EP0652297B1 - Eisen- Aluminium-Legierung und Verwendung dieser Legierung - Google Patents
Eisen- Aluminium-Legierung und Verwendung dieser Legierung Download PDFInfo
- Publication number
- EP0652297B1 EP0652297B1 EP93118045A EP93118045A EP0652297B1 EP 0652297 B1 EP0652297 B1 EP 0652297B1 EP 93118045 A EP93118045 A EP 93118045A EP 93118045 A EP93118045 A EP 93118045A EP 0652297 B1 EP0652297 B1 EP 0652297B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- alloy
- iron
- ppm
- aluminum
- titanium
- 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 - Lifetime
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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
- C22C38/06—Ferrous alloys, e.g. steel alloys containing aluminium
Definitions
- Iron-aluminum alloys can be subjected to high thermal loads exposed to oxidizing and / or corrosive effects Parts of thermal machines can be used. You are supposed to be there increasingly special steels and nickel-based superalloys replace.
- the invention as set out in claim 1 lies based on the task of an iron-aluminum alloy develop, which develop at temperatures of more than 700 ° C characterized by good mechanical properties. Task of Invention is also a suitable use of this alloy.
- the alloy according to the invention exhibits even at temperatures between 700 and 800 ° C still mechanical properties that their use in mechanically slightly stressed components enable.
- the invention is distinguished Alloy due to excellent thermal shock resistance and can therefore be used to particular advantage in thermal cycling Share thermal systems, such as in particular Housing or housing part of a gas turbine or one Turbocharger or as a nozzle ring, especially for one Turbocharger.
- the Alloy very inexpensive by casting or by casting and make rollers.
- Another advantage of Alloy according to the invention is that its Components have only metals, which comparatively inexpensive and independent of strategic-political Influencing are available.
- Alloy I (alloy according to a preferred embodiment of the invention): component At.% aluminum 16.00 chrome 5.00 niobium 1.00 Silicon 1.00 boron 3.53 titanium 1.51 carbon 300ppm zirconium 100ppm iron rest
- Alloy II (state of the art alloy) component At%. Silicon 4.00 carbon 3.35 molybdenum 1.00 manganese 0.30 phosphorus 0.01 sulfur 0.05 iron rest
- Alloy I was tested in an arc furnace under argon Shielding gas melted. The served as starting materials individual elements with a degree of purity of more than 99%. The melt became a cast body approximately 100 mm in diameter and cast about 100 mm high. The cast body was remelted under vacuum and also under vacuum in the form of round bars with a diameter of approx. 12 mm and approx. 70 mm Length, in the form of carrots with a minimum diameter of approx. 10 mm, a maximum diameter of approx. 16 mm and one Length of about 65 mm or in the form of disc-shaped discs with a disk diameter of 80 mm, a disk thickness up to 14 mm and a radius at the edge of the disc of approx. 1 mm shed.
- the discus-shaped Discs along the disc axis each with a hole introduced a diameter of 19.5 mm.
- From the round bars and carrots were made specimens for tensile tests.
- the disks were used to determine the thermal shock resistance.
- Appropriately sized test specimens for determining the mechanical strength and thermal shock resistance have been commercially available on a large scale Alloy II used as material for gas turbine housings and a related alloy with a 25% lower alloy Share of silicon and a 40% lower share Made of molybdenum.
- the thermal shock resistance according to Glenny was determined with the help of the disc-shaped discs. Two disks per alloy were cyclically heated to 650 ° C in a fluid bed and then cooled to 200 C with compressed air. After a certain number of such heating and cooling cycles, the number of cracks possibly forming at the edge of the panes with a crack length greater than 2 mm was then counted. The total number of cracks occurring on both disks as a function of the number of cycles is given below for alloy I according to the invention and for the two alloys according to the prior art.
- Alloy I invention
- Alloy II further alloy (State of the art) 140 0 0 0 240 0 2nd 1 340 0 2nd 4th 540 0 4th 4th 740 0 4th 8th
- the alloy according to the invention comparably outperforms usable alloys according to the prior art not only in terms of mechanical strength at temperatures higher 700 ° C, but also in terms of thermal shock resistance.
- the alloy according to the invention can therefore with particular Advantage as a material for components of thermal systems are used, which at temperatures between 700 ° C and 800 ° C still have a relatively high mechanical strength, and which, like gas turbine housings, have strong temperature changes subject to.
- niobium By adding 0.1 to 2 at% of niobium, the hardness and the Strength of the alloy according to the invention increased. Beside or Instead of niobium, tungsten and / or tantalum can also be used Proportion of 0.1 to 2 at% can be added.
- a proportion of 0.1 to 2 at% silicon improves the Castability of the alloy according to the invention and acts favorable for their resistance to oxidation and corrosion. Silicon also increases hardness.
- the thermal shock, oxidation and corrosion resistance of the alloy according to the invention is considerably improved. This is primarily due to the fact that finely divided titanium diboride TiB 2 then forms in the alloy.
- a protective layer predominantly containing aluminum oxides forms on the surface of the alloy according to the invention.
- the titanium diboride phase contributes to a substantial stabilization of this protective layer by the titanium diboride phase engaging in the protective layer, for example in the form of acicular crystallites from the alloy, and thereby causing the protective layer to adhere particularly well to the underlying alloy.
- the proportion of boron should not be more than 5 at% and that of titanium should not be more than 2 at%, since otherwise too much titanium diboride will form and the alloy will become brittle. If the proportion of boron is below 0.1 at% and that of titanium below 0.01 at%, the thermal shock, oxidation and corrosion resistance of the alloy according to the invention deteriorate considerably.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Supercharger (AREA)
- Powder Metallurgy (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
Description
Bestandteil | At.% |
Aluminium | 16,00 |
Chrom | 5,00 |
Niob | 1,00 |
Silicium | 1,00 |
Bor | 3,53 |
Titan | 1,51 |
Kohlenstoff | 300ppm |
Zirkonium | 100ppm |
Eisen | Rest |
Bestandteil | At%. |
Silicium | 4,00 |
Kohlenstoff | 3,35 |
Molybdän | 1,00 |
Mangan | 0,30 |
Phosphor | 0,01 |
Schwefel | 0,05 |
Eisen | Rest |
Zyklenzahl | Anzahl Risse grösser 2 mm | ||
Legierung I (Erfindung) | Legierung II | weitere Legierung | |
(Stand der Technik) | |||
140 | 0 | 0 | 0 |
240 | 0 | 2 | 1 |
340 | 0 | 2 | 4 |
540 | 0 | 4 | 4 |
740 | 0 | 4 | 8 |
Rest Eisen.
Claims (4)
- Legierung auf der Basis von Eisen und Aluminium, dadurch gekennzeichnet, dass sie folgende Bestandteile in Atomprozent enthält:12 - 18 Aluminium0,1 - 10 Chrom0,1 - 2 Niob0,1 - 2 Silicium0,1 - 5 Bor0,01 - 2 Titan100 - 500 ppm Kohlenstoff50 - 200 ppm Zirkonium
Rest Eisen. - Legierung nach Anspruch 1, dadurch gekennzeichnet, dass sie folgende Bestandteile enthält:14 - 16 Aluminium0,5 - 1,5 Niob4 - 6 Chrom0,5 - 1,5 Silicium3 - 4 Bor1 - 2 Titanca. 300 ppm Kohlenstoffca. 100 ppm Zirkonium
Rest Eisen. - Verwendung der Legierung nach Anspruch 1 als thermoschockbeständiger Werkstoff.
- Verwendung nach Anspruch 3, dadurch gekennzeichnet, dass der Werkstoff der Bildung eines heissgasführenden Bauteils, insbesondere des Gehäuses einer Gasturbine dient.
Priority Applications (9)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP93118045A EP0652297B1 (de) | 1993-11-08 | 1993-11-08 | Eisen- Aluminium-Legierung und Verwendung dieser Legierung |
DE59309611T DE59309611D1 (de) | 1993-11-08 | 1993-11-08 | Eisen- Aluminium-Legierung und Verwendung dieser Legierung |
AT93118045T ATE180517T1 (de) | 1993-11-08 | 1993-11-08 | Eisen- aluminium-legierung und verwendung dieser legierung |
US08/174,352 US5411702A (en) | 1993-11-08 | 1993-12-28 | Iron-aluminum alloy for use as thermal-shock resistance material |
PL94305673A PL305673A1 (en) | 1993-11-08 | 1994-11-02 | Fe-al alloy |
RU94040155A RU2122044C1 (ru) | 1993-11-08 | 1994-11-04 | Сплав железа с алюминием |
JP27240494A JP3517462B2 (ja) | 1993-11-08 | 1994-11-07 | 鉄−アルミニウム合金およびこの合金の用途 |
KR1019940029070A KR950014344A (ko) | 1993-11-08 | 1994-11-07 | 철-알루미늄 합금 및 그 합금의 용도 |
CN94118112A CN1038051C (zh) | 1993-11-08 | 1994-11-08 | 铁铝合金及其用途 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP93118045A EP0652297B1 (de) | 1993-11-08 | 1993-11-08 | Eisen- Aluminium-Legierung und Verwendung dieser Legierung |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0652297A1 EP0652297A1 (de) | 1995-05-10 |
EP0652297B1 true EP0652297B1 (de) | 1999-05-26 |
Family
ID=8213403
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP93118045A Expired - Lifetime EP0652297B1 (de) | 1993-11-08 | 1993-11-08 | Eisen- Aluminium-Legierung und Verwendung dieser Legierung |
Country Status (9)
Country | Link |
---|---|
US (1) | US5411702A (de) |
EP (1) | EP0652297B1 (de) |
JP (1) | JP3517462B2 (de) |
KR (1) | KR950014344A (de) |
CN (1) | CN1038051C (de) |
AT (1) | ATE180517T1 (de) |
DE (1) | DE59309611D1 (de) |
PL (1) | PL305673A1 (de) |
RU (1) | RU2122044C1 (de) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6436163B1 (en) * | 1994-05-23 | 2002-08-20 | Pall Corporation | Metal filter for high temperature applications |
DE19603515C1 (de) * | 1996-02-01 | 1996-12-12 | Castolin Sa | Spritzwerkstoff auf Eisenbasis zum Herstellen einer korrosionsbeständigen Beschichtung, Herstellungsverfahren für die Beschichtung sowie Verwendung der Schicht |
DE19753876A1 (de) * | 1997-12-05 | 1999-06-10 | Asea Brown Boveri | Eisenaluminidbeschichtung und Verfahren zum Aufbringen einer Eisenaluminidbeschichtung |
US6114058A (en) * | 1998-05-26 | 2000-09-05 | Siemens Westinghouse Power Corporation | Iron aluminide alloy container for solid oxide fuel cells |
US7754342B2 (en) * | 2005-12-19 | 2010-07-13 | General Electric Company | Strain tolerant corrosion protecting coating and spray method of application |
DE102009020922A1 (de) | 2009-05-12 | 2010-11-18 | Christoph Henrik Sterzel | Die Anwendung von niedrigviskosem Schwefel als Wärmeträger- und Wärmespeicherflüssigkeit |
EP2239349A1 (de) * | 2009-04-10 | 2010-10-13 | Schüttenhelm, Martin | Abgaskrümmer oder Turboladergehäuse aus einer FeAl-Stahllegierung |
MA33950B1 (fr) | 2010-01-05 | 2013-01-02 | Basf Se | Liquides caloporteurs et accumulateurs thermiques a base de polysulfures pour des temperatures extremement elevees |
KR20140038472A (ko) * | 2011-06-07 | 2014-03-28 | 보르그워너 인코퍼레이티드 | 터보차저 및 그 구성요소 |
CN105624535A (zh) * | 2015-12-09 | 2016-06-01 | 上海大学 | Fe-Al-Mn-Si合金的制备方法 |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CA648140A (en) * | 1962-09-04 | Westinghouse Electric Corporation | Grain-refined aluminum-iron alloys | |
CA648141A (en) * | 1962-09-04 | H. Schramm Jacob | Aluminum-chromium-iron resistance alloys | |
US2387980A (en) * | 1945-02-17 | 1945-10-30 | Hugh S Cooper | Electrical resistance alloys |
US3026197A (en) * | 1959-02-20 | 1962-03-20 | Westinghouse Electric Corp | Grain-refined aluminum-iron alloys |
JPS4841918A (de) * | 1971-10-04 | 1973-06-19 | ||
CA1298492C (en) * | 1986-04-30 | 1992-04-07 | Haruo Shimada | Seawater-corrosion-resistant non-magnetic steel materials |
US4844865A (en) * | 1986-12-02 | 1989-07-04 | Nippon Steel Corporation | Seawater-corrosion-resistant non-magnetic steel materials |
-
1993
- 1993-11-08 EP EP93118045A patent/EP0652297B1/de not_active Expired - Lifetime
- 1993-11-08 DE DE59309611T patent/DE59309611D1/de not_active Expired - Fee Related
- 1993-11-08 AT AT93118045T patent/ATE180517T1/de not_active IP Right Cessation
- 1993-12-28 US US08/174,352 patent/US5411702A/en not_active Expired - Lifetime
-
1994
- 1994-11-02 PL PL94305673A patent/PL305673A1/xx unknown
- 1994-11-04 RU RU94040155A patent/RU2122044C1/ru active
- 1994-11-07 JP JP27240494A patent/JP3517462B2/ja not_active Expired - Fee Related
- 1994-11-07 KR KR1019940029070A patent/KR950014344A/ko not_active Application Discontinuation
- 1994-11-08 CN CN94118112A patent/CN1038051C/zh not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
RU2122044C1 (ru) | 1998-11-20 |
CN1106467A (zh) | 1995-08-09 |
RU94040155A (ru) | 1997-02-27 |
JP3517462B2 (ja) | 2004-04-12 |
PL305673A1 (en) | 1995-05-15 |
DE59309611D1 (de) | 1999-07-01 |
US5411702A (en) | 1995-05-02 |
EP0652297A1 (de) | 1995-05-10 |
CN1038051C (zh) | 1998-04-15 |
JPH07238353A (ja) | 1995-09-12 |
ATE180517T1 (de) | 1999-06-15 |
KR950014344A (ko) | 1995-06-15 |
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