GB2549944A - Heat resistant composite material structure - Google Patents

Heat resistant composite material structure Download PDF

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Publication number
GB2549944A
GB2549944A GB1607656.4A GB201607656A GB2549944A GB 2549944 A GB2549944 A GB 2549944A GB 201607656 A GB201607656 A GB 201607656A GB 2549944 A GB2549944 A GB 2549944A
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GB
United Kingdom
Prior art keywords
composite material
based composite
ceramic
resin
material element
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.)
Withdrawn
Application number
GB1607656.4A
Other versions
GB201607656D0 (en
Inventor
Henry Nicholas
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.)
S S Tube Tech Ltd
Original Assignee
S S Tube Tech Ltd
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 S S Tube Tech Ltd filed Critical S S Tube Tech Ltd
Priority to GB1607656.4A priority Critical patent/GB2549944A/en
Publication of GB201607656D0 publication Critical patent/GB201607656D0/en
Priority to PCT/GB2017/051220 priority patent/WO2017191441A1/en
Publication of GB2549944A publication Critical patent/GB2549944A/en
Withdrawn legal-status Critical Current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
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • 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
    • B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • 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
    • B32B27/28—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42
    • 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 form; Layered products having particular features of form
    • B32B3/02—Layered 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 features of form at particular places, e.g. in edge regions
    • B32B3/04—Layered 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 features of form at particular places, e.g. in edge regions characterised by at least one layer folded at the edge, e.g. over another layer ; characterised by at least one layer enveloping or enclosing a material
    • 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
    • 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
    • B32B7/10—Interconnection of layers at least one layer having inter-reactive 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
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/005—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising one layer of ceramic material, e.g. porcelain, ceramic tile
    • 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
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • 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
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B9/045—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • 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
    • B32B2255/00—Coating on the layer surface
    • 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
    • B32B2255/00—Coating on the layer surface
    • B32B2255/10—Coating on the layer surface on synthetic resin layer or on natural or synthetic rubber 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
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal 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
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/304—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
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/306—Resistant to heat
    • 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
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/544—Torsion strength; Torsion stiffness
    • 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
    • B32B2307/70—Other properties
    • B32B2307/718—Weight, e.g. weight per square meter
    • 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
    • B32B2307/70—Other properties
    • B32B2307/732—Dimensional 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
    • B32B2307/70—Other properties
    • B32B2307/738—Thermoformability
    • 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
    • B32B2315/00—Other materials containing non-metallic inorganic compounds not provided for in groups B32B2311/00 - B32B2313/04
    • B32B2315/02—Ceramics
    • 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
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft

Abstract

A composite structure 10 comprising an element of a ceramic based composite material 12 and an element of a resin based composite material 14, the ceramic serving as a heat shield for the resin. The ceramic may be arranged to shield the connections between the two composite elements and may also be shaped to hold the resin based component. The ceramic may shield the entirety of the resin component or may only shield part of the resin component. The ceramic composite may include finger like structures 18 to extend behind and hold the resin component. The resin and ceramic components may house a heat absorbing core 20. The core may provide thermal protection for points at which the composite materials are joined together. The resin based composite may including mounting fittings. A further layer of material may be included to enhance the thermal properties of the structure. The further layer may comprise a coating or a layer laminated to the rest of the structure.

Description

HEAT RESISTANT COMPOSITE MATERIAL STRUCTURE
This invention relates to a composite material structure, and in particular to a composite material structure of good heat resistant properties.
The use of composite materials in the manufacture of a number of components is becoming widespread, the composite materials typically being of good strength and of relatively low weight, and so lending themselves for use in a wide range of applications. By way of example, carbon or glass fibre reinforced epoxy resin composite materials are in widespread use. Whilst these materials are of good strength and relatively low weight, they suffer from the disadvantage that they are only suitable for use in applications in which the operating temperature is relatively low. At higher temperatures, the resin materials used therein tend to soften with the result that the strength of the material is lost.
Ceramic based composite materials are also known, and have the benefit that they are suitable for use over a much wider range of operating temperatures. They, like epoxy resin based composites, are of low weight. However, it has been found that ceramic based composite materials tend to be relatively brittle, being of low bending strength and elongation under load, and so lack the strength characteristics of many resin based composite materials. Accordingly, the number of applications in which they can be used is relatively low. Furthermore, the nature of ceramic based composite materials is such that mounting components manufactured from such materials can be problematic as drilling into them or otherwise machining them in order to fix mounting brackets or the like thereto often results in damage to the components.
Metallic heat shields are known but are relatively heavy and so it is not preferred to use them in some applications.
It is an object of the invention to provide a composite material structure in which at least some of the disadvantages associated with known composite materials are overcome or are of reduced effect.
According to the present invention there is provided a composite material structure comprising an element of a ceramic based composite material secured to an element of a resin based composite material, the ceramic based composite material element serving as a heat shield, shielding the resin based composite material element from heat produced, in use, from a heat source.
It will be appreciated that, in such an arrangement, the strength benefits associated with the use of a resin based composite material can be maintained, enabling the provision of a structure of good structural rigidity, the presence of the ceramic based composite material shielding the resin based composite material and so avoiding exposure of the resin based composite material to high temperatures despite being used in a high temperature environment. The disadvantages usually associated with resin based composite materials of having a restricted range of operating temperatures are thus overcome.
The ceramic based composite element is preferably arranged to shield the connections between the composite material elements from the heat produced, in use, from the heat source. As a result, a resin based adhesive or the like may be used to secure the composite material elements to one another.
The composite material elements are preferably adapted to, together, house a heat absorbing core. The core may further serve to provide thermal protection for the points at which the elements are secured to one another.
The resin based composite material element may have mounting fittings or the like secured thereto, for example being co-cured therewith or mechanically attached thereto.
An arrangement of the type set out before may be used in the formation of, for example, a heat shield of low weight and good thermal performance, the heat shield also having good strength characteristics.
The invention will further be described, by way of example, with reference to the accompanying drawings, in which:
Figure 1 is a diagram illustrating part of a structure in accordance with one embodiment of the invention; and
Figure 2 is a diagram illustrating part of a structure in accordance with another embodiment of the invention.
Referring firstly to Figure 1, a composite material structure 10 is illustrated. The structure 10 is intended to serve, in use, as a heat shield, providing thermal protection for a device or component 6 against heat output, in use, from a heat source 8. The structure 10 may be used in a wide range of applications in which heat shielding is required, for example protecting engine control components from heat emitted from parts of an engine or exhaust system in automotive applications. However, it will be appreciated that the invention is also suitable for use in other applications, for example in aerospace applications in which there are significant weight constraints.
The structure 10 comprises a ceramic based composite material element 12 and an epoxy resin based composite material element 14. As illustrated, the ceramic based composite material element 12 is of generally channel shaped form, defining a pair of side walls 16, the free edges of which terminate with inwardly extending fingers 18. The fingers 18, in this embodiment, are substantially coplanar. The resin based composite material element 14 is located within the channel defined by the ceramic based composite material element 12, abutting the inner faces of the fingers 18.
Between the ceramic based composite material element 12 and the resin based composite material element 14 is located a core 20 of a heat absorbing, for example microporous, material.
It is envisaged that the resin based composite material element 14 will be secured to the ceramic based composite material element 12 by means of a suitable adhesive, for example a resin based adhesive provided at the interfaces between the resin based composite material element 14 and the fingers 18. Similarly, the core 20 may be secured in position using a suitable adhesive.
In use, as illustrated, the structure 10 is orientated such that the ceramic based composite material element 12 is located closest to the heat source 8, shielding the resin based composite material element 14 from extreme temperatures. As a result, the strength properties associated with the resin based composite material element 14 are not significantly impaired despite the element 14 being used in an environment in which, in the absence of the protection provided by the ceramic based composite material element 12, it would not normally be suitable for use. The heat shielding provided by the ceramic based composite material element 12 further provides protection for the adhesive used to secure the elements 12, 14 to one another, and so the connection therebetween is not negatively impacted despite the structure 10 being used in a high temperature environment.
Both of the elements 12, 14 are of relatively low weight, thus the structure 10 is of low weight. The strength benefits associated with the use of a resin based composite material are maintained, as are the benefits associated with such materials being relatively easy to machine or process and secure to other components, and the ease with which fittings (for example fittings 22) may be attached thereto, for example by being co-cured therewith or subsequently mechanically attached thereto.
It is envisaged that the process by which the structure 10 is manufactured will involve producing the ceramic based composite material element 12 as a standalone component, fabricated and cured independently of the other parts of the structure 10. Once the manufacture thereof has been completed, the core 20 and resin based composite material element 14 may be introduced thereto and secured in position. By completing the manufacture of the ceramic based composite material element 12 as a standalone component, the infiltration processes involved in the manufacture thereof will not result in resin materials used therein being absorbed into the pores of the core 20, which could negatively impact upon its thermal properties.
The structure 10 may be arranged to perform load bearing functions as permitted by the presence of the resin based composite material element 14. Whilst, the entirety of the element 14 may be shielded by the element 12, it is envisaged that in many applications only the part(s) of the element 14 that, in use, would be exposed to unacceptably high temperatures will be provided with the element 12 to provide shielding against such temperatures, for example as shown in Figure 2 described below.
With reference to Figure 2, it will be appreciated that in some arrangements, no core 20 may be required. Furthermore, there may be no need for the element 12 to include fingers 18 extending adjacent a rear face of the element 14. Instead, the element 12 may be adhered or otherwise secured just to part or all of the front face of the element 14. In such an arrangement, the element 12 still provides thermal protection for at least part of the element 14 and for the adhesive or the like located therebetween and used to secure the elements 12, 14 to one another.
In the arrangements described hereinbefore, one or more coatings and/or layers of materials serving to enhance the thermal properties of the structure 10 may be applied, laminated to, or otherwise provided, part or all of the structure 10. By way of example, a coating of a material that serves to enhance thermal radiation from the structure 10 by be applied to at least part thereof.
Whilst specific embodiments of the invention have been described hereinbefore with reference to the accompanying drawings, it will be appreciated that a wide range of modifications and alterations may be made without departing from the scope of the invention as defined by the appended claims. By way of example, the shapes and relative dimensions of the elements 12, 14 and core 20 may differ from those shown and may depend, for example, on the application in which the structure 10 is to be used.

Claims (11)

CLAIMS:
1. A composite material structure comprising an element of a ceramic based composite material secured to an element of a resin based composite material, the ceramic based composite material element serving as a heat shield, shielding the resin based composite material element from heat produced, in use, from a heat source.
2. A structure according to Claim 1, wherein the ceramic based composite element is arranged to shield the connections between the composite material elements from the heat produced, in use, from the heat source.
3. A structure according to Claim 2, wherein the ceramic based composite material element is shaped to hold the resin based composite material element captive thereto.
4. A structure according to any of the preceding claims, wherein the ceramic based composite material element includes fingers shaped to extend behind the resin based composite material element to hold the resin based composite material element to the ceramic based composited material element.
5. A structure according to any of the preceding claims, wherein the composite material elements are adapted to, together, house a heat absorbing core.
6. A structure according to Claim 5, wherein the core serves to provide thermal protection for points at which the composite material elements are secured to one another.
7. A structure according to any of the preceding claims, wherein the resin based composite material element has mounting fittings or the like secured thereto.
8. A structure according to any of the preceding claims, wherein the ceramic based composite material element provides heat shielding to the entirety of the resin based composite material element.
9. A structure according to any of Claims 1 to 7, wherein the ceramic based composite material element provides heat shielding to only part of the resin based composite material element.
10. A structure according to any of the preceding claims, further comprising a layer of a material to enhance the thermal properties of the structure.
11. A structure according to Claim 10, wherein the layer comprises a coating or a layer laminated to at least part of the structure.
GB1607656.4A 2016-05-03 2016-05-03 Heat resistant composite material structure Withdrawn GB2549944A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB1607656.4A GB2549944A (en) 2016-05-03 2016-05-03 Heat resistant composite material structure
PCT/GB2017/051220 WO2017191441A1 (en) 2016-05-03 2017-05-02 Heat resistant composite material structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1607656.4A GB2549944A (en) 2016-05-03 2016-05-03 Heat resistant composite material structure

Publications (2)

Publication Number Publication Date
GB201607656D0 GB201607656D0 (en) 2016-06-15
GB2549944A true GB2549944A (en) 2017-11-08

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Family Applications (1)

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GB1607656.4A Withdrawn GB2549944A (en) 2016-05-03 2016-05-03 Heat resistant composite material structure

Country Status (2)

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GB (1) GB2549944A (en)
WO (1) WO2017191441A1 (en)

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994020432A1 (en) * 1991-04-19 1994-09-15 Allied-Signal Inc. A fiber-reinforced glass composite for protecting polymeric substrates
US6200660B1 (en) * 1996-12-26 2001-03-13 Aerospatiale Societe Nationale Industrielle Device and method for thermal protection of a surface against a thermally and mechanically aggressive environment

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013014037A (en) * 2011-07-01 2013-01-24 Star Hard Kk Foamed plastic composite heat insulation material and production method thereof
KR101583670B1 (en) * 2014-06-12 2016-01-11 (주) 웹스 Thermal diffusion sheet having a flexible layer and a rigid layer of ceramic-carbon composite
KR101603582B1 (en) * 2014-06-12 2016-03-16 (주) 웹스 Thermal diffusion sheet having a flexible layer of ceramic-carbon composite

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994020432A1 (en) * 1991-04-19 1994-09-15 Allied-Signal Inc. A fiber-reinforced glass composite for protecting polymeric substrates
US6200660B1 (en) * 1996-12-26 2001-03-13 Aerospatiale Societe Nationale Industrielle Device and method for thermal protection of a surface against a thermally and mechanically aggressive environment

Also Published As

Publication number Publication date
WO2017191441A1 (en) 2017-11-09
GB201607656D0 (en) 2016-06-15

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