CA2637499C - Iron-nickel-cobalt alloy - Google Patents
Iron-nickel-cobalt alloy Download PDFInfo
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- CA2637499C CA2637499C CA2637499A CA2637499A CA2637499C CA 2637499 C CA2637499 C CA 2637499C CA 2637499 A CA2637499 A CA 2637499A CA 2637499 A CA2637499 A CA 2637499A CA 2637499 C CA2637499 C CA 2637499C
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- iron
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- 229910000531 Co alloy Inorganic materials 0.000 title claims abstract description 8
- KGWWEXORQXHJJQ-UHFFFAOYSA-N [Fe].[Co].[Ni] Chemical compound [Fe].[Co].[Ni] KGWWEXORQXHJJQ-UHFFFAOYSA-N 0.000 title claims abstract description 8
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 26
- 239000000956 alloy Substances 0.000 claims abstract description 26
- 238000004519 manufacturing process Methods 0.000 claims abstract description 8
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 7
- 239000000470 constituent Substances 0.000 claims abstract description 6
- 229910052748 manganese Inorganic materials 0.000 claims abstract description 6
- 239000000463 material Substances 0.000 claims description 9
- 229910052802 copper Inorganic materials 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 4
- 239000000126 substance Substances 0.000 claims description 4
- 229910052717 sulfur Inorganic materials 0.000 claims description 4
- 229910052726 zirconium Inorganic materials 0.000 claims description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 239000003733 fiber-reinforced composite Substances 0.000 claims description 3
- 229910052750 molybdenum Inorganic materials 0.000 claims description 3
- 229910052757 nitrogen Inorganic materials 0.000 claims description 3
- 229910052698 phosphorus Inorganic materials 0.000 claims description 3
- 229910052758 niobium Inorganic materials 0.000 claims description 2
- 239000011265 semifinished product Substances 0.000 claims description 2
- 238000003466 welding Methods 0.000 claims description 2
- 229910052804 chromium Inorganic materials 0.000 claims 1
- 229910052760 oxygen Inorganic materials 0.000 claims 1
- 238000010276 construction Methods 0.000 abstract description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 9
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 7
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 239000004753 textile Substances 0.000 description 1
- 238000001721 transfer moulding Methods 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/08—Ferrous alloys, e.g. steel alloys containing nickel
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/10—Ferrous alloys, e.g. steel alloys containing cobalt
- C22C38/105—Ferrous alloys, e.g. steel alloys containing cobalt containing Co and Ni
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/02—Ferrous alloys, e.g. steel alloys containing silicon
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/04—Ferrous alloys, e.g. steel alloys containing manganese
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/06—Ferrous alloys, e.g. steel alloys containing aluminium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/10—Ferrous alloys, e.g. steel alloys containing cobalt
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/12—Ferrous alloys, e.g. steel alloys containing tungsten, tantalum, molybdenum, vanadium, or niobium
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
- Heat Treatment Of Steel (AREA)
- Heat Treatment Of Sheet Steel (AREA)
- Sealing Battery Cases Or Jackets (AREA)
- Production Of Liquid Hydrocarbon Mixture For Refining Petroleum (AREA)
Abstract
Use of an iron-nickel-cobalt alloy in CFC mould construction comprising (in % by mass) Ni from 30 to 35%, Co from 3 to 6%, Al from 0.001 to 0.1%, Mn from 0.005 to 0.5%, Si from 0.005 to 0.5%, C max. 0.1%, balance Fe and constituents resulting from production, with the alloy having a mean coefficient of thermal expansion in the temperature range from 20 to 200°C of < 2.0 x 10 -6/K.
Description
Iron-Nickel-Cobalt Alloy The invention relates to the use of an iron-nickel-cobalt alloy.
Increasingly, components are being produced from carbon fiber-reinforced composites (CFC), even those for products with safety considerations, such as in aircraft manufacture. For producing such components, implements (molds) are needed in which the viscous resin-carbon fiber layer is cured at a temperature of approx. 180 C. In the so-called RTM
(resin transfer molding) process, carbon fiber textiles are added to the mold, the mold is evacuated, and then the resin is injected into the mold. After curing at approx. 180 C, the component is removed from the implement. Materials used for these molds are either C steels or an alloy with a low coefficient of expansion (iron with 36% nickel, Ni36) that typically has a mean'thermal expansion coefficient between 1.6 and 2.5 x 10-6 K-'.
The use of these RTM molds is associated with difficulties and significant complexity because after it is cured the component is difficult to release from the mold and in addition the component must undergo complex subsequent processing so that it can satisfy its functional demands.
The invention provides an alloy for these molds, with which alloy the aforesaid difficulties can be overcome or at least mitigated simply.
This is attained by using an iron-nickel-cobalt alloy in the CFC mold having (in % by weight):
Ni 30 to 35%
Co 3 to 6%
Al 0.001 to 0.1%
Mn 0.005 to0.5%
Si 0.005 to 0.5%
C Max. 0.1%
remainder Fe and constituents resulting from the production process, the alloy having a mean thermal expansion coefficient of < 2.0 x 10-6/K in the temperature range from 20 to 200 C.
Depending on the application area, the Ni content can be adjusted ranging from 32 to 34.5%, where needed even 32.5 to 33.5%.
One preferred alloy is distinguished by the following composition (in % by weight):
Ni 32.5 to 34.5%
Co >3.0to5.5%
Al 0.001 to 0.5%
Mn 0,005 to 0.1 %
Si 0.005 to 0.1%
C 0.005 to 0.05%
remainder Fe and constituents resulting from the production process, the alloy having a mean thermal expansion coefficient of < 1.5 x 10-6/K in the temperature range from 20 to 200 C.
The following elements with the given maximum contents can advantageously be provided for accompanying elements in the alloy to be used:
Cr maxØ1%
MO max. 0, 1%
Cu max. 0.1 %
Ti max. 0.1 %
Mg max. 0.005%
B max. 0.005%
Increasingly, components are being produced from carbon fiber-reinforced composites (CFC), even those for products with safety considerations, such as in aircraft manufacture. For producing such components, implements (molds) are needed in which the viscous resin-carbon fiber layer is cured at a temperature of approx. 180 C. In the so-called RTM
(resin transfer molding) process, carbon fiber textiles are added to the mold, the mold is evacuated, and then the resin is injected into the mold. After curing at approx. 180 C, the component is removed from the implement. Materials used for these molds are either C steels or an alloy with a low coefficient of expansion (iron with 36% nickel, Ni36) that typically has a mean'thermal expansion coefficient between 1.6 and 2.5 x 10-6 K-'.
The use of these RTM molds is associated with difficulties and significant complexity because after it is cured the component is difficult to release from the mold and in addition the component must undergo complex subsequent processing so that it can satisfy its functional demands.
The invention provides an alloy for these molds, with which alloy the aforesaid difficulties can be overcome or at least mitigated simply.
This is attained by using an iron-nickel-cobalt alloy in the CFC mold having (in % by weight):
Ni 30 to 35%
Co 3 to 6%
Al 0.001 to 0.1%
Mn 0.005 to0.5%
Si 0.005 to 0.5%
C Max. 0.1%
remainder Fe and constituents resulting from the production process, the alloy having a mean thermal expansion coefficient of < 2.0 x 10-6/K in the temperature range from 20 to 200 C.
Depending on the application area, the Ni content can be adjusted ranging from 32 to 34.5%, where needed even 32.5 to 33.5%.
One preferred alloy is distinguished by the following composition (in % by weight):
Ni 32.5 to 34.5%
Co >3.0to5.5%
Al 0.001 to 0.5%
Mn 0,005 to 0.1 %
Si 0.005 to 0.1%
C 0.005 to 0.05%
remainder Fe and constituents resulting from the production process, the alloy having a mean thermal expansion coefficient of < 1.5 x 10-6/K in the temperature range from 20 to 200 C.
The following elements with the given maximum contents can advantageously be provided for accompanying elements in the alloy to be used:
Cr maxØ1%
MO max. 0, 1%
Cu max. 0.1 %
Ti max. 0.1 %
Mg max. 0.005%
B max. 0.005%
2 N max. 0.006%
0 max. 0.003%
S max. 0.005%
P max. 0.008%
Ca max. 0.005%
Zr max. 0.05%
Another alloy that can be used advantageously is distinguished by the following chemical composition (in % by weight):
Ni 32.5 to 33.5%
Co >3.5to<4.5%
Mo max. 0.05%
Cr max. 0.05%
C max. 0.009%
Mn max. 0.04%
Si max. 0.03%
S max. 0.003%
N max. 0.004%
Ti max. 0.01%
Cu max. 0.05%
P max. 0.005%
Al 0.001 to 0.05%
Mg max. 0.0008%
Ca max. 0.0003%
Zr max. 0.03%
0 max. 0.003%
remainder Fe and constituents resulting from the production process, the alloy having a mean thermal expansion coefficient of < 1.3 x 10'6/K in the temperature range from 20 to 200 C.
The alloy may further contain 0.001 to 0.1 weight % Nb.
0 max. 0.003%
S max. 0.005%
P max. 0.008%
Ca max. 0.005%
Zr max. 0.05%
Another alloy that can be used advantageously is distinguished by the following chemical composition (in % by weight):
Ni 32.5 to 33.5%
Co >3.5to<4.5%
Mo max. 0.05%
Cr max. 0.05%
C max. 0.009%
Mn max. 0.04%
Si max. 0.03%
S max. 0.003%
N max. 0.004%
Ti max. 0.01%
Cu max. 0.05%
P max. 0.005%
Al 0.001 to 0.05%
Mg max. 0.0008%
Ca max. 0.0003%
Zr max. 0.03%
0 max. 0.003%
remainder Fe and constituents resulting from the production process, the alloy having a mean thermal expansion coefficient of < 1.3 x 10'6/K in the temperature range from 20 to 200 C.
The alloy may further contain 0.001 to 0.1 weight % Nb.
3 Advantageously, the molds are made as milled parts from heat-formed (forged or rolled) or cast mass material and then annealed. The alloy can also be used in the form of wire material, in particular as an added welding substance when producing the mold. The alloy can also be used in the form of a large-format semi-finished product which is a sheet material, strip material or tube material.
One preferred application for the alloy is found in aircraft manufacture, wherein it is possible to use the alloy as a molded component, in particular for producing CFC fittings using the RTM
technology. Other aircraft components that are also embodied using the light-weight CFC
construction can also be produced with components made of the suggested alloy.
Compared to alloys based on Ni 36 that have been used in the past, components can easily be removed from molds of this alloy, because the thermal shrinkage of the mold is lower after the curing process. Given a suitable design for the mold, the component can be removed such that it can perform its function without subsequent processing.
The simpler removal of the component from the mold will also increase the service life of the mold, because no sharp-edged tools have to be used in order to release the component from the mold.
Table 1 provides examples of chemical compositions for inventive iron-nickel-cobalt alloys (El, E2, E3, E4, E5, E6) compared to other iron-nickel-cobalt alloys (TI, U1) that were investigated.
One preferred application for the alloy is found in aircraft manufacture, wherein it is possible to use the alloy as a molded component, in particular for producing CFC fittings using the RTM
technology. Other aircraft components that are also embodied using the light-weight CFC
construction can also be produced with components made of the suggested alloy.
Compared to alloys based on Ni 36 that have been used in the past, components can easily be removed from molds of this alloy, because the thermal shrinkage of the mold is lower after the curing process. Given a suitable design for the mold, the component can be removed such that it can perform its function without subsequent processing.
The simpler removal of the component from the mold will also increase the service life of the mold, because no sharp-edged tools have to be used in order to release the component from the mold.
Table 1 provides examples of chemical compositions for inventive iron-nickel-cobalt alloys (El, E2, E3, E4, E5, E6) compared to other iron-nickel-cobalt alloys (TI, U1) that were investigated.
4 Element (%) El E2 E3 E4 E5 E6 C 0.002 0.47 0.002 0.008 0.002 0.036 S 0.0023 0.0009 0.0006 0.0015 0.0004 0.0011 N 0.001 0.001 0.001 0.001 Cr 0.02 0.01 <0.01 <0.01 <0.01 0.01 Ni 34.20 34.25 32.75 32.80 32.80 32.55 Mn <0.01 <0.01 <0.01 <0.01 <0.01 <0.01 Si 0.07 <0.01 <0.01 <0.01 <0.01 <0.01 Mo 0.01 0.02 0.01 0.01 0.05 Ti <0.01 <0.01 <0.01 <0.01 <0.01 <0.01 Cu 0.01 <0.01 <0.01 <0.01 <0.01 <0.01 P 0.002 0.002 0.002 0.002 0.002 0.002 Al 0.004 0.007 0.001 0.005 0.005 0.014 Mg 0.0004 0.0003 0.0003 0.0003 0.0002 0.0003 Ca 0.0004 < 0.001 0.0006 0.0006 0.0007 < 0.001 Co 3.1 3.1 3.38 3.9 4.45 4.9 Fe Remainder Remainder Remainder Remainder Remainder Remainder Element (%) Ti U1 C 0.004 0.002 S 0.0008 0.0025 N 0.001 Cr 0.01 0.02 Ni 35.50 34.20 Mn 0.03 < 0.01 Si 0.04 0.11 Mo 0.09 Ti < 0.01 < 0.01 Cu 0.05 0.01 P 0.002 0.003 Al 0.011 0.010 Mg 0.0006 0.0005 Ca 0.0002 0.0003 Co 1.44 2.3 Fe Remainder Remainder Inventive alloys E 1 - E3 and E6 attain thermal expansion coefficients ranging from 1.5 - < 2.0 x 10"6/K in the 20 - 200 C temperature range.
The inventive alloys E4 and E5 attain an even lower expansion coefficient of about 1.3 x 10-6/K
in the 20 to 200 C temperature range so that with the alloys E4 and E5 a combination of increased strength with simultaneously lower thermal expansion is attained.
The inventive alloys E4 and E5 attain an even lower expansion coefficient of about 1.3 x 10-6/K
in the 20 to 200 C temperature range so that with the alloys E4 and E5 a combination of increased strength with simultaneously lower thermal expansion is attained.
Claims (9)
1. Use of an iron-nickel-cobalt alloy in a carbon fiber-reinforced composite (CFC) mold having in % by weight:
Ni 32.5 to 34.5%
Co >3.0 to 5.5%
Al 0.001 to 0.1%
Mn 0.005 to 0.1%
Si 0.005 to 0.1 %
C 0.005 to 0.05%
wherein the alloy contains the following maximum contents of accompanying elements:
Cr max. 0.1 %
Mo max. 0.1%
Cu max. 0.1%
Ti max. 0.1 %
Mg max. 0.005%
B max. 0.005%
N max. 0.006%
O max. 0.003%
S max. 0.005%
P max. 0.008%
Ca max. 0.005%
Zr max. 0.05%
remainder Fe and constituents resulting from the production process, the alloy having a mean thermal expansion coefficient of <1.5 x 10 -6/K
in the temperature range from 20 to 200°C.
Ni 32.5 to 34.5%
Co >3.0 to 5.5%
Al 0.001 to 0.1%
Mn 0.005 to 0.1%
Si 0.005 to 0.1 %
C 0.005 to 0.05%
wherein the alloy contains the following maximum contents of accompanying elements:
Cr max. 0.1 %
Mo max. 0.1%
Cu max. 0.1%
Ti max. 0.1 %
Mg max. 0.005%
B max. 0.005%
N max. 0.006%
O max. 0.003%
S max. 0.005%
P max. 0.008%
Ca max. 0.005%
Zr max. 0.05%
remainder Fe and constituents resulting from the production process, the alloy having a mean thermal expansion coefficient of <1.5 x 10 -6/K
in the temperature range from 20 to 200°C.
2. The use in accordance with claim 1, wherein the alloy has the following composition in % by weight:
Ni 32.5 to 33.5%
Co > 3.5 to < 4.5%
Mo max. 0.05%
Cr max. 0.05%
C max. 0.009%
Mn max. 0.04%
Si max. 0.03%
S max. 0.003%
N max. 0.004%
Ti max. 0.01 %
Cu max. 0.05%
P max. 0.005%
Al 0,001 to 0.05%
Mg max. 0.0008%
Ca max. 0.003%
Zr max. 0.03%
O max. 0.003%
remainder Fe and constituents resulting from the production process, the alloy having a mean thermal expansion coefficient of <1.3 x 10 -6/K
in the temperature range from 20 to 200°C.
Ni 32.5 to 33.5%
Co > 3.5 to < 4.5%
Mo max. 0.05%
Cr max. 0.05%
C max. 0.009%
Mn max. 0.04%
Si max. 0.03%
S max. 0.003%
N max. 0.004%
Ti max. 0.01 %
Cu max. 0.05%
P max. 0.005%
Al 0,001 to 0.05%
Mg max. 0.0008%
Ca max. 0.003%
Zr max. 0.03%
O max. 0.003%
remainder Fe and constituents resulting from the production process, the alloy having a mean thermal expansion coefficient of <1.3 x 10 -6/K
in the temperature range from 20 to 200°C.
:3. The use in accordance with claim 1 or 2, wherein the alloy further contains 0.001 to 0.1 weight % Nb.
4. The use in accordance with any one of claims 1 to 3, for a large-format semi-finished product which is a sheet material, strip material or tube material.
5. The use in accordance with any one of claims 1 to 3, for a wire.
6. The use in accordance with claim 5, wherein the wire is an added welding substance.
7. The use in accordance with any one of claims 1 to 3, for a molded component for producing an aircraft part from a carbon fiber-reinforced composite.
8. The use in accordance with any one of claims 1 to 3, for a forged part.
9. The use in accordance with any one of claims 1 to 3, for a cast component.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102006005252A DE102006005252B4 (en) | 2006-02-02 | 2006-02-02 | Molded part made of an iron-nickel-cobalt alloy |
| DE102006005252.8 | 2006-02-02 | ||
| PCT/DE2007/000142 WO2007087786A1 (en) | 2006-02-02 | 2007-01-26 | Iron-nickel-cobalt alloy |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2637499A1 CA2637499A1 (en) | 2007-08-09 |
| CA2637499C true CA2637499C (en) | 2012-04-17 |
Family
ID=38001632
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2637499A Active CA2637499C (en) | 2006-02-02 | 2007-01-26 | Iron-nickel-cobalt alloy |
Country Status (10)
| Country | Link |
|---|---|
| US (1) | US20100175847A1 (en) |
| EP (1) | EP1979502B1 (en) |
| JP (1) | JP2009525400A (en) |
| CN (1) | CN101379210B (en) |
| AT (1) | AT508430B1 (en) |
| CA (1) | CA2637499C (en) |
| DE (1) | DE102006005252B4 (en) |
| ES (1) | ES2330186B2 (en) |
| GB (1) | GB2447856B (en) |
| WO (1) | WO2007087786A1 (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101474839A (en) * | 2008-12-24 | 2009-07-08 | 西安飞机工业（集团）有限责任公司 | Mold structure for molding composite material |
| CN102575332B (en) * | 2009-06-11 | 2014-05-21 | 福特汽车公司 | Low CTE slush molds with textured surface, and method of making and using the same |
| CN103924153B (en) * | 2014-04-22 | 2016-04-27 | 钢铁研究总院 | A kind of low bulk magnetic shielding Alloy And Preparation Method |
| JP6188643B2 (en) * | 2014-06-30 | 2017-08-30 | 新報国製鉄株式会社 | Extremely low thermal expansion alloy and manufacturing method thereof |
| US10351459B2 (en) * | 2015-08-14 | 2019-07-16 | Corning Incorporated | Molds and methods to control mold surface quality |
| WO2023227929A1 (en) * | 2022-05-27 | 2023-11-30 | Aperam | Alloy for manufacturing tools intended for manufacturing aeronautical parts made of composite material |
Family Cites Families (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1929909A (en) * | 1930-10-04 | 1933-10-10 | Lebanon Steel Foundry | Manufacture of die blocks and the like |
| GB912826A (en) * | 1960-03-23 | 1962-12-12 | British Petroleum Co | Improvements in or relating to the production of isoprene-containing material |
| US4853298A (en) * | 1986-04-08 | 1989-08-01 | Carpenter Technology Corporation | Thermally stable super invar and its named article |
| JPH01306540A (en) * | 1988-05-31 | 1989-12-11 | Shinichi Enomoto | Low thermal expansion alloy iron |
| JPH02298236A (en) * | 1989-05-12 | 1990-12-10 | Shinichi Enomoto | Low thermal expansion alloy |
| DE69920743T2 (en) * | 1998-10-02 | 2005-10-13 | Sumitomo Metal Industries, Ltd. | WELDED STRUCTURE OF ALLOY WITH LOW THERMAL EXPANSION COEFFICIENT AND WELDED MATERIAL |
| JP2001049395A (en) * | 1999-08-11 | 2001-02-20 | Hitachi Metals Ltd | Iron-nickel-cobalt alloy excellent in etching characteristic and low thermal expansion characteristic, and shadow mask excellent in smoothness of inside peripheral shape of etch pit |
| JP2001181796A (en) * | 1999-12-28 | 2001-07-03 | Hitachi Metals Ltd | Fe-Ni-Co ALLOY EXCELLENT IN ETCHING CHARACTERISTIC AND LOW THERMAL EXPANSION CHARACTERISTIC, AND SHADOW MASK EXCELLENT IN ETCHING PIT SHAPE CHARACTERISTIC |
| JP3542024B2 (en) * | 2000-03-17 | 2004-07-14 | 日立金属株式会社 | High strength low thermal expansion Fe-Ni alloy, shadow mask, lead frame |
| US6510601B1 (en) * | 2000-03-20 | 2003-01-28 | The Boeing Company | Invar forming method for making tooling |
| FR2819825B1 (en) * | 2001-01-24 | 2003-10-31 | Imphy Ugine Precision | PROCESS FOR MANUFACTURING A FE-NI ALLOY STRIP |
| ES2205961B2 (en) * | 2001-02-13 | 2005-03-01 | Eads Construcciones Aeronauticas, S.A. | PROCEDURE FOR THE MANUFACTURE OF COMPOSITE MATERIAL ELEMENTS THROUGH THE COENCOLATE TECHNOLOGY. |
| JP2004183000A (en) * | 2002-11-29 | 2004-07-02 | Jfe Steel Kk | Low thermal expansion alloy thin sheet excellent in formability and impact resistance, its production method, and shadow mask using the alloy thin sheet |
| DE10258356B3 (en) * | 2002-12-12 | 2004-05-27 | Thyssenkrupp Vdm Gmbh | Use of an iron-nickel-cobalt alloy for shadow masks and their frames in flat monitors and TV screens |
| DE102005008479B4 (en) * | 2005-02-24 | 2011-07-07 | Airbus Operations GmbH, 21129 | Arrangement and method for producing a component |
-
2006
- 2006-02-02 DE DE102006005252A patent/DE102006005252B4/en not_active Expired - Fee Related
-
2007
- 2007-01-26 EP EP07721865.9A patent/EP1979502B1/en active Active
- 2007-01-26 AT AT0900107A patent/AT508430B1/en active
- 2007-01-26 CA CA2637499A patent/CA2637499C/en active Active
- 2007-01-26 ES ES200850067A patent/ES2330186B2/en not_active Expired - Fee Related
- 2007-01-26 GB GB0813844A patent/GB2447856B/en active Active
- 2007-01-26 CN CN2007800041283A patent/CN101379210B/en active Active
- 2007-01-26 WO PCT/DE2007/000142 patent/WO2007087786A1/en active IP Right Grant
- 2007-01-26 JP JP2008552672A patent/JP2009525400A/en active Pending
- 2007-01-26 US US12/223,131 patent/US20100175847A1/en not_active Abandoned
Also Published As
| Publication number | Publication date |
|---|---|
| EP1979502B1 (en) | 2014-01-22 |
| GB2447856B (en) | 2011-09-07 |
| WO2007087786A8 (en) | 2007-10-11 |
| CN101379210B (en) | 2012-07-04 |
| ES2330186A1 (en) | 2009-12-04 |
| EP1979502A1 (en) | 2008-10-15 |
| JP2009525400A (en) | 2009-07-09 |
| WO2007087786A1 (en) | 2007-08-09 |
| AT508430A5 (en) | 2011-01-15 |
| CA2637499A1 (en) | 2007-08-09 |
| GB2447856A (en) | 2008-10-01 |
| US20100175847A1 (en) | 2010-07-15 |
| CN101379210A (en) | 2009-03-04 |
| DE102006005252A1 (en) | 2007-08-16 |
| ES2330186B2 (en) | 2010-04-19 |
| DE102006005252B4 (en) | 2010-10-28 |
| AT508430B1 (en) | 2011-01-15 |
| GB0813844D0 (en) | 2008-09-03 |
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