GB1577771A - Resilient heat-resistant laminated composite - Google Patents
Resilient heat-resistant laminated composite Download PDFInfo
- Publication number
- GB1577771A GB1577771A GB17033/77A GB1703377A GB1577771A GB 1577771 A GB1577771 A GB 1577771A GB 17033/77 A GB17033/77 A GB 17033/77A GB 1703377 A GB1703377 A GB 1703377A GB 1577771 A GB1577771 A GB 1577771A
- Authority
- GB
- United Kingdom
- Prior art keywords
- composite
- silicone rubber
- assembly
- cloth
- layers
- 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.)
- Expired
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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
- B32B19/00—Layered products comprising a layer of natural mineral fibres or particles, e.g. asbestos, mica
- B32B19/06—Layered products comprising a layer of natural mineral fibres or particles, e.g. asbestos, mica 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
- 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
- B32B9/047—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 made of fibres or filaments
-
- 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
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B30/00—Compositions for artificial stone, not containing binders
- C04B30/02—Compositions for artificial stone, not containing binders containing fibrous materials
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
- C04B37/003—Joining burned ceramic articles with other burned ceramic articles or other articles by heating by means of an interlayer consisting of a combination of materials selected from glass, or ceramic material with metals, metal oxides or metal salts
- C04B37/005—Joining burned ceramic articles with other burned ceramic articles or other articles by heating by means of an interlayer consisting of a combination of materials selected from glass, or ceramic material with metals, metal oxides or metal salts consisting of glass or ceramic 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
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
-
- 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
- B32B2315/00—Other materials containing non-metallic inorganic compounds not provided for in groups B32B2311/00 - B32B2313/04
- B32B2315/02—Ceramics
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/48—Organic compounds becoming part of a ceramic after heat treatment, e.g. carbonising phenol resins
- C04B2235/483—Si-containing organic compounds, e.g. silicone resins, (poly)silanes, (poly)siloxanes or (poly)silazanes
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5248—Carbon, e.g. graphite
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5252—Fibers having a specific pre-form
- C04B2235/5256—Two-dimensional, e.g. woven structures
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/04—Ceramic interlayers
- C04B2237/08—Non-oxidic interlayers
- C04B2237/086—Carbon interlayers
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/04—Ceramic interlayers
- C04B2237/09—Ceramic interlayers wherein the active component for bonding is not the largest fraction of the interlayer
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
- C04B2237/32—Ceramic
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/50—Processing aspects relating to ceramic laminates or to the joining of ceramic articles with other articles by heating
- C04B2237/58—Forming a gradient in composition or in properties across the laminate or the joined articles
- C04B2237/586—Forming a gradient in composition or in properties across the laminate or the joined articles by joining layers or articles of the same composition but having different densities
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/50—Processing aspects relating to ceramic laminates or to the joining of ceramic articles with other articles by heating
- C04B2237/70—Forming laminates or joined articles comprising layers of a specific, unusual thickness
- C04B2237/708—Forming laminates or joined articles comprising layers of a specific, unusual thickness of one or more of the interlayers
Description
(54) RESILIENT HEAT-RESISTANT LAMINATED COMPOSITE
(71) We, COORS PORCELAIN COMPANY, a Corporation of Colorado, United States of America, of 600 Ninth Street, Golden,
Colorado 80401, United States of America, do hereby declare the invention, for which we pray that a patent may be granted to us, and the method by which it is to be performed, to be particularly described in and by the following statement:- The subject matter of the present invention is a resilient heat-resistant composite. The composite has particular utility for bonding together ceramic or other refractory components to form assemblies which in operation undergo thermal expansion or thermal cycling, and hence the invention will be described chiefly in connection therewith.
There is frequently requirement for an assembly of ceramic or other refractory components which are bonded to each other and which assembly during its operation is subjected to thermal cycling or other thermal conditions resulting in different thermal expansions of the bonded components. The different thermal expansions can occur either because the components are of materials having different coefficients of thermal expansion or because the components, even though of the same material, are exposed to different temperatures. But irrespective of the reason for the differences in thermal expansion between the components, unless the bond between the components is resilient there is hazard that one or both of the components will fracture because of the resulting stresses.Hence, there is need for a resilient material which has high temperature resistance and which can be used to bond the component together to form such an assembly.
Silicone rubber has relatively high temperature resistance as compared with other organic resilient or rubberlike materials; however, even silicone rubber cannot be used for protracted periods at temperatures in excess of about 450"F without loss of its resiliency.
Briefly, what we have discovered is that by forming a laminated composite of layers of fibrous graphite bonded together by silicone rubber, the useful temperature can be extended to at least 600"F. That is, the resulting composite of the layers of fibrous graphite bonded by the silicone rubber can be used for protracted periods at 600"F, and at even higher temperatures for shorter periods and yet with the composite retaining its resiliency. In the preferred embodiments the composite of the present invention contains at least 60% by volume of the fibrous graphite, and the layers of the fibrous graphite are woven graphite cloth.
Further according to the present invention there is provided an assembly comprising two members, for example of ceramic, bonded together by a composite as described in the immediately preceding paragraph.
Other features and advantages of the invention will appear more clearly from the following detailed description thereof made, by way of example, with reference to the accompanying drawings in which:
FIGURE 1 is a sectional fragmentary view of an assembly incorporating the heat resistant resilient composite of the present invention; and
FIGURE 2 is an enlarged sectional and fragmentary view of the assembly shown in
FIGURE 1.
Referring now to FIGURE 1, the assembly shown comprises a cellular ceramic body 2 bonded to a dense ceramic member 4 by resilient material 6. The particular assembly of which a portion is shown in FIGURE 1 is used as a heat exchanger, the passages 8 of the cellular body 2 being for the passage of hot gases therethrough. The ceramic member 4 functions as a solid strong periphery or rim for the cellular body. During operation of the assembly the thermal expansion of the ceramic member 4 differs from that of the cellular ceramic body 2 because of the difference in the temperatures to which the two components are exposed and also because in some cases the ceramic of which the member 4 is formed might be different from that used for the cellular ceramic body 2 and hence have
a different coefficient of thermal expansion.
In accordance with the invention the
material used for the layer 6 which bonds
cellular ceramic body 2 to the ceramic -member 4 is a laminate of layers of fibrous
graphite bonded together by silicone rubber,
the fibrous graphite preferably constituting
from 60% to 90% by volume of the composite
and preferably being present in the form of
graphite cloth. The fibrous graphite can be of
matted or felted construction, i.e. cloth with
the fibers in random orientation; but it is
preferable that the cloth used be of woven construction, i.e. a construction wherein the cloth is formed of threads or yarns consisting
of twisted bundles of the graphite fibers and with the threads being in a predetermined interlocked relationship with each other as is characteristic of woven cloths or fabrics.
Referring now to FIGURE 2, the layer 6 contains four layers of silicone rubber-coated
woven graphite cloth which are bonded
together, the cloth layers being shown at 10,
12, 14 and 16 and the silicone rubber coatings
for these layers being shown at 18a, 18b, 18c
and 18drespectively. The cloth shown is, and
should preferably be, of plain weave, and it is
desirable that the cloth have a relatively
open weave. In the particular construction
illustrated the graphite cloth used was one
marketed by the Carborundum Company of
Niagara Falls, New York under the designa
tion GSGC-2 graphite cloth and the silicone rubber used was one marketed by Dow
Corning Company of Midland, Michigan under the designation RTV-106.Further, in the particular embodiment illustrated the graphite cloth constituted about 80% by volume of the laminated composite 6, the silicone rubber constituting the remaining 20% by volume. It is in all cases preferred that the
graphite fiber, e.g. the woven graphite cloth
in the preferred embodiments, constitute from 60% to 90% by volume of the composite
material and the silicone rubber from 10%
to 40% by volume. This range is preferred
because it provides the optimum heat
resistance attainable with the two materials
while yet providing sufficient resilience.
The cloth used in the particular embodi
ment shown in FIGURE 2 had a weight of
about 7.5 ounces per square yard and a thickness of about 17-5 mils. To attain the
optimum combination of desired characteristics it is preferred that the graphite cloth used have a thickness of from 15 to 20 mils and that from four to six layers of the cloth be used in each 1/8" thickness of the laminated composite.
Any of the various silicone rubbers (i.e.
elastomeric organosiloxane polymers) avail
able on the market can be used in the practice
of the invention, the precise molecular
structure or substituted organic radical of
the silicone rubber being of no importance so long as the silicone "rubber" is just thatelastomeric. The important point concerning the invention is that by way of the laminated structure of fibrous graphite layers bonded together by the silicone rubber coatings, the useful temperature range for the successful employment of silicone rubber to provide resiliency can be extended upwardly by about 1500F. Hence, where the silicone rubber is one which is prescribed by its manufacturer only for applications where it will not be exposed for extended periods'to temperatures above 4500 F, by the practice of the present invention that silicone rubber can be used in applications where resiliency is required and where the temperature will, for protracted periods, be as high as 600"F. While there is no certainty as to the reasons which would explain the results, it is believed that because of the particular resiliency characteristics of graphite cloth, even after prolonged exposure to high temperature, the graphite cloth complements the silicone rubber, and the silicone rubber complements the graphite cloth, in the composite to the end that any loss in the resiliency of the silicone rubber after protracted exposure to high temperatures is compensated for by the resiliency characteristics of the graphite cloth.
The structure of the composite material will still better be understood from the following description of a method for its manufacture.
The uncured silicone rubber to be used is dissolved in sufficient solvent to provide a paste-like consistency. Typical of suitable solvents for the silicone rubbers are pentane and methyl ethyl ketone. Such formation of the silicone rubber in the solvent is coated onto the graphite cloth, as by means of a doctor blade, so as to coat the surfaces of the cloth with the paste-like formulation. It is preferred that the silicone rubber-solvent formulation not be worked into the interstices of the cloth so as to completely fill same but rather that at least some inner portion or portions of the total thickness of the cloth be left void of the silicone rubber. The solvent is then evaporated and the silicone rubber cured at such temperature as is specified or recommended by the manufacturer of the silicone rubber for the curing thereof. The amount of the silicone rubber applied should preferably be such as to result in just a thin layer of the silicone rubber over the top and bottom surfaces of the cloth.
The resulting composite sheet, consisting of the graphite cloth coated on both sides with the silicone rubber, is cut into pieces of the desired shape. The surfaces of a number of these pieces are then coated with a very thin layer of the silicone rubber-solvent formulation. For this formulation more solvent can be included such as to provide a lesser viscosity and hence easier attainment of only a very thin layer. After most of the solvent has evaporated the pieces are then stacked one on top of the other until the desired number of laminations is attained and then pressure is applied sufficient to provide a bond between adjacent layers and the resulting laminated composite is then cured at the curing temperature of the silicone rubber.
For use of the resulting composite material in bonding together ceramic or other components to form an assembly, the top and bottom surfaces of the composite material are provided with a very thin layer of the silicone rubber-solvent formulation and the composite material is then pressed between the surfaces of the components desired to be bonded together and the assembly is then complete upon the application of the temperature required for the curing of the thin layers of silicone rubber in contact with the surfaces of the components.
While the invention has been described specifically with reference to use of the composite material as a bonding layer between ceramic or other components of an assembly, it will be understood that the composite material of the present invention has numerous other uses-uses wherever there is requirement for a material having resiliency and a high temperature resistance.
As indicated above, a key point of the present invention is that it enables the use of silicone rubber in applications where resiliency is required and where the temperatures will be above those to which the silicone rubber can be exposed without losing resiliency and other properties. This, then, qualifies silicone rubber for many applications where silicone rubber would not otherwise be qualified.
Hence, it will be understood that while the invention has been described particularly with reference to preferred embodiments and with reference to a particular use thereof various changes and modifications may be made within the scope of the claims which follow.
As previously mentioned the resilient heat resistant laminated composite may be formed with voids within its volume. However, where a percentage volume of the composite is referred to herein, it is hereby stated that the percentage volume of the solid content of the composite is intended.
WHAT WE CLAIM IS:- 1. A resilient heat resistant laminated composite consisting essentially of a plurality of layers of fibrous graphite bonded together by silicone rubber.
2. A composite as claimed in claim 1 and wherein said layers of fibrous graphite are woven graphite cloth.
3. A composite as claimed in claim 2 wherein said cloth has a thickness of from 15 to 20 mils and wherein there are from four to six layers of said cloth in each one-eighthinch thickness of said composite.
4. A composite as claimed in any one of claims 1 to 3 and containing from 60% to 90% by volume of said fibrous graphite and from 10% to 40% by volume of said silicone rubber.
5. A composite substantially as herein described with reference to the accompanying drawings.
6. An assembly comprising two members bonded together by a resilient heat resistant laminated composite as claimed in any one of the preceding claims.
7. An assembly as claimed in claim 6 wherein said members are ceramic.
8. An assembly substantially as herein described with reference to the accompanying drawings.
**WARNING** end of DESC field may overlap start of CLMS **.
Claims (8)
1. A resilient heat resistant laminated composite consisting essentially of a plurality of layers of fibrous graphite bonded together by silicone rubber.
2. A composite as claimed in claim 1 and wherein said layers of fibrous graphite are woven graphite cloth.
3. A composite as claimed in claim 2 wherein said cloth has a thickness of from 15 to 20 mils and wherein there are from four to six layers of said cloth in each one-eighthinch thickness of said composite.
4. A composite as claimed in any one of claims 1 to 3 and containing from 60% to 90% by volume of said fibrous graphite and from 10% to 40% by volume of said silicone rubber.
5. A composite substantially as herein described with reference to the accompanying drawings.
6. An assembly comprising two members bonded together by a resilient heat resistant laminated composite as claimed in any one of the preceding claims.
7. An assembly as claimed in claim 6 wherein said members are ceramic.
8. An assembly substantially as herein described with reference to the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB17033/77A GB1577771A (en) | 1977-04-25 | 1977-04-25 | Resilient heat-resistant laminated composite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB17033/77A GB1577771A (en) | 1977-04-25 | 1977-04-25 | Resilient heat-resistant laminated composite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1577771A true GB1577771A (en) | 1980-10-29 |
Family
ID=10088042
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB17033/77A Expired GB1577771A (en) | 1977-04-25 | 1977-04-25 | Resilient heat-resistant laminated composite |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1577771A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2208625A (en) * | 1987-08-11 | 1989-04-12 | Tba Industrial Products Ltd | Piledriver pads |
| FR2666048A1 (en) * | 1990-08-21 | 1992-02-28 | Aerospatiale | SHEET MATERIAL FOR THE PRODUCTION OF THERMAL SCREENS WITH HIGH PERFORMANCE AND THERMAL SCREENS THEREFORE. |
| US5292575A (en) * | 1990-08-21 | 1994-03-08 | Aerospatiale Societe Nationale Industrielle | Sheet material for constructing high performance thermal screens |
| WO2009019195A1 (en) * | 2007-08-08 | 2009-02-12 | Sgl Carbon Ag | Layered material |
-
1977
- 1977-04-25 GB GB17033/77A patent/GB1577771A/en not_active Expired
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2208625A (en) * | 1987-08-11 | 1989-04-12 | Tba Industrial Products Ltd | Piledriver pads |
| FR2666048A1 (en) * | 1990-08-21 | 1992-02-28 | Aerospatiale | SHEET MATERIAL FOR THE PRODUCTION OF THERMAL SCREENS WITH HIGH PERFORMANCE AND THERMAL SCREENS THEREFORE. |
| EP0473487A1 (en) * | 1990-08-21 | 1992-03-04 | AEROSPATIALE Société Nationale Industrielle | High performance heat screens |
| US5292575A (en) * | 1990-08-21 | 1994-03-08 | Aerospatiale Societe Nationale Industrielle | Sheet material for constructing high performance thermal screens |
| WO2009019195A1 (en) * | 2007-08-08 | 2009-02-12 | Sgl Carbon Ag | Layered material |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed [section 19, patents act 1949] | ||
| PCNP | Patent ceased through non-payment of renewal fee |