GB2096535A - Honeycomb panel construction - Google Patents

Honeycomb panel construction Download PDF

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Publication number
GB2096535A
GB2096535A GB8111777A GB8111777A GB2096535A GB 2096535 A GB2096535 A GB 2096535A GB 8111777 A GB8111777 A GB 8111777A GB 8111777 A GB8111777 A GB 8111777A GB 2096535 A GB2096535 A GB 2096535A
Authority
GB
United Kingdom
Prior art keywords
honeycomb
method
perforate
perforate member
honeycomb core
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.)
Granted
Application number
GB8111777A
Other versions
GB2096535B (en
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce 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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB8111777A priority Critical patent/GB2096535B/en
Publication of GB2096535A publication Critical patent/GB2096535A/en
Application granted granted Critical
Publication of GB2096535B publication Critical patent/GB2096535B/en
Application status is Expired legal-status Critical

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form ; Layered products having particular features of form
    • B32B3/10Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form ; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form ; Layered products 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
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form ; Layered products having particular features of form
    • B32B3/26Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form ; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/266Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form ; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/12Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/14Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
    • B32B37/146Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers whereby one or more of the layers is a honeycomb structure
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04Interconnection of layers
    • B32B7/12Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • EFIXED CONSTRUCTIONS
    • E04BUILDING
    • E04CSTRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C2/00Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels
    • E04C2/30Building 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
    • E04C2/34Building 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
    • E04C2/36Building 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
    • E04C2/365Building 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 by honeycomb structures
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B32LAYERED PRODUCTS
    • B32BLAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00Properties of the layers or laminate
    • B32B2307/10Properties of the layers or laminate having particular acoustical properties
    • B32B2307/102Insulating

Abstract

A method of bonding a honeycomb panel to a perforate member comprises placing thermo-plastic adhesive film upon one face of either the perforate or the honeycomb, blowing heated air at the adhesive film to puncture it and remove it from the apertures or perforations, and thereafter locating the honeycomb panel and the perforate member together and subjecting them to further heating such that they become bonded together.

Description

SPECIFICATION Honeycomb panel construction This invention relates to a honeycomb panel construction and in particular to an acoustic honeycomb panel suitable for use within a gas turbine engine.

It is at present well known to use honeycomb panels for the purpose of absorbing noise within the ducts of gas turbine engines. Such panels usually consist of a honeycomb material sandwiched between either one perforate layer and one inperforate layer, or alternatively both the layers may be perforated for particular applications.

The usual method of making such a panel is to place a film of reticulate thermo-setting resin upon the honeycomb and thereafter puncturing the resin film within each honeycomb cell. The assembly is then heated such that the resin shrinks back and forms a bead upon the edges of the honeycomb and the perforate layer is then placed upon the honeycomb further heat and pressure is thus provided such that the leads of resin secure the two members together.

It will be appreciated that puncturing of the resin film after application overthe honeycomb is both time consuming and monotonous particularly in view of the fact that this must be carried out manually due to varying cell distortion within the honeycomb. Furthermore some of the perforations within the perforate sheet become blocked with resin when the sheet is secured to the honeycomb and this can result in reducing the porosity of the component by as much as 25%.

An object of the present invention is to provide a honeycomb panel construction in which the aforementioned disadvantages are substantially eliminated.

According to the present invention a method of securing a honeycomb core to at least one perforate member comprises applying a film of reticular adhesive to either the perforate member or to one side of the honeycomb core, blowing a supply of heated pressurised air through the core or perforate member such that the adhesive film is punctured and displaced from the area defined by either the apertures within either the perforate member or the honeycomb core, and thereafter locating the perforate member and the honeycomb together maintaining them in firm contact with each other and subjecting the assembly to a temperature increase such as to cure the adhesive to secure the perforate member to the honeycomb core.

Preferably the assembled honeycomb and perforate member is subjected to a temperature increase within an oven or furnace to secure them together.

Preferably the perforate member consists of a metallic perforated sheet or alternatively a perforated sheet manufactured from fibre reinforced resin material.

The honeycomb material may be manufactured from a plurality of metallic strips which are either brazed or welded or bonded together.

Alternatively the honeycomb material may consist of a plurality of fibre reinforced resin strips which are bonded together.

Preferably the reticular adhesive comprises a film of thermosetting resin.

Further the honeycomb panel may have a perforate sheet secured to each of its respective sides.

For better understanding thereof an embodiment of the present invention will be more particularly described by way of example only and with reference to the accompanying drawings in which Figure 7 shows a diagramatic side view of a ducted fan type gas turbine engine incorporating a honeycomb panel made in accordance with an embodiment of the present invention.

Figure 2 shows an enlarged pictorial view in greater detail of the view shown diagramatically at Figure 1.

Figure 3 shows a cross-sectional side view of the view shown at Figure 2 including a perforate layer on both sides of the honeycomb.

Referring to the drawings a gas turbine engine shown generally at 10 comprises in flow series a fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, combustion equipment 15, a high pressure turbine 16, an intermediate pressure turbine 17, a low pressure turbine 18, the engine terminating in an exhaust nozzle 19. A cowling 20 is arranged radially outwardly of the fan 12 defining a fan duct and has arranged upon its radially innermost surface adjacent the fan 12 an annulus of honeycomb panels 21 made in accordance with an embodiment of the present invention.

Figure 2 shows a portion of the honeycomb panel in greater detail and includes a perforate member 22 with the honeycomb core 23 secured thereto. The perforate member 22 may consist of a mechanically perforated metallic sheet or alternatively may comprise a composite structure composed of fibres such as for example carbon or glass fibres secured together within a resin matrix. In this case the material may either be perforated mechanically or alternatively the perforations may be moulded into the structure during manufacture.

The honeycomb material 23 may consist of either a plurality of metallic strips which are shaped and secured together by means of brazing, welding or bonding; or alternatively the panel may consist of a plurality of fibre reinforced resin or plastic strips which are bonded together to form the required structure.

To secure the honeycomb core 23 to the perforate member 22 a film of reticulate thermo-setting adhesive is applied to one side of one of either the honeycomb panel 23 orthe perforate member 22.

Such film adhesive is a proprietary product and is manufactured by CIBA and sold under the references BSL 319 and BSL 308.

After the adhesive film has been placed up one side of the honeycomb or perforate a regulated supply of heated air is blown at it. The hot pressurised air softens the adhesive such that it punctures at the perforations or apertures at their centres and the adhesive film shrinks from the vicinity of the perforations and apertures and increases the thick nests of the adhesive or forms a bead of adhesive around the perforations or apertures. In the case of the perforate member it has been found preferable to blow the air onto the opposite side of the perforate to which the film is attached for best results. In the case of the honeycomb core however it has been found preferable to blow the air directly at the film for best results.

The honeycomb panel or perforate member which is still free from adhesive is thereafter placed upon the adhesive layer and the clamped assembly thereafter placed in an oven or furnace to cure the adhesive to ensure that the two members are securely bonded together.

It will be appreciated that the hereinbefore mentioned methods of applying adhesive to the perforate member ensures the maximum possible porosity of the completed panel as none of the perforations or apertures can become blocked with adhesive. It is therefore by use of the method relatively simple to manufacture a honeycomb panel to a desired porosity. This is obviously particularly important if the honeycomb is to be used for sound attenuation purposes for example such as that used within gas turbine engine fan ducts.

Claims (8)

1. A method of securing a honeycomb core to at least one perforate member comprises applying a film of reticular adhesive to either the perforate member or to one side of the honeycomb core, blowing a supply of heated pressurised air through the honeycomb core or perforate member such that the film of reticular adhesive is punctured and displaced from the area defined by either the apertures within the perforate member or honeycomb core, and thereafter locating the perforated member and honeycomb together, maintaining them in firm contact with each other and subjecting the assembly to a temperature increase such as to cure the adhesive to secure the perforate member to the honeycomb core.
2. A method as claimed in claim 1 in which the honeycomb core and perforate member are subjected to a temperature increase within an oven or furnace to secure them together.
3. A method as claimed in claim 1 in which the perforate member consists of a metallic perforated sheet, or alternatively a perforated sheet manufactured from fibre reinforced resin material.
4. A method as claimed in claim 1 in which the honeycomb material is manufactured from a plurality of metallic strips which are either brazed, welded or bonded together.
5. A method as claimed in claim 1 in which the reticular adhesive film comprises a thermo-setting resin.
6. A method as claimed in claim 1 in which the honeycomb core may have a perforate sheet secured to each of its respective sides.
7. A honeycomb panel as claimed in any preced ing claim suitable for use as part of an acoustic liner within a gas turbine engine fan duct.
8. A method of making a honeycomb panel as claimed in claim 1 to 6 and substantially as hereinbefore described by way of example only and as illustrated in the accompanying drawings.
GB8111777A 1981-04-14 1981-04-14 Honeycomb panel construction Expired GB2096535B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB8111777A GB2096535B (en) 1981-04-14 1981-04-14 Honeycomb panel construction

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB8111777A GB2096535B (en) 1981-04-14 1981-04-14 Honeycomb panel construction

Publications (2)

Publication Number Publication Date
GB2096535A true GB2096535A (en) 1982-10-20
GB2096535B GB2096535B (en) 1984-06-13

Family

ID=10521144

Family Applications (1)

Application Number Title Priority Date Filing Date
GB8111777A Expired GB2096535B (en) 1981-04-14 1981-04-14 Honeycomb panel construction

Country Status (1)

Country Link
GB (1) GB2096535B (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0527109A1 (en) 1991-08-05 1993-02-10 Alusuisse-Lonza Services Ag Process for the manufacture of a composite panel with a cellular core and at least one outer layer
EP0824066A1 (en) * 1996-08-14 1998-02-18 Hispano-Suiza Ventilated honeycomb sandwich panel and ventilation method of such a panel
FR2839075A1 (en) * 2002-04-25 2003-10-31 Airbus France Adhesive film for bonding a wall to a honeycomb structure comprises holes in front of the cells of the honeycomb structure
WO2004028804A1 (en) 2002-09-26 2004-04-08 Gkn Westland Aerospace, Inc. Method and apparatus for applying a film adhesive to a perforated panel
EP2321067A1 (en) * 2008-09-05 2011-05-18 Bell Helicopter Textron Inc. Method and apparatus for reticulating an adhesive to the surface network of a cellular core structure
CN104078036A (en) * 2014-06-19 2014-10-01 上海交通大学 Low and medium frequency light thin layer sound insulation and absorption board and combined board thereof
CN104553238A (en) * 2014-12-12 2015-04-29 中航复合材料有限责任公司 Method for reinforcing surface stability of core of honeycomb-like porous structure by hot film blowing and breaking method
RU2596772C1 (en) * 2015-05-05 2016-09-10 Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" Method for formation of fillets of glue on edges of cellular filler cells
WO2019170358A1 (en) * 2018-03-05 2019-09-12 Ruag Schweiz Ag Vented panel

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0527109A1 (en) 1991-08-05 1993-02-10 Alusuisse-Lonza Services Ag Process for the manufacture of a composite panel with a cellular core and at least one outer layer
AU650769B2 (en) * 1991-08-05 1994-06-30 3A Technology & Management Ltd. Process for the production of a composite sheet comprising a cellular core and at least one outer layer
TR27034A (en) * 1991-08-05 1994-10-10 Alusuisse Lonza Services Ag I'm short on cellular and producing at least one layer in a transaction that includes an outer coat on.
US6099683A (en) * 1991-08-05 2000-08-08 Alusuisse Technology & Management Ltd. Process for the production of a composite sheet
EP0824066A1 (en) * 1996-08-14 1998-02-18 Hispano-Suiza Ventilated honeycomb sandwich panel and ventilation method of such a panel
WO1998006563A1 (en) * 1996-08-14 1998-02-19 Hispano Suiza Ventilated honeycombed sandwich construction and method for ventilating same
FR2752392A1 (en) * 1996-08-14 1998-02-20 Hispano Suiza Sa Sandwich ventilated beam panel and method for ventilation of such a panel
US6122892A (en) * 1996-08-14 2000-09-26 Societe Hispano-Suiza Ventilated honeycomb cell sandwich panel and ventilation process for such a panel
US7338696B2 (en) 2002-04-25 2008-03-04 Airbus France Perforated adhesive film and its manufacturing process
EP1382652A1 (en) * 2002-04-25 2004-01-21 Airbus France Perforated adhesive film and process for producing it
FR2839075A1 (en) * 2002-04-25 2003-10-31 Airbus France Adhesive film for bonding a wall to a honeycomb structure comprises holes in front of the cells of the honeycomb structure
EP1542870A1 (en) * 2002-09-26 2005-06-22 GKN Westland Aerospace, Inc. Method and apparatus for applying a film adhesive to a perforated panel
EP1542870A4 (en) * 2002-09-26 2010-04-28 Gkn Westland Aerospace Inc Method and apparatus for applying a film adhesive to a perforated panel
WO2004028804A1 (en) 2002-09-26 2004-04-08 Gkn Westland Aerospace, Inc. Method and apparatus for applying a film adhesive to a perforated panel
EP2321067A1 (en) * 2008-09-05 2011-05-18 Bell Helicopter Textron Inc. Method and apparatus for reticulating an adhesive to the surface network of a cellular core structure
EP2321067A4 (en) * 2008-09-05 2014-06-25 Bell Helicopter Textron Inc Method and apparatus for reticulating an adhesive to the surface network of a cellular core structure
US10040269B2 (en) 2008-09-05 2018-08-07 Textron Innovations Inc. Method and apparatus for reticulating an adhesive to the surface network of a cellular core structure
CN104078036A (en) * 2014-06-19 2014-10-01 上海交通大学 Low and medium frequency light thin layer sound insulation and absorption board and combined board thereof
CN104553238A (en) * 2014-12-12 2015-04-29 中航复合材料有限责任公司 Method for reinforcing surface stability of core of honeycomb-like porous structure by hot film blowing and breaking method
RU2596772C1 (en) * 2015-05-05 2016-09-10 Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" Method for formation of fillets of glue on edges of cellular filler cells
WO2019170358A1 (en) * 2018-03-05 2019-09-12 Ruag Schweiz Ag Vented panel

Also Published As

Publication number Publication date
GB2096535B (en) 1984-06-13

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee