GB2096535A - Honeycomb panel construction - Google Patents
Honeycomb panel construction Download PDFInfo
- 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
- perforate
- honeycomb core
- perforate member
- adhesive
- 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
Links
- 238000010276 construction Methods 0.000 title description 4
- 238000000034 method Methods 0.000 claims abstract description 10
- 239000002313 adhesive film Substances 0.000 claims abstract description 6
- 238000007664 blowing Methods 0.000 claims abstract description 3
- 239000000853 adhesive Substances 0.000 claims description 15
- 230000001070 adhesive effect Effects 0.000 claims description 15
- 239000011347 resin Substances 0.000 claims description 13
- 229920005989 resin Polymers 0.000 claims description 13
- 239000000463 material Substances 0.000 claims description 8
- 239000000835 fiber Substances 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 abstract 1
- 229920001169 thermoplastic Polymers 0.000 abstract 1
- 239000004416 thermosoftening plastic Substances 0.000 abstract 1
- 239000010410 layer Substances 0.000 description 5
- 239000011324 bead Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000012790 adhesive layer Substances 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- 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
- B32B3/26—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 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
- B32B3/266—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 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
-
- 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
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
-
- 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
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/14—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
- B32B37/146—Methods 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
-
- 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
- B32B7/00—Layered 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
- B32B7/04—Interconnection of layers
- B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
-
- 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
- E04C2/365—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 by honeycomb structures
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Laminated Bodies (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
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.
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 (10)
| 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 |
| US11260641B2 (en) | 2019-05-10 | 2022-03-01 | American Honda Motor Co., Inc. | Apparatus for reticulation of adhesive and methods of use thereof |
-
1981
- 1981-04-14 GB GB8111777A patent/GB2096535B/en not_active Expired
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 | A process for producing a layer containing a cellular interior and at least an outer layer. |
| US6099683A (en) * | 1991-08-05 | 2000-08-08 | Alusuisse Technology & Management Ltd. | Process for the production of a composite sheet |
| 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 |
| 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 |
| 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 |
| EP1382652A1 (en) * | 2002-04-25 | 2004-01-21 | Airbus France | Perforated adhesive film and process for producing it |
| WO2004028804A1 (en) | 2002-09-26 | 2004-04-08 | Gkn Westland Aerospace, Inc. | Method and apparatus for applying a film adhesive to a perforated panel |
| 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 |
| 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 |
| US11260641B2 (en) | 2019-05-10 | 2022-03-01 | American Honda Motor Co., Inc. | Apparatus for reticulation of adhesive and methods of use thereof |
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 |