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US20100175847A1 - Iron-Nickel-Cobalt Alloy - Google Patents

Iron-Nickel-Cobalt Alloy Download PDF

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Publication number
US20100175847A1
US20100175847A1 US12/223,131 US22313107A US2010175847A1 US 20100175847 A1 US20100175847 A1 US 20100175847A1 US 22313107 A US22313107 A US 22313107A US 2010175847 A1 US2010175847 A1 US 2010175847A1
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US
United States
Prior art keywords
max
alloy
mold
accordance
weight
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.)
Abandoned
Application number
US12/223,131
Inventor
Bodo Gehrmann
Bernd Boer
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.)
VDM Metals GmbH
Original Assignee
ThyssenKrupp VDM GmbH
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 ThyssenKrupp VDM GmbH filed Critical ThyssenKrupp VDM GmbH
Assigned to THYSSENKRUPP VDM GMBH reassignment THYSSENKRUPP VDM GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GEHRMANN, BODO, BOER, BERND
Publication of US20100175847A1 publication Critical patent/US20100175847A1/en
Assigned to OUTOKUMPU VDM GMBH reassignment OUTOKUMPU VDM GMBH CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: THYSSENKRUPP VDM GMBH
Abandoned legal-status Critical Current

Links

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

Definitions

  • the invention relates to the use of an iron-nickel-cobalt alloy.
  • CFC carbon fiber-reinforced composites
  • implements 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.
  • RTM resin transfer molding
  • 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 ⁇ 10 ⁇ 6 K ⁇ 1 .
  • RTM molds are 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 underlying object of the invention is therefore to provide an alloy for these molds, with which alloy the aforesaid difficulties can be overcome simply.
  • the alloy having a mean thermal expansion coefficient of ⁇ 2.0 ⁇ 10 ⁇ 6 /K in the temperature range from 20 to 200° C.
  • 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):
  • Another alloy that can be used advantageously is distinguished by the following chemical composition (in % by weight):
  • 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.
  • 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.
  • 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.
  • Table 1 provides examples of chemical compositions for inventive iron-nickel-cobalt alloys (E1, E2, E3, E4, E5, E6) compared to other iron-nickel-cobalt alloys (T1, U1) that were investigated.
  • Inventive alloys E1-E3 and E6 attain thermal expansion coefficients ranging from 1.5- ⁇ 2.0 ⁇ 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 ⁇ 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.

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  • 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 DEG C of <2.0 OE10<−6>/K.

Description

  • 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 2.5×10−6 K−1.
  • 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 underlying object of the invention is therefore to provide an alloy for these molds, with which alloy the aforesaid difficulties can be overcome simply.
  • This object 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 to 0.5%
    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 <2.0×10−6/K in the temperature range from 20 to 200° C.
  • Advantageous refinements of the inventive subject-matter can be found in the subordinate claims.
  • 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 >3.0 to 5.5%
    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 <1.5×10−6/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 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%
  • Another alloy that can be used advantageously is distinguished by the following chemical composition (in % by weight):
  •
    Ni 32.5 to 34.5%
    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. 0.0001%
    Zr max. 0.03%
    O max. 0.006%

    remainder Fe and constituents resulting from the production process, the alloy having a mean thermal expansion coefficient of <1.3×10−6/K in the temperature range from 20 to 200° C.
  • 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.
  • 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 N±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 (E1, E2, E3, E4, E5, E6) compared to other iron-nickel-cobalt alloys (T1, U1) that were investigated.
  • Element (%) E1 E2 E3 E4 E5 E6 T1 U1
    C 0.002 0.47 0.002 0.008 0.002 0.036 0.004 0.002
    S 0.0023 0.0009 0.0006 0.0015 0.0004 0.0011 0.0008 0.0025
    N 0.001 0.001 0.001 0.001 0.001
    Cr 0.02 0.01 <0.01 <0.01 <0.01 0.01 0.01 0.02
    Ni 34.20 34.25 32.75 32.80 32.80 32.55 35.50 34.20
    Mn <0.01 <0.01 <0.01 <0.01 <0.01 <0.01 0.03 <0.01
    Si 0.07 <0.01 <0.01 <0.01 <0.01 <0.01 0.04 0.11
    Mo 0.01 0.02 0.01 0.01 0.05 0.09
    Ti <0.01 <0.01 <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 0.05 0.01
    P 0.002 0.002 0.002 0.002 0.002 0.002 0.002 0.003
    Al 0.004 0.007 0.001 0.005 0.005 0.014 0.011 0.010
    Mg 0.0004 0.0003 0.0003 0.0003 0.0002 0.0003 0.0006 0.0005
    Ca 0.0004 <0.001 0.0006 0.0006 0.0007 <0.001 0.0002 0.0003
    Co 3.1 3.1 3.38 3.9 4.45 4.9 1.44 2.3
    Fe Remainder Remainder Remainder Remainder Remainder Remainder Remainder Remainder
  • Inventive alloys E1-E3 and E6 attain thermal expansion coefficients ranging from 1.5-<2.0×10−6/K in the 20-200° C. temperature range.
  • The inventive alloys E4 and E5 attain an even lower expansion coefficient of about 1.3×10−6/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 (12)

1. A method comprising fabricating a mold from materials comprising an iron-nickel-cobalt alloy and producing an object of carbon-fiber reinforced composite in the mold, the alloy comprising, in % by weight:
Ni 30 to 35% Co 3 to 6% Al 0.001 to 0.1% Mn 0.005 to 0.5% Si 0.005 to 0.5% C max. 0.1%
remainder Fe and impurities, the alloy having a mean thermal expansion coefficient of <2.0×10−6/K in a temperature range from 20 to 200° C.
2. Method in accordance with claim 1, wherein the Ni content of the alloy is 32.0 to 34.5%, in % by weight.
3. Method in accordance with claim 1, wherein the Ni content of the alloy is 32.5 to 33.5%, in % by weight.
4. Method in accordance with claim 1, wherein the alloy comprises in % by weight:
Ni 32.5 to 34.5% Co >3.0 to 5.5% 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 impurities, the alloy having a mean thermal expansion coefficient of <1.5×10−6/K in a temperature range from 20 to 200° C.
5. Method in accordance with claim 1, wherein the alloy comprises the following maximum contents of the following elements, in % by weight:
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%
6. A method, comprising fabricating a mold from materials comprising an iron-nickel-cobalt alloy and producing an object of carbon-fiber reinforced composite in the mold, the alloy comprising, in % by weight:
Ni 32.5 to 34.5% 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. 0.0003% Zr max. 0.05% O max. 0.006%
remainder Fe and impurities, the alloy having a mean thermal expansion coefficient of <1.3×10−6/K in a temperature range from 20 to 200° C.
7. Method in accordance with claim 1 or 4, wherein the alloy further comprises 0.001 to 0.1%, in % by weight, Nb.
8. Method in accordance with claim 1 or 4, wherein the alloy from which the mold is fabricated comprises sheet material, strip material, or tube material.
9. Method in accordance with claim 1 or 4, wherein the alloy from which the mold is fabricated comprises wire and the fabricating of the mold comprises welding with the wire comprised of the alloy.
10. Method in accordance with claim 1 or 4, wherein the object comprises an aircraft part.
11. Method in accordance with claim 1 or 4, wherein the alloy from which the mold is fabricated is in the form of forged stock.
12. Method in accordance with claim 1 or 4, wherein the alloy from which the mold is fabricated is in the form of cast stock.
US12/223,131 2006-02-02 2007-01-26 Iron-Nickel-Cobalt Alloy Abandoned US20100175847A1 (en)

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 (1)

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US20100175847A1 true US20100175847A1 (en) 2010-07-15

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Country Status (10)

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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)

Cited By (2)

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US10435780B2 (en) 2009-06-11 2019-10-08 Genius Solutions Engineering Company Low CTE slush molds with textured surface, and method of making and using the same
WO2023227929A1 (en) * 2022-05-27 2023-11-30 Aperam Alloy for manufacturing tools intended for manufacturing aeronautical parts made of composite material

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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
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
KR20240098517A (en) * 2022-12-21 2024-06-28 주식회사 포스코 Non-coated austenitic steel sheet with improved corrosion resistance in an alkaline environment and method for manufacturing the same
WO2024219358A1 (en) * 2023-04-19 2024-10-24 新報国マテリアル株式会社 Low thermal expansion steel casting product and method for manufacturing same

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10435780B2 (en) 2009-06-11 2019-10-08 Genius Solutions Engineering Company Low CTE slush molds with textured surface, and method of making and using the same
WO2023227929A1 (en) * 2022-05-27 2023-11-30 Aperam Alloy for manufacturing tools intended for manufacturing aeronautical parts made of composite material

Also Published As

Publication number Publication date
GB2447856A (en) 2008-10-01
CN101379210B (en) 2012-07-04
GB2447856B (en) 2011-09-07
CA2637499A1 (en) 2007-08-09
CN101379210A (en) 2009-03-04
JP2009525400A (en) 2009-07-09
GB0813844D0 (en) 2008-09-03
EP1979502A1 (en) 2008-10-15
WO2007087786A8 (en) 2007-10-11
CA2637499C (en) 2012-04-17
DE102006005252A1 (en) 2007-08-16
DE102006005252B4 (en) 2010-10-28
EP1979502B1 (en) 2014-01-22
WO2007087786A1 (en) 2007-08-09
ES2330186A1 (en) 2009-12-04
AT508430B1 (en) 2011-01-15
AT508430A5 (en) 2011-01-15
ES2330186B2 (en) 2010-04-19

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