EP0652297A1 - Iron-aluminium alloy and application of this alloy - Google Patents
Iron-aluminium alloy and application of this alloy Download PDFInfo
- Publication number
- EP0652297A1 EP0652297A1 EP93118045A EP93118045A EP0652297A1 EP 0652297 A1 EP0652297 A1 EP 0652297A1 EP 93118045 A EP93118045 A EP 93118045A EP 93118045 A EP93118045 A EP 93118045A EP 0652297 A1 EP0652297 A1 EP 0652297A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- alloy
- iron
- aluminum
- approx
- 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.)
- Granted
Links
Images
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 used in parts of thermal machines that are subjected to high thermal loads and are subject to oxidizing and / or corrosive effects. There, they are expected to increasingly replace special steels and nickel-based superalloys.
- the invention is based on the object of developing an iron-aluminum alloy which is distinguished by good mechanical properties at temperatures of more than 700 ° C.
- the object of the invention is also a suitable use of this alloy.
- the alloy according to the invention still has mechanical properties which enable it to be used in components which are subject to slight mechanical loads.
- the alloy according to the invention is characterized by excellent thermal shock resistance and can therefore be used with particular advantage in parts of thermal systems subject to thermal shock, such as in particular as a housing or housing part of a gas turbine or a turbocharger or as a nozzle ring, in particular for a turbocharger.
- the alloy can be produced very cheaply by casting or by casting and rolling.
- Another advantage of the alloy according to the invention is that its constituents exclusively contain metals, which are comparatively inexpensive and are available regardless of strategic-political influence.
- the sole figure shows a diagram in which the tensile strength UTS [MPa] of an alloy I according to the invention and an alloy II according to the prior art is shown as a function of the temperature T [° C.].
- Alloys I and II shown in the figure have the following compositions: 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 melted in an arc furnace under argon as a protective gas.
- the individual elements with a degree of purity of more than 99% served as starting materials.
- the melt was poured into a cast body approximately 100 mm in diameter and approximately 100 mm high.
- the cast body was melted again under vacuum and also under vacuum in the form of round bars with a diameter of approx. 12 mm and a length of approx. 70 mm, in the form of carrots with a minimum diameter of approx. 10 mm and a maximum diameter of approx. 16 mm and a length of approx. 65 mm or in the form of disc-shaped discs with a disc diameter of 80 mm, a disc thickness of up to 14 mm and a radius at the edge of the disc of approx.
- test specimens for tensile tests were made from the round bars and carrots. The disks were used to determine the thermal shock resistance.
- Correspondingly sized test specimens for determining the mechanical strength and the thermal shock resistance were made from the commercially available alloy II, which is used to a large extent as a material for gas turbine casings, and a related alloy with an approximately 25% lower silicon content and an approximately 40% lower content 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 the two alloys according to the prior art.
- the alloy according to the invention outperforms comparable usable alloys according to the prior art not only in terms of mechanical strength at temperatures higher than 700 ° C., but also in terms of thermal shock resistance.
- the alloy according to the invention can therefore be used with particular advantage as a material for components of thermal systems which still have a relatively high mechanical strength at temperatures between 700.degree. C. and 800.degree. C. and which, like gas turbine housings, are subject to severe temperature changes.
- Alloying 0.1 to 10 at% chromium further increases the thermal shock, oxidation and corrosion resistance. Chromium also improves ductility. However, additions of more than 10 at.% Cr generally deteriorate the mechanical properties again.
- Alloying 0.1 to 2 at% of niobium increases the hardness and strength of the alloy according to the invention.
- tungsten and / or tantalum can also be added in a proportion of 0.1 to 2 at%.
- a proportion of 0.1 to 2 at% silicon improves the castability of the alloy according to the invention and has a favorable effect on its 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 TiB2 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.
- Alloys with the following composition have particularly good values of mechanical strength and thermal shock resistance: 14 - 16 aluminum 0.5 - 1.5 niobium 4 - 6 chrome 0.5-1.5 silicon 3 - 4 boron 1 - 2 titanium approx. 300 ppm carbon approx. 100 ppm zirconium Rest of iron.
Abstract
Description
Eisen-Aluminium-Legierungen können in thermisch hoch belasteten und oxidierenden und/oder korrodierenden Wirkungen ausgesetzten Teilen thermischer Maschinen verwendet werden. Sie sollen dort in zunehmendem Masse Spezialstähle sowie Nickelbasis-Superlegierungen ersetzen.Iron-aluminum alloys can be used in parts of thermal machines that are subjected to high thermal loads and are subject to oxidizing and / or corrosive effects. There, they are expected to increasingly replace special steels and nickel-based superalloys.
Im Literaturaufsatz "Acceptable Aluminium Additions for Minimal Environmental Effect in Iron-Aluminium Alloys", Mat. Res. Soc. Symp. Proc. Vol. 288, S.971-976, beschreiben V.K.Sikka et al. eine Eisen-Aluminium-Legierung mit einem Anteil von ca. 16 At% Aluminium und ca. 5 At% Chrom, welche gegebenenfalls ca. 0,1 At% Kohlenstoff und/oder Zirkonium und/oder 1 at% Molybdän enthält. Die bekannte Legierung weist bei Raumtemperatur gegenüber Eisen-Aluminium-Legierungen mit einem Aluminiumanteil von 22 bis 28 At% eine wesentlich höhere Duktilität auf. Bei einer Temperatur von 700°C ist die Zugfestigkeit dieser Legierung mit ca. 100 MPa relativ klein. Aus der Legierung hergestellte Bauteile sollten daher nicht bei Temperaturen oberhalb 700°C verwendet werden.In the article "Acceptable Aluminum Additions for Minimal Environmental Effect in Iron-Aluminum Alloys", Mat. Res. Soc. Symp. Proc. Vol. 288, pp.971-976, describe VKSikka et al. an iron-aluminum alloy with a proportion of approx. 16 at% aluminum and approx. 5 at% chromium, which optionally contains approx. 0.1 at% carbon and / or zirconium and / or 1 at% molybdenum. The known alloy has a significantly higher ductility at room temperature than iron-aluminum alloys with an aluminum content of 22 to 28 at%. At a temperature of 700 ° C the tensile strength of this alloy is relatively low at around 100 MPa. Components made from the alloy should therefore not be used at temperatures above 700 ° C.
Der Erfindung, wie sie in Patentanspruch 1 angegeben ist, liegt die Aufgabe zugrunde, eine Eisen-Aluminium-Legierung zu entwickeln, welche sich bei Temperaturen von mehr als 700°C durch gute mechanische Eigenschaften auszeichnet. Aufgabe der Erfindung ist auch eine geeignete Verwendung dieser Legierung.The invention, as specified in
Die erfindungsgemässe Legierung weist selbst bei Temperaturen zwischen 700 und 800°C noch mechanische Eigenschaften auf, die deren Einsatz in mechanisch geringfügig belasten Bauteilen ermöglichen. Zugleich zeichnet sich die erfindungsgemässe Legierung durch eine ausgezeichnete Thermoschockbeständigkeit aus und kann daher mit besonderem Vorteil in temperaturwechselbelasteten Teilen thermischer Anlagen, wie inbesondere als Gehäuse oder Gehäuseteil einer Gasturbine oder eines Turboladers oder als Düsenring, insbesondere für einen Turbolader, eingesetzt werden. Darüber hinaus lässt sich die Legierung sehr kostengünstig durch Giessen oder durch Giessen und Walzen herstellen. Ein weiterer Vorteil der erfindungsgemässen Legierung besteht darin, dass ihre Bestandteile ausschliesslich Metalle aufweisen, welche vergleichsweise preiswert und unabhängig von strategischpolitischer Beeinflussung verfügbar sind.Even at temperatures between 700 and 800 ° C., the alloy according to the invention still has mechanical properties which enable it to be used in components which are subject to slight mechanical loads. At the same time, the alloy according to the invention is characterized by excellent thermal shock resistance and can therefore be used with particular advantage in parts of thermal systems subject to thermal shock, such as in particular as a housing or housing part of a gas turbine or a turbocharger or as a nozzle ring, in particular for a turbocharger. In addition, the alloy can be produced very cheaply by casting or by casting and rolling. Another advantage of the alloy according to the invention is that its constituents exclusively contain metals, which are comparatively inexpensive and are available regardless of strategic-political influence.
Die Erfindung wird nachfolgend anhand eines in einer Figur näher erläuterten Ausführungsbeispiele beschrieben.The invention is described below with reference to an exemplary embodiment explained in more detail in a figure.
Hierbei zeigt die einzige Figur ein Diagramm, in dem die Zugfestigkeit UTS [MPa] einer Legierung I nach der Erfindung und einer Legierungen II nach dem Stand der Technik in Abhängigkeit von der Temperatur T [°C ] dargestellt ist.The sole figure shows a diagram in which the tensile strength UTS [MPa] of an alloy I according to the invention and an alloy II according to the prior art is shown as a function of the temperature T [° C.].
Die in der Figur angegebenen Legierungen I und II weisen die folgenden Zusammensetzungen auf:
Legierung I (Legierung gemäss einem bevorzugten Ausführungsbeispiel der Erfindung):
Legierung II (Legierung nach dem Stand der Technik)
Alloy I (alloy according to a preferred embodiment of the invention):
Alloy II (state of the art alloy)
Die Legierung I wurde in einem Lichtbogenofen unter Argon als Schutzgas erschmolzen. Als Ausgangsmaterialien dienten die einzelnen Elemente mit einem Reinheitsgrad von mehr als 99 %. Die Schmelze wurde zu einem Gusskörper von ca. 100 mm Durchmesser und ca. 100 mm Höhe abgegossen. Der Gusskörper wurde unter Vakuum wieder aufgeschmolzen und ebenfalls unter Vakuum in Form von Rundstäben mit ca. 12 mm Durchmesser und ca. 70 mm Länge, in Form von Karotten mit einem minimalen Durchmesser von ca. 10 mm, einem maximalen Durchmesser von ca. 16 mm und einer Länge von ca. 65 mm oder in Form von diskusförmigen Scheiben mit einem Scheibendurchmesser von 80 mm, einer Scheibendicke bis zu 14 mm und einem Radius am Scheibenrand von ca.1 mm vergossen. In einem weiteren Schritt wurde in die diskusförmigen Scheiben entlang der Scheibenachse jeweils eine Bohrung mit einem Durchmesser von 19,5 mm eingebracht. Aus den Rundstäben und Karotten wurden Probekörper für Zugversuche hergestellt. Die Scheiben dienten der Bestimmung der Thermoschockbeständigkeit. Entsprechend bemessene Probekörper zur Bestimmung der mechanischen Festigkeit und der Thermoschockbeständigkeit wurden aus der kommerziell erhältlichen und in grossem Umfang als Werkstoff für Gasturbinengehäuse eingesetzten Legierung II und einer verwandten Legierung mit einem um ca. 25% geringeren Anteil an Silicium und einem um ca. 40% geringeren Anteil an Molybdän hergestellt.Alloy I was melted in an arc furnace under argon as a protective gas. The individual elements with a degree of purity of more than 99% served as starting materials. The melt was poured into a cast body approximately 100 mm in diameter and approximately 100 mm high. The cast body was melted again under vacuum and also under vacuum in the form of round bars with a diameter of approx. 12 mm and a length of approx. 70 mm, in the form of carrots with a minimum diameter of approx. 10 mm and a maximum diameter of approx. 16 mm and a length of approx. 65 mm or in the form of disc-shaped discs with a disc diameter of 80 mm, a disc thickness of up to 14 mm and a radius at the edge of the disc of approx. 1 mm. In a further step, a hole was drilled into the disc-shaped disks along the disk axis introduced a diameter of 19.5 mm. Test specimens for tensile tests were made from the round bars and carrots. The disks were used to determine the thermal shock resistance. Correspondingly sized test specimens for determining the mechanical strength and the thermal shock resistance were made from the commercially available alloy II, which is used to a large extent as a material for gas turbine casings, and a related alloy with an approximately 25% lower silicon content and an approximately 40% lower content Made of molybdenum.
Die Zugversuche wurden in Abhängigkeit von der Temperatur durchgeführt. Hieraus ergab sich für die erfindungsgemässe Legierung I eine Zugfestigkeit, welche bei einer Temperatur von 800°C mit ca. 100 MPa erheblich höher ist als diejenige der Legierung II nach dem Stand der Technik. Entsprechendes gilt auch für die in der Figur nicht dargestellte Legierung nach dem Stand der Technik mit reduzierten Silicium- und Molybdänanteilen.The tensile tests were carried out depending on the temperature. This gave the alloy I according to the invention a tensile strength which, at a temperature of 800 ° C. and approximately 100 MPa, is considerably higher than that of the alloy II according to the prior art. The same applies correspondingly to the alloy according to the prior art, which is not shown in the figure and has reduced silicon and molybdenum contents.
Mit Hilfe der diskusförmigen Scheiben wurde die Thermoschockbeständigkeit nach Glenny ermittelt. Je zwei Scheiben pro Legierung wurden zyklisch jeweils in einem Fliessbett auf 650°C aufgeheizt und danach mit Pressluft auf 200 C abgekühlt. Nach einer bestimmten Anzahl solcher Aufheiz- und Abkühlzyklen wurde sodann die Anzahl von sich möglicherweise am Rand der Scheiben bildenden Rissen mit einer Risslänge grösser 2 mm gezählt. Die aufsummierte Anzahl der an beiden Scheiben auftretenden Risse in Abhängigkeit von der Zyklenzahl ist nachfolgend für die erfindungsgemässe Legierung I sowie die beiden Legierungen nach dem Stand der Technik angegeben.
Hieraus ist ersichtlich, dass bei den üblicherweise als Werkstoff für Gasturbinengehäuse verwendeten Legierungen nach dem Stand der Technik bereits nach 240 Zyklen unerwünschte Risse auftraten, wohingegen die Legierung nach der Erfindung selbst nach 740 Zyklen noch rissfrei blieb.From this it can be seen that in the alloys of the prior art which are usually used as a material for gas turbine housings, undesirable cracks occurred after only 240 cycles, whereas the alloy according to the invention remained crack-free even after 740 cycles.
Die Legierung nach der Erfindung übertrifft vergleichbar verwendbare Legierungen nach dem Stand der Technik nicht nur hinsichtlich der mechanischen Festigkeit bei Temperaturen höher 700°C, sondern auch hinsichtlich der Thermoschockbeständigkeit. Die erfindungsgemässe Legierung kann daher mit besonderem Vorteil als Werkstoff für Bauteile von thermischen Anlagen verwendet werden, welche bei Temperaturen zwischen 700°C und 800°C noch eine relativ hohe mechanische Festigkeit aufweisen, und welche wie Gasturbinengehäuse starken Temperaturwechselbelastungen unterliegen.The alloy according to the invention outperforms comparable usable alloys according to the prior art not only in terms of mechanical strength at temperatures higher than 700 ° C., but also in terms of thermal shock resistance. The alloy according to the invention can therefore be used with particular advantage as a material for components of thermal systems which still have a relatively high mechanical strength at temperatures between 700.degree. C. and 800.degree. C. and which, like gas turbine housings, are subject to severe temperature changes.
Gute Festigkeitseigenschaften bei Temperaturen zwischen 700 und 800°C und eine hohe Thermoschockbeständigkeit weisen erfindungsgemäss ausgeführte Legierung dann auf, wenn der Aluminiumgehalt mindestens 12 und höchstens 18 At% beträgt. Sinkt der Aluminiumgehalt unter 12 At%, so verschlechtern sich die Oxidations-, die Korrosions- und die Thermoschockbeständigkeit der erfindungsgemässen Legierung. Ist der Aluminiumgehalt grösser 18 At%, so versprödet die Legierung zunehmend.Good strength properties at temperatures between 700 and 800 ° C and high thermal shock resistance have alloy according to the invention when the aluminum content is at least 12 and at most 18 at%. If the aluminum content drops below 12 at%, the oxidation, corrosion and thermal shock resistance of the alloy according to the invention deteriorate. If the aluminum content is greater than 18 at%, the alloy becomes increasingly brittle.
Durch Zulegieren von 0,1 bis 10 At% Chrom wird die Thermoschock-, die Oxidations- und die Korrosionsbeständigkeit weiter erhöht. Zudem wird durch Chrom die Duktilität verbessert. Zugaben von mehr als 10 At.-% Cr verschlechtern jedoch im allgemeinen die mechanischen Eigenschaften wieder.Alloying 0.1 to 10 at% chromium further increases the thermal shock, oxidation and corrosion resistance. Chromium also improves ductility. However, additions of more than 10 at.% Cr generally deteriorate the mechanical properties again.
Durch Zulegieren von 0,1 bis 2 At% Niob wird die Härte und die Festigkeit der erfindungsgemässen Legierung erhöht. Neben oder anstelle von Niob können auch Wolfram und/oder Tantal mit einem Anteil von 0,1 bis 2 At% zulegiert werden.Alloying 0.1 to 2 at% of niobium increases the hardness and strength of the alloy according to the invention. In addition to or instead of niobium, tungsten and / or tantalum can also be added in a proportion of 0.1 to 2 at%.
Ein Anteil an 0,1 bis 2 At% Silicium verbessert die Giessbarkeit der erfindungsgemässen Legierung und wirkt sich günstig auf deren Oxidations- und Korrosionsbeständigkeit aus. Zudem wirkt Silicium härtesteigernd.A proportion of 0.1 to 2 at% silicon improves the castability of the alloy according to the invention and has a favorable effect on its resistance to oxidation and corrosion. Silicon also increases hardness.
Durch Zulegieren von 0,1 bis 5 At% Bor und 0,01 bis 2 At% Titan wird die Thermoschock-, die Oxidations- und Korrosionsbeständigkeit der erfindungsgemässen Legierung ganz erheblich verbessert. Dies ist vor allem dadurch bedingt, dass sich dann in der Legierung fein verteiltes Titandiborid TiB₂ bildet. Bei hohen Temperaturen und unter oxidierenden und/oder korrodierenden Bedingungen bildet sich auf der Oberfläche der erfindungsgemässen Legierung eine überwiegend Aluminiumoxide enthaltende Schutzschicht aus. Die Titandiborid-Phase trägt zu einer wesentlichen Stabilisierung dieser Schutzschicht bei, indem die Titandiborid-Phase etwa in Form nadelförmiger Kristallite aus der Legierung in die Schutzschicht eingreift und dadurch eine besonders gute Haftung der Schutzschicht auf der darunterliegenden Legierung bewirkt. Der Anteil an Bor sollte nicht mehr als 5 At% und derjenige von Titan nicht mehr als 2 At% betragen, da sich andernfalls zuviel Titandiborid bildet und die Legierung versprödet. Liegt der Boranteil unter 0,1 At% und derjenige von Titan unter 0,01 At%, so verschlechtern sich die Thermoschock-, die Oxidations- und die Korrosionsbeständigkeit der erfindungsgemässen Legierung ganz erheblich.By alloying 0.1 to 5 at% boron and 0.01 to 2 at% titanium, 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 TiB₂ then forms in the alloy. At high temperatures and under oxidizing and / or corrosive conditions, 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.
Eine geringfügige Erhöhung der mechanischen Festigkeit und zugleich eine erhebliche Verbesserung der Schweissbarkeit wird durch Zulegieren von 100 bis 500 ppm Kohlenstoff und 50 bis 200 ppm Zirkonium erreicht.A slight increase in mechanical strength and at the same time a considerable improvement in weldability is achieved by alloying 100 to 500 ppm carbon and 50 to 200 ppm zirconium.
Besonders gute Werte der mechanischen Festigkeit und der Thermoschockbeständigkeit weisen Legierungen der folgenden Zusammensetzung auf:
14 - 16 Aluminium
0,5 - 1,5 Niob
4 - 6 Chrom
0,5 - 1,5 Silicium
3 - 4 Bor
1 - 2 Titan
ca. 300 ppm Kohlenstoff
ca. 100 ppm Zirkonium
Rest Eisen.Alloys with the following composition have particularly good values of mechanical strength and thermal shock resistance:
14 - 16 aluminum
0.5 - 1.5 niobium
4 - 6 chrome
0.5-1.5 silicon
3 - 4 boron
1 - 2 titanium
approx. 300 ppm carbon
approx. 100 ppm zirconium
Rest of iron.
Claims (4)
12 - 18 Aluminium
0,1 - 10 Chrom
0,1 - 2 Niob
0,1 - 2 Silicium
0,1 - 5 Bor
0,01 - 2 Titan
100 - 500 ppm Kohlenstoff
50 - 200 ppm Zirkonium
Rest Eisen.Alloy based on iron and aluminum, characterized in that it contains the following components in atomic percent:
12 - 18 aluminum
0.1-10 chromium
0.1 - 2 niobium
0.1-2 silicon
0.1 - 5 boron
0.01 - 2 titanium
100-500 ppm carbon
50-200 ppm zirconium
Rest of iron.
14 - 16 Aluminium
0,5 - 1,5 Niob
4 - 6 Chrom
0,5 - 1,5 Silicium
3 - 4 Bor
1 - 2 Titan
ca. 300 ppm Kohlenstoff
ca. 100 ppm Zirkonium
Rest Eisen.Alloy according to claim 1, characterized in that it contains the following components:
14 - 16 aluminum
0.5 - 1.5 niobium
4 - 6 chrome
0.5-1.5 silicon
3 - 4 boron
1 - 2 titanium
approx. 300 ppm carbon
approx. 100 ppm zirconium
Rest of iron.
Priority Applications (9)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE59309611T DE59309611D1 (en) | 1993-11-08 | 1993-11-08 | Iron-aluminum alloy and use of this alloy |
| AT93118045T ATE180517T1 (en) | 1993-11-08 | 1993-11-08 | IRON-ALUMINUM ALLOY AND USE OF THIS ALLOY |
| EP93118045A EP0652297B1 (en) | 1993-11-08 | 1993-11-08 | Iron-aluminium alloy and application of this alloy |
| 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 (en) | 1993-11-08 | 1994-11-04 | Alloy containing iron and aluminium |
| KR1019940029070A KR950014344A (en) | 1993-11-08 | 1994-11-07 | Iron-Aluminum Alloys and Their Uses |
| JP27240494A JP3517462B2 (en) | 1993-11-08 | 1994-11-07 | Iron-aluminum alloys and their uses |
| CN94118112A CN1038051C (en) | 1993-11-08 | 1994-11-08 | Iron-aluminum alloy and use of said alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP93118045A EP0652297B1 (en) | 1993-11-08 | 1993-11-08 | Iron-aluminium alloy and application of this alloy |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0652297A1 true EP0652297A1 (en) | 1995-05-10 |
| EP0652297B1 EP0652297B1 (en) | 1999-05-26 |
Family
ID=8213403
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP93118045A Expired - Lifetime EP0652297B1 (en) | 1993-11-08 | 1993-11-08 | Iron-aluminium alloy and application of this alloy |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US5411702A (en) |
| EP (1) | EP0652297B1 (en) |
| JP (1) | JP3517462B2 (en) |
| KR (1) | KR950014344A (en) |
| CN (1) | CN1038051C (en) |
| AT (1) | ATE180517T1 (en) |
| DE (1) | DE59309611D1 (en) |
| PL (1) | PL305673A1 (en) |
| RU (1) | RU2122044C1 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19603515C1 (en) * | 1996-02-01 | 1996-12-12 | Castolin Sa | Spraying material used to form corrosive-resistant coating |
| EP2239349A1 (en) * | 2009-04-10 | 2010-10-13 | Schüttenhelm, Martin | Exhaust manifold or turbocahrger housing made of a FeAl steel alloy |
| DE102009020922A1 (en) | 2009-05-12 | 2010-11-18 | Christoph Henrik Sterzel | Use of liquid sulfur containing hydrogen sulfide and polysulfane or chlorine, as heat transfer- and heat storage liquid for transporting and storing of thermal energy, preferably in solar thermal power plants |
| WO2011083053A1 (en) | 2010-01-05 | 2011-07-14 | Basf Se | Heat transfer and heat storage fluids for extremely high temperatures, based on polysulfides |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6436163B1 (en) * | 1994-05-23 | 2002-08-20 | Pall Corporation | Metal filter for high temperature applications |
| DE19753876A1 (en) * | 1997-12-05 | 1999-06-10 | Asea Brown Boveri | Iron aluminide coating and method of applying an iron aluminide coating |
| 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 |
| CN103534458A (en) * | 2011-06-07 | 2014-01-22 | 博格华纳公司 | Turbocharger and component therefor |
| CN105624535A (en) * | 2015-12-09 | 2016-06-01 | 上海大学 | Preparation method for Fe-Al-Mn-Si alloy |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Family Cites Families (5)
| 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 | |
| JPS4841918A (en) * | 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 AT AT93118045T patent/ATE180517T1/en not_active IP Right Cessation
- 1993-11-08 DE DE59309611T patent/DE59309611D1/en not_active Expired - Fee Related
- 1993-11-08 EP EP93118045A patent/EP0652297B1/en not_active Expired - Lifetime
- 1993-12-28 US US08/174,352 patent/US5411702A/en not_active Expired - Lifetime
-
1994
- 1994-11-02 PL PL94305673A patent/PL305673A1/en unknown
- 1994-11-04 RU RU94040155A patent/RU2122044C1/en active
- 1994-11-07 KR KR1019940029070A patent/KR950014344A/en not_active Application Discontinuation
- 1994-11-07 JP JP27240494A patent/JP3517462B2/en not_active Expired - Fee Related
- 1994-11-08 CN CN94118112A patent/CN1038051C/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19603515C1 (en) * | 1996-02-01 | 1996-12-12 | Castolin Sa | Spraying material used to form corrosive-resistant coating |
| WO1997028289A1 (en) * | 1996-02-01 | 1997-08-07 | Castolin S.A. | Iron-based spray material for producing a corrosion-resistant coating, process for producing the coating and use of the coat |
| EP2239349A1 (en) * | 2009-04-10 | 2010-10-13 | Schüttenhelm, Martin | Exhaust manifold or turbocahrger housing made of a FeAl steel alloy |
| DE102009020922A1 (en) | 2009-05-12 | 2010-11-18 | Christoph Henrik Sterzel | Use of liquid sulfur containing hydrogen sulfide and polysulfane or chlorine, as heat transfer- and heat storage liquid for transporting and storing of thermal energy, preferably in solar thermal power plants |
| WO2011083053A1 (en) | 2010-01-05 | 2011-07-14 | Basf Se | Heat transfer and heat storage fluids for extremely high temperatures, based on polysulfides |
Also Published As
| Publication number | Publication date |
|---|---|
| EP0652297B1 (en) | 1999-05-26 |
| CN1106467A (en) | 1995-08-09 |
| PL305673A1 (en) | 1995-05-15 |
| CN1038051C (en) | 1998-04-15 |
| JP3517462B2 (en) | 2004-04-12 |
| US5411702A (en) | 1995-05-02 |
| ATE180517T1 (en) | 1999-06-15 |
| KR950014344A (en) | 1995-06-15 |
| JPH07238353A (en) | 1995-09-12 |
| RU2122044C1 (en) | 1998-11-20 |
| RU94040155A (en) | 1997-02-27 |
| DE59309611D1 (en) | 1999-07-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| DE1238672B (en) | Use of a nickel-cobalt-chromium alloy for castings that are resistant to creep at high temperatures | |
| DE102012011162A1 (en) | Nickel-chromium alloy with good processability, creep resistance and corrosion resistance | |
| DE102018107248A1 (en) | USE OF NICKEL CHROME IRON ALUMINUM ALLOY | |
| US4740354A (en) | Nickel-base alloys for high-temperature forging dies usable in atmosphere | |
| EP0652297B1 (en) | Iron-aluminium alloy and application of this alloy | |
| US4613368A (en) | Tri-nickel aluminide compositions alloyed to overcome hot-short phenomena | |
| EP0581204A1 (en) | Heat-resistant material | |
| US3257178A (en) | Coated metal article | |
| GB2116211A (en) | Oxidation resistant nickel alloy | |
| EP0570072B1 (en) | Method of producing a chromium-base alloy | |
| EP1589122B1 (en) | Coating containing NiAl beta Phases | |
| DE2161954A1 (en) | FERRITIC HEAT RESISTANT STEEL | |
| EP0709478B1 (en) | Alloy based of silicides and further containing chromium and molybdenum | |
| DE3590031C2 (en) | Process for producing a metal powder | |
| DE1219236B (en) | Process for the production of castings, in particular of gas turbine rotors with blades cast onto the hub, from a nickel-chromium alloy | |
| EP0609682B1 (en) | Oxidation- and corrosion-resistant alloy based on doped iron aluminide and application of this alloy | |
| EP0303957B1 (en) | Corrosion resisting alloy and corrosion resisting member | |
| EP0340789B1 (en) | Hot working aluminum base alloys | |
| CA1101699A (en) | High-strength, high-expansion manganese alloy | |
| EP0260465B1 (en) | Oxide dispersion-strengthened nickel-base superalloy with improved corrosion resistance | |
| DE3630321C2 (en) | ||
| US3515545A (en) | Refractory and ceramic brazing alloys | |
| JPS6130645A (en) | Tantalum-niobium-molybdenum-tangsten alloy | |
| EP0425972B1 (en) | Oxidation- and corrosion-resistant heat-resisting alloy, based on an intermetallic compound | |
| DE2712692A1 (en) | NICKEL-CHROME ALLOY |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
| AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE CH DE DK ES FR GB IE IT LI NL PT SE |
|
| 17P | Request for examination filed |
Effective date: 19951006 |
|
| RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: ASEA BROWN BOVERI AG |
|
| GRAG | Despatch of communication of intention to grant |
Free format text: ORIGINAL CODE: EPIDOS AGRA |
|
| 17Q | First examination report despatched |
Effective date: 19980717 |
|
| GRAG | Despatch of communication of intention to grant |
Free format text: ORIGINAL CODE: EPIDOS AGRA |
|
| GRAH | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOS IGRA |
|
| GRAH | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOS IGRA |
|
| GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
| AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AT BE CH DE DK ES FR GB IE IT LI NL PT SE |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SE Free format text: THE PATENT HAS BEEN ANNULLED BY A DECISION OF A NATIONAL AUTHORITY Effective date: 19990526 Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 19990526 Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRE;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.SCRIBED TIME-LIMIT Effective date: 19990526 Ref country code: ES Free format text: THE PATENT HAS BEEN ANNULLED BY A DECISION OF A NATIONAL AUTHORITY Effective date: 19990526 |
|
| REF | Corresponds to: |
Ref document number: 180517 Country of ref document: AT Date of ref document: 19990615 Kind code of ref document: T |
|
| REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
| REF | Corresponds to: |
Ref document number: 59309611 Country of ref document: DE Date of ref document: 19990701 |
|
| REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: GERMAN |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 19990826 Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 19990826 |
|
| GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 19990811 |
|
| ET | Fr: translation filed | ||
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 19991108 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 19991130 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 19991130 Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 19991130 |
|
| PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
| STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
| 26N | No opposition filed | ||
| BERE | Be: lapsed |
Owner name: ASEA BROWN BOVERI A.G. Effective date: 19991130 |
|
| REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
| REG | Reference to a national code |
Ref country code: IE Ref legal event code: FD4D |
|
| REG | Reference to a national code |
Ref country code: GB Ref legal event code: IF02 |
|
| REG | Reference to a national code |
Ref country code: GB Ref legal event code: 732E |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: CD Ref country code: FR Ref legal event code: CA |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: TP |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20081121 Year of fee payment: 16 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20081113 Year of fee payment: 16 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20081117 Year of fee payment: 16 |
|
| GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20091108 |
|
| REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST Effective date: 20100730 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20091130 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20100601 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20091108 |