EP0256555A2 - Dispersionsverstärkte Legierungen - Google Patents

Dispersionsverstärkte Legierungen Download PDF

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Publication number
EP0256555A2
EP0256555A2 EP87111982A EP87111982A EP0256555A2 EP 0256555 A2 EP0256555 A2 EP 0256555A2 EP 87111982 A EP87111982 A EP 87111982A EP 87111982 A EP87111982 A EP 87111982A EP 0256555 A2 EP0256555 A2 EP 0256555A2
Authority
EP
European Patent Office
Prior art keywords
alloy
chromium
aluminum
product according
volume
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP87111982A
Other languages
English (en)
French (fr)
Other versions
EP0256555A3 (en
EP0256555B1 (de
Inventor
Raymond Christopher Benn
John Joseph Fischer
Gaylord Darrell Smith
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.)
Huntington Alloys Corp
Original Assignee
Inco Alloys International Inc
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 Inco Alloys International Inc filed Critical Inco Alloys International Inc
Priority to AT87111982T priority Critical patent/ATE81679T1/de
Publication of EP0256555A2 publication Critical patent/EP0256555A2/de
Publication of EP0256555A3 publication Critical patent/EP0256555A3/en
Application granted granted Critical
Publication of EP0256555B1 publication Critical patent/EP0256555B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C33/00—Making ferrous alloys
    • C22C33/02—Making ferrous alloys by powder metallurgy
    • C22C33/0257—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements
    • C22C33/0278—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements with at least one alloying element having a minimum content above 5%
    • C22C33/0292—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements with at least one alloying element having a minimum content above 5% with more than 5% preformed carbides, nitrides or borides
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/10—Alloys containing non-metals
    • C22C1/1084—Alloys containing non-metals by mechanical alloying (blending, milling)
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • C22C32/001—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides
    • C22C32/0015—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides with only single oxides as main non-metallic constituents
    • C22C32/0026—Matrix based on Ni, Co, Cr or alloys thereof

Definitions

  • burner cans in aircraft gas turbine engines of advanced design are currently intended for use at increasingly higher operating temperatures, i.e., about 1250°C (2308°F), and above, e.g., 1300°C (2372°F).
  • industrial applications involving intimate contact with such aggressive corrosives as flue dust, fly ash, molten glass, etc. require more oxidation and/or corrosion-­resistant materials.
  • Kornilov "Aluminum in Iron and Steel” by S.C. Case and K.R. Van Horn, John Wiley and Sons (1953). Kornilov studied the effect of up to 10% aluminum and up to 65% chromium on scaling losses in both cast and wrought Fe-Cr-Al alloys. Aluminum benefited scaling resistance but seemingly there was little benefit conferred by chromium beyond the 25% level at 1100-1400°C. None in the Kornilov investigation involved fabricability of an ODS product or manufacture of sheet.
  • the alloys may also contain up to 5% titanium, up to 2% each of zirconium, hafnium, tantalum and vanadium, up to 6% each of molybdenum and tungsten, up to 0.5% each of silicon and niobium, up to 0.05% each of calcium, yttrium and rare earth metals, up to 0.2% boron and the balance essentially iron plus, to enhance strength, a small but effective amount, e.g., 0.2 volume %, of at least one finely divided dispersoid having a melting point of at least about 1510°C (2750°F) and selected from the group consisting of oxides, nitrides, carbides, borides and other refractory materials. This connection oxides may be present up to about 10 volume % whereas carbides should not exceed about 2 volume %. Nitrides and borides need not exceed 5% by volume.
  • the chromium should not exceed 30% to minimize the formation of deleterious levels to topologically close packed (TCP) phases such as sigma, phases which adversely impact mechanical properties.
  • TCP topologically close packed
  • chromium percentages above about 27%.
  • the percentage of chromium can be extended downward to 20% where less demanding operational parameters are contemplated but at the risk that oxidation resistance will be decreased at a given aluminum level.
  • Aluminum should be from about 5% to 8% for oxidation and corrosion resistance but as indicated, supra, preferably should not exceed 6% when seeking the optimum in terms of fabrication into sheet, strip, etc.
  • Such elements as nickel and cobalt are not required and confer no particular advantage.
  • Carbon need not exceed 0.1% though higher percentages can be tolerated.
  • Our investigation has not shown silicon or boron to be particularly beneficial. Boron is thought to be causative of (or a contributor to) distortion when the sheet product form is heat treated at elevated temperatures. It preferably should not exceed 0.1%.
  • Such constituents as titanium, zirconium, tantalum, niobium, hafnium, zirconium and vanadium need not exceed 1%.
  • Tantalum for example, at the 1% level has resulted in a loss of fabricability. It tends to stiffen the alloys of the invention and possibly raises the ductile-brittle trans-formation temperature too much.
  • a range of titanium from 0.2 or 0.25 to 0.75% is preferred.
  • a series of alloy compositions were prepared using raw material powders namely, elemental (e.g., Fe, Cr, Al), master alloy (e.g., Fe-Cr-Al-Ti) and yttrium bearing oxide (Y2O3) which powders were thereafter blended to produce the chemistries given in Table I.
  • the powder blends were mechanically alloyed (MA) in high energy ball mills under an argon atmosphere for about 24 hours at a ball-to-­powder ratio of about 20:1 using steel balls as the impacting/­grinding media.
  • the MA powders were screened to remove the coarser particles (above about 600 microns), placed in mild steel cans, sealed and hot compacted by extrusion.
  • extrusions were decanned and then hot and cold rolled to 1.25 mm (0.05in) thick sheet, the sheet thereafter being subjected to a final anneal which was typically 1315°C (2400°F) for 1 hour to achieve recrystallization.
  • Figures 1-3 illustrate more graphically what happens by increasing the chromium level of a typical commercial '161 alloy which contained, apart from the different chromium levels, 0.02%C, 4.5%Al, 0.3%Ti, 0.5%Y2O3, incidental impurities, with iron being essentially the balance.
  • the spallation rate mass change
  • the aluminum content should also be increased, preferably proportionately, to reduce the rate of spallation and ensure better integrity of the alloy composition. This is reflected by Figures 4 and 5 where at a 25% Cr level the spallation rate is markedly reduced through the co-presence of an additional 2% of aluminum above the '161 alloy.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Powder Metallurgy (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Colloid Chemistry (AREA)
EP87111982A 1986-08-18 1987-08-18 Dispersionsverstärkte Legierungen Expired - Lifetime EP0256555B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT87111982T ATE81679T1 (de) 1986-08-18 1987-08-18 Dispersionsverstaerkte legierungen.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US89774586A 1986-08-18 1986-08-18
US897745 1986-08-18

Publications (3)

Publication Number Publication Date
EP0256555A2 true EP0256555A2 (de) 1988-02-24
EP0256555A3 EP0256555A3 (en) 1989-02-22
EP0256555B1 EP0256555B1 (de) 1992-10-21

Family

ID=25408352

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87111982A Expired - Lifetime EP0256555B1 (de) 1986-08-18 1987-08-18 Dispersionsverstärkte Legierungen

Country Status (5)

Country Link
EP (1) EP0256555B1 (de)
JP (1) JP2845877B2 (de)
AT (1) ATE81679T1 (de)
AU (1) AU600009B2 (de)
DE (1) DE3782294T2 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2256202A (en) * 1991-04-24 1992-12-02 Inco Alloys Int Controlled grain size for ods iron-base alloys
EP0566254A1 (de) * 1992-03-26 1993-10-20 British Ceramic Service Company Limited Förderbandofen
EP0735148A1 (de) * 1995-03-25 1996-10-02 PLANSEE Aktiengesellschaft Verfahren zur Herstellung eines Bauteiles mit aufgelöteten Folien aus ODS-Sintereisen-Legierungen und nach diesem Verfahren hergestelltes Bauteil
WO1999040231A1 (en) * 1998-02-04 1999-08-12 Sandvik Ab; (Publ) Dispersion hardening alloy and method for the production of the alloy
US6416871B1 (en) 1999-05-27 2002-07-09 Sandvik Ab Surface modification of high temperature alloys
DE10261207A1 (de) * 2002-12-20 2004-07-15 Mk Metallfolien Gmbh Eisenlegierung, insbesondere zur Verwendung in einer Abgasreinigungseinheit
CN108950357A (zh) * 2018-07-27 2018-12-07 中南大学 一种多尺度多相弥散强化铁基合金及其制备和表征方法
CN116121574A (zh) * 2023-02-08 2023-05-16 内蒙古蒙泰集团有限公司 一种适用于铝硅铸造合金中的铁相改形方法

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04194038A (ja) * 1990-11-27 1992-07-14 Gunze Ltd 紡績糸の製造方法
US5427601A (en) * 1990-11-29 1995-06-27 Ngk Insulators, Ltd. Sintered metal bodies and manufacturing method therefor
JP2585900B2 (ja) * 1991-08-28 1997-02-26 株式会社日立製作所 耐熱性強化部材の製造方法
CN108330408B (zh) * 2017-01-18 2019-10-01 天津大学 一种高强度含铝铁素体ods钢及其制备方法
CN110343935B (zh) * 2019-07-11 2021-02-09 中国科学院金属研究所 采用表面氧化+爆炸压实制备氧化物弥散强化铁素体钢

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3992161A (en) * 1973-01-22 1976-11-16 The International Nickel Company, Inc. Iron-chromium-aluminum alloys with improved high temperature properties
US4402746A (en) * 1982-03-31 1983-09-06 Exxon Research And Engineering Co. Alumina-yttria mixed oxides in dispersion strengthened high temperature alloys

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE794142A (fr) * 1972-01-17 1973-07-17 Int Nickel Ltd Alliages pour hautes temperatures
US4391634A (en) * 1982-03-01 1983-07-05 Huntington Alloys, Inc. Weldable oxide dispersion strengthened alloys
US4619699A (en) * 1983-08-17 1986-10-28 Exxon Research And Engineering Co. Composite dispersion strengthened composite metal powders
JPS61221303A (ja) * 1985-03-27 1986-10-01 Riken Corp 酸化物分散Ｆｅ基高合金の製造方法

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3992161A (en) * 1973-01-22 1976-11-16 The International Nickel Company, Inc. Iron-chromium-aluminum alloys with improved high temperature properties
US4402746A (en) * 1982-03-31 1983-09-06 Exxon Research And Engineering Co. Alumina-yttria mixed oxides in dispersion strengthened high temperature alloys
EP0091260A2 (de) * 1982-03-31 1983-10-12 Exxon Research And Engineering Company Verfahren zur Herstellung einer durch Oxiddispersion gehärteten Hochtemperaturlegierung

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2256202A (en) * 1991-04-24 1992-12-02 Inco Alloys Int Controlled grain size for ods iron-base alloys
GB2256202B (en) * 1991-04-24 1994-08-24 Inco Alloys Int Controlled grain size for ods iron-base alloys
EP0566254A1 (de) * 1992-03-26 1993-10-20 British Ceramic Service Company Limited Förderbandofen
EP0735148A1 (de) * 1995-03-25 1996-10-02 PLANSEE Aktiengesellschaft Verfahren zur Herstellung eines Bauteiles mit aufgelöteten Folien aus ODS-Sintereisen-Legierungen und nach diesem Verfahren hergestelltes Bauteil
WO1999040231A1 (en) * 1998-02-04 1999-08-12 Sandvik Ab; (Publ) Dispersion hardening alloy and method for the production of the alloy
US6416871B1 (en) 1999-05-27 2002-07-09 Sandvik Ab Surface modification of high temperature alloys
DE10261207A1 (de) * 2002-12-20 2004-07-15 Mk Metallfolien Gmbh Eisenlegierung, insbesondere zur Verwendung in einer Abgasreinigungseinheit
CN108950357A (zh) * 2018-07-27 2018-12-07 中南大学 一种多尺度多相弥散强化铁基合金及其制备和表征方法
CN116121574A (zh) * 2023-02-08 2023-05-16 内蒙古蒙泰集团有限公司 一种适用于铝硅铸造合金中的铁相改形方法

Also Published As

Publication number Publication date
JP2845877B2 (ja) 1999-01-13
EP0256555A3 (en) 1989-02-22
AU600009B2 (en) 1990-08-02
ATE81679T1 (de) 1992-11-15
EP0256555B1 (de) 1992-10-21
AU7672387A (en) 1988-02-25
DE3782294D1 (de) 1992-11-26
DE3782294T2 (de) 1993-03-04
JPS6350448A (ja) 1988-03-03

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