr, Inc. Acoustic structural panel with herringbone core
US10800117B2 (en) 2015-03-12 2020-10-13 Rohr, Inc. Method of forming an acoustic bond panel with insertable acoustic assemblies
US9656452B2 (en) 2015-03-12 2017-05-23 Rohr, Inc. Method of forming an acoustic bond panel with insertable acoustic assemblies
US9708930B2 (en) 2015-12-09 2017-07-18 Rohr, Inc. Multi-degree of freedom acoustic panel
US10487943B2 (en) 2016-07-12 2019-11-26 United Technologies Corporation Multi-ply seal ring
JP7605620B2 (ja) * 2020-12-01 2024-12-24 株式会社イノアックコーポレーション 吸遮音材

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1347270A (en) * 1970-12-18 1974-02-27 American Cyanamid Co Sound absorbing laminate
US3819007A (en) * 1973-04-27 1974-06-25 Lockheed Aircraft Corp Controllable laminar sound absorptive structure
US3821999A (en) * 1972-09-05 1974-07-02 Mc Donnell Douglas Corp Acoustic liner
GB2019983A (en) * 1978-05-01 1979-11-07 Boeing Co Sound-attenuating panel
US4318453A (en) * 1979-09-17 1982-03-09 Rohr Industries, Inc. Double layer attenuation panel
US4433021A (en) * 1982-09-22 1984-02-21 Rohr Industries, Inc. Sound attenuation sandwich panel including barrier material for corrosion control
FR2660787A1 (fr) * 1990-04-06 1991-10-11 Technologies Speciales Ingenie Ecran anechouide.
EP0352993B1 (fr) * 1988-07-25 1993-09-22 Short Brothers Plc Panneau amortissant le bruit

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3831710A (en) * 1973-01-24 1974-08-27 Lockheed Aircraft Corp Sound absorbing panel
GB1502314A (en) * 1974-04-08 1978-03-01 Lockheed Aircraft Corp Cellular sound absorptive structure

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1347270A (en) * 1970-12-18 1974-02-27 American Cyanamid Co Sound absorbing laminate
US3821999A (en) * 1972-09-05 1974-07-02 Mc Donnell Douglas Corp Acoustic liner
US3819007A (en) * 1973-04-27 1974-06-25 Lockheed Aircraft Corp Controllable laminar sound absorptive structure
GB2019983A (en) * 1978-05-01 1979-11-07 Boeing Co Sound-attenuating panel
US4318453A (en) * 1979-09-17 1982-03-09 Rohr Industries, Inc. Double layer attenuation panel
US4433021A (en) * 1982-09-22 1984-02-21 Rohr Industries, Inc. Sound attenuation sandwich panel including barrier material for corrosion control
EP0352993B1 (fr) * 1988-07-25 1993-09-22 Short Brothers Plc Panneau amortissant le bruit
FR2660787A1 (fr) * 1990-04-06 1991-10-11 Technologies Speciales Ingenie Ecran anechouide.

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6187123B1 (en) 1995-03-29 2001-02-13 Aerospatiale Societe Nationale Industrielle Method for producing a lightened SiC sandwich type structure with a honeycomb-shaped core and structure obtained by said method
US5888610A (en) * 1995-06-08 1999-03-30 Aerospatiale Societe Nationale Industrielle Method for producing a panel or the like with structural and acoustic properties and panel obtained by said method
FR2735093A1 (fr) * 1995-06-09 1996-12-13 Aerospatiale Panneau sandwich en materiau composite et procede de fabrication
US6267838B1 (en) 1995-06-09 2001-07-31 Aerospatiale Societe Nationale Industrielle Sandwich panel made of a composite material and production method
CN1082438C (zh) * 1995-06-09 2002-04-10 国家宇航公司 复合材料夹心板及其生产方法
EP0747285A1 (fr) * 1995-06-09 1996-12-11 AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE, Société Anonyme Panneau sandwich en matériau composite et procédé de fabrication
US7797809B2 (en) 2004-07-27 2010-09-21 United Technologies Corporation Zero acoustic splice fan case liner
FR2951854A1 (fr) * 2009-10-22 2011-04-29 Onera (Off Nat Aerospatiale) Dispositif d'absorption acoustique
WO2011048323A3 (fr) * 2009-10-22 2012-04-05 ONERA (Office National d'Etudes et de Recherches Aérospatiales) Dispositif d'absorption acoustique
US10294815B2 (en) 2012-03-01 2019-05-21 The Boeing Company SPF/DB structure for attenuation of noise from air flow
CN111300912A (zh) * 2013-06-13 2020-06-19 波音公司 整体式超塑成形和扩散结合夹层结构以及推进系统
KR20160020408A (ko) * 2013-06-13 2016-02-23 더 보잉 컴파니 기류로부터의 소음 감쇠를 위한 초소성 성형/확산 접합 구조물
RU2637276C2 (ru) * 2013-06-13 2017-12-01 Зе Боинг Компани Конструкция на основе суперпластического формообразования/диффузного связывания для ослабления шума от потока воздуха
WO2014200499A1 (fr) * 2013-06-13 2014-12-18 The Boeing Company Structure de soudage par diffusion/formation superplastique pour atténuation du bruit provenant du débit d'air
KR102108885B1 (ko) * 2013-06-13 2020-05-12 더 보잉 컴파니 기류로부터의 소음 감쇠를 위한 초소성 성형/확산 접합 구조물
WO2016020623A1 (fr) * 2014-08-06 2016-02-11 Aircelle Procédé pour la fabrication d'un panneau à âme alvéolaire
FR3024708A1 (fr) * 2014-08-06 2016-02-12 Aircelle Sa Panneau a ame alveolaire pour nacelle d’aeronef et procede de fabrication d’un tel panneau
FR3026045A1 (fr) * 2014-09-24 2016-03-25 Faurecia Automotive Ind Procede de fabrication d'une piece composite a base de resine aqueuse et piece composite issue d'un tel procede
WO2016045802A1 (fr) * 2014-09-24 2016-03-31 Faurecia Automotive Industrie Procédé de fabrication d'une pièce composite à base de résine aqueuse et pièce composite issue d'un tel procédé
US10634059B2 (en) 2014-12-24 2020-04-28 Safran Nacelles Acoustic attenuation panel for a turbojet engine nacelle
WO2016102894A1 (fr) 2014-12-24 2016-06-30 Aircelle Panneau d'atténuation acoustique pour nacelle de turboréacteur
FR3031142A1 (fr) * 2014-12-24 2016-07-01 Aircelle Sa Panneau d’attenuation acoustique pour nacelle de turboreacteur
CN110998710A (zh) * 2017-08-04 2020-04-10 赫克赛尔公司 有角声学蜂窝
US10577117B2 (en) 2017-08-04 2020-03-03 Hexcel Corporation Angled acoustic honeycomb
WO2019027664A1 (fr) * 2017-08-04 2019-02-07 Hexcel Corporation Nid d'abeilles acoustique incliné
CN110998710B (zh) * 2017-08-04 2021-03-30 赫克赛尔公司 有角声学蜂窝
EP3712390A1 (fr) * 2019-03-19 2020-09-23 Rolls-Royce plc Panneau de chemise acoustique et confinement pour un moteur de turbine à gaz
CN114074753A (zh) * 2020-08-19 2022-02-22 中国航发商用航空发动机有限责任公司 蜂窝件及其制造方法、蜂窝装置、声衬和航空发动机
FR3126334A1 (fr) 2021-08-30 2023-03-03 Safran Nacelles Procédé de fabrication d’un panneau acoustique à cavités obliques
FR3126340A1 (fr) 2021-08-30 2023-03-03 Safran Nacelles Panneau acoustique à cavités obliques
WO2023031540A1 (fr) 2021-08-30 2023-03-09 Safran Nacelles Panneau acoustique à cavités obliques
WO2023031550A1 (fr) 2021-08-30 2023-03-09 Safran Nacelles Procédé de fabrication d'un panneau acoustique a cavités obliques
CN117897270A (zh) * 2021-08-30 2024-04-16 赛峰短舱公司 具有倾斜腔体的隔音板

Also Published As

Publication number Publication date
GB2252075A (en) 1992-07-29
GB2252075B (en) 1994-10-19
AU1170792A (en) 1992-08-27
EP0568573A1 (fr) 1993-11-10
CA2092410A1 (fr) 1992-07-23
GB9201243D0 (en) 1992-03-11
GB9101395D0 (en) 1991-03-06
JPH06504629A (ja) 1994-05-26

Similar Documents

Publication Publication Date Title
EP0352993B1 (fr) Panneau amortissant le bruit
US5414232A (en) Noise attenuation panel
WO1992012854A1 (fr) Element structurel alveolaire
EP0489894B1 (fr) Element de construction composite
GB2252076A (en) Noise attenuation panel
US4433021A (en) Sound attenuation sandwich panel including barrier material for corrosion control
EP0509166B1 (fr) Structure en nid d'abeilles pour l'atténuation du bruit
US6840349B2 (en) Multi-component acoustically resistive layer for acoustical attenuation panel and panel thus obtained
US20020157764A1 (en) Method for making a sound reducing panel with resistive layer having structural property and resulting panel
WO1992022053A1 (fr) Panneau attenuant le bruit
WO1992013339A1 (fr) Panneau d'amortissement de bruit
Schmitz et al. Boundary layer control device for duct silencers

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AU BR CA JP US

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): AT BE CH DE DK ES FR GB GR IT LU MC NL SE

DFPE Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101)
WWE Wipo information: entry into national phase

Ref document number: 1992903277

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 2092410

Country of ref document: CA

WWP Wipo information: published in national office

Ref document number: 1992903277

Country of ref document: EP

WWW Wipo information: withdrawn in national office

Ref document number: 1992903277

Country of ref document: EP