EP0347614B1 - Ruthenium enthaltende Legierungen auf Eisenbasis für hochtemperaturbeanspruchte Bauteile - Google Patents

Ruthenium enthaltende Legierungen auf Eisenbasis für hochtemperaturbeanspruchte Bauteile Download PDF

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Publication number
EP0347614B1
EP0347614B1 EP19890109694 EP89109694A EP0347614B1 EP 0347614 B1 EP0347614 B1 EP 0347614B1 EP 19890109694 EP19890109694 EP 19890109694 EP 89109694 A EP89109694 A EP 89109694A EP 0347614 B1 EP0347614 B1 EP 0347614B1
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EP
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Prior art keywords
ruthenium
alloy
temperatures
high temperature
alloys
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Expired
Application number
EP19890109694
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English (en)
French (fr)
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EP0347614A1 (de
Inventor
Melvin Robert Jackson
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General Electric Co
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General Electric Co
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    • 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
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium

Definitions

  • the present invention relates generally to alloys formed for structural use at high temperatures. More particularly, it relates to an iron-base structural alloy having a novel ruthenium content and adapted to use at high temperatures. It is known that jet engines operate more efficiently at higher temperatures than at lower temperatures. Increase in the operating temperature of an engine can give the engine itself higher performance characteristics. One of the great difficulties in achieving higher operating temperatures in jet engines and in other gas turbines is the lack of materials for the building of engines which can tolerate such high temperatures.
  • one of the basic problems of increasing the operating temperature of engines is that of finding materials which have suitable combination of properties for use at the higher temperatures.
  • the temperatures of structural components in the hottest sections of such engines are envisioned to range from 1250°C (2300°F) to temperatures which are reached when stoichiometric ratios of gas and air are burned. As noted above, such temperatures are above the melting point of presently used nickel-base superalloys. Because of the distinct advantages in the operating at such elevated temperatures, efforts have been made to find alloys from which structural components for use at such temperatures can be formed. If such engines can be built, there is a reward of a greater thrust to weight ratio possible as an improvement over present designs.
  • compositions which have a desirable set of properties for use as structural elements in high temperature environments.
  • Another object is to provide a metal component which has the capability of operating in the temperature range of 1250°C (2300°F)or higher.
  • Another object is to provide a metal capable of providing structural elements within a jet engine for operation at very elevated temperatures.
  • Another object is to provide components of a jet engine capable of operating at very high temperatures.
  • Another object is to provide a composition capable of structural support in an operating environment at or above the melting point of the commonly used nickel-base superalloys.
  • a preferred composition of one of the other aspects of the invention has the following ranges of ingredients:
  • balance iron indicates that the other ingredient of the composition is predominantly iron. However it will be understood that impurities normally encountered in metal processing may be present as well.
  • compositional range is within the following compositional range:
  • Figure 1 is a graph in which the yield strength in MPa (ksi) is plotted against temperature in degrees centigrade and Fahrenheit for a number of compositions which contain various concentrations of ruthenium.
  • Figure 2 is a graph in which yield strength in MPa (ksi) is plotted against temperature for a number of compositions prepared by different methods and showing a contrast between the alloys which do not contain ruthenium and those that do.
  • Figure 3 is a photomicrograph in which samples of alloys as provided pursuant to the present invention are shown at high magnification.
  • the present invention concerns structural alloys which have solidification temperatures (1565.5° (2850°F) and which have use temperatures of 1250°C of (2300°F) and above.
  • One aspect of the invention rests on the discovery that the properties of a known high temperature material FeCrAlY can be strikingly improved by additions of RuAl as ingredients.
  • the alloys of Examples 1, 2, 3, and 4 were prepared by induction melting of four separate melts which were then each cast into ingots.
  • the alloy of Example 2 was machined in order to prepare test specimens of the sample but difficulties in machining the alloy of Example 2 resulted in the sample with 5 atomic percent ruthenium being eliminated from the testing accorded the alloys 1, 3 and 4.
  • the other three alloys could be machined and were machined to provide tensile test specimens.
  • the alloys of Examples 3 and 4 were tensile tested at temperatures from 860°C to 1160°C (1580°F to 2120°F). The results which were obtained from the tests are plotted in Figure 1. In this Figure, three different samples of alloy were tested at the temperatures indicated in the abscissa of the graph.
  • the FeCrAlY sample of Example 1 was tested and found to have the lowest yield strength in ksi at the temperatures tested as illustrated in Figure 1.
  • the sample containing 10 atomic percent ruthenium had a very distinct improvement in tensile strength and, as can be seen from the Figure, was more than twice as strong in this tensile property than the FeCrAlY alloy which contained no ruthenium.
  • the alloy MA956 is an oxide dispersion strengthened FeCrAlY alloy which has been mechanically alloyed through powdered metallurgy techniques and is supplied commercially by the International Nickel Company.
  • compositions containing the 10 and 15 atomic percent ruthenium are very strong and accordingly very valuable alloys.
  • microstructures of the alloys containing the 10 and 15 atomic percent ruthenium were obtained in a conventional fashion.
  • the photomicrographs of this microstructure are provided in Figure 3.
  • the upper figure, Figure 3A has a magnification of 260X and displays the composition with the 10 atomic percent ruthenium.
  • the lower portion of the figure, Figure 3B is at the same magnification and displays the microstructure of the sample containing 15 atomic percent ruthenium.
  • a large second phase is evident in the Figures and it was determined by analysis to be B-2 (body centered) structure (Ru,Fe)Al, normally identified as ⁇ .
  • the size and morphology of the second phase suggests that it is possible to achieve greater strength and ductility by refining the second phase grain size.
  • the FeCrAlYRu material may be directionally solidified, or potentially may be oxide dispersion strengthened (ODS treated) in a manner similar to the ODS MA956.
  • ODS treated oxide dispersion strengthened
  • Solidification temperatures for these materials are approximately 1570°C (2860°F) as compared to less than 1350°C (2460°F) for typical nickel-base superalloys.
  • the strength of the novel FeCrRuAlY alloy of this invention is shown in relation to materials prepared by casting and rapid solidification deposition in Figure 2. It is evident from this figure that incorporation of the ruthenium aluminum in the FeCrAlY alloy results in a very significant increase in the tensile strength of the alloy. In general cast alloy tends to be coarse grained and rapidly solidified plasma deposited (RSPD) alloy tends to be fine grained. This difference in grain structure accounts for a small part of the differences in properties of materials prepared by the two different methods.
  • RSPD rapidly solidified plasma deposited

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Heat Treatment Of Steel (AREA)
  • Powder Metallurgy (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)

Claims (4)

  1. Legierung enthaltend die folgenden Konzentrationsbereiche von Bestandteilen:
    Figure imgb0010
  2. Zusammensetzung nach Anspruch 1 mit den folgenden Bereichen der Bestandteile
    Figure imgb0011
  3. Zusammensetzung nach Anspruch 1 mit den folgenden Bereichen der Bestandteile
    Figure imgb0012
  4. Bauteil zum Einsatz in Hochtemperatur-Strahltriebwerken, die bei sehr hohen Temperaturen arbeiten, wobei das Bauteil aus einer Zusammensetzung nach irgendeinem der Ansprüche 1 bis 3 gebildet ist.
EP19890109694 1988-06-20 1989-05-30 Ruthenium enthaltende Legierungen auf Eisenbasis für hochtemperaturbeanspruchte Bauteile Expired EP0347614B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US20890588A 1988-06-20 1988-06-20
US208905 1988-06-20

Publications (2)

Publication Number Publication Date
EP0347614A1 EP0347614A1 (de) 1989-12-27
EP0347614B1 true EP0347614B1 (de) 1992-09-23

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Family Applications (1)

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EP19890109694 Expired EP0347614B1 (de) 1988-06-20 1989-05-30 Ruthenium enthaltende Legierungen auf Eisenbasis für hochtemperaturbeanspruchte Bauteile

Country Status (3)

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EP (1) EP0347614B1 (de)
JP (1) JPH02182865A (de)
DE (1) DE68902957T2 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7794652B2 (en) * 2004-12-27 2010-09-14 The Argen Corporation Noble dental alloy
US11427894B2 (en) 2019-08-02 2022-08-30 The Argen Corporation Cobalt based platinum-containing noble dental alloys

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4018569A (en) * 1975-02-13 1977-04-19 General Electric Company Metal of improved environmental resistance
EP0091989A1 (de) * 1982-04-15 1983-10-26 The Furukawa Electric Co., Ltd. Legierung mit hoher Permeabilität

Also Published As

Publication number Publication date
DE68902957T2 (de) 1993-04-15
EP0347614A1 (de) 1989-12-27
JPH02182865A (ja) 1990-07-17
DE68902957D1 (de) 1992-10-29

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