EP0347614A1 - 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
EP0347614A1
EP0347614A1 EP89109694A EP89109694A EP0347614A1 EP 0347614 A1 EP0347614 A1 EP 0347614A1 EP 89109694 A EP89109694 A EP 89109694A EP 89109694 A EP89109694 A EP 89109694A EP 0347614 A1 EP0347614 A1 EP 0347614A1
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EP
European Patent Office
Prior art keywords
ruthenium
alloy
ingredient
high temperature
temperatures
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
EP89109694A
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English (en)
French (fr)
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EP0347614B1 (de
Inventor
Melvin Robert Jackson
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.)
General Electric Co
Original Assignee
General Electric Co
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Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP0347614A1 publication Critical patent/EP0347614A1/de
Application granted granted Critical
Publication of EP0347614B1 publication Critical patent/EP0347614B1/de
Expired 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
    • 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.
  • compositions which have a desirable set of properties for use as structural elements in high tempera­ture environments.
  • 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.
  • objects of the invention can be achieved by providing an alloy containing the following ingredients in approximate weight percent Range of Concentrations in Atomic % Ingredient From About To About Iron Balance Chromium 16 24 Ruthenium 4 20 Aluminum 16 30
  • a preferred composition of one of the other aspects of the invention has the following ranges of ingredients: Range of Concentrations in Atomic % Ingredient From about To about Iron Balance Chromium 15 20 Ruthenium 10 16 Aluminum 20 30 Yttrium 0 0.2
  • balance iron indicates that the other ingredients of the composition are predominantly iron. However it will be understood that other ingredients which do not detract from the beneficial properties of the alloy including impurities normally encountered in metal processing may be present as well.
  • compositional range Range of Concentrations in Atomic % Ingredient From about To about Iron Balance Chromium 15 20 Ruthenium 13 15 Aluminum 24 30 Yttrium 0 0.2
  • the present invention concerns structural alloys which have solidification temperatures about 2850°F and which have use temperatures 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 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)
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 true EP0347614A1 (de) 1989-12-27
EP0347614B1 EP0347614B1 (de) 1992-09-23

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19890109694 Expired EP0347614B1 (de) 1988-06-20 1989-05-30 Ruthenium enthaltende Legierungen auf Eisenbasis für hochtemperaturbeanspruchte Bauteile

Country Status (3)

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2421513A (en) * 2004-12-27 2006-06-28 Argen Corp Dental alloys containing chromium and ruthenium
US11427894B2 (en) 2019-08-02 2022-08-30 The Argen Corporation Cobalt based platinum-containing noble dental alloys

Citations (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

Patent Citations (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

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2421513A (en) * 2004-12-27 2006-06-28 Argen Corp Dental alloys containing chromium and ruthenium
GB2421513B (en) * 2004-12-27 2007-04-04 Argen Corp Noble dental alloy
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

Also Published As

Publication number Publication date
EP0347614B1 (de) 1992-09-23
DE68902957T2 (de) 1993-04-15
JPH02182865A (ja) 1990-07-17
DE68902957D1 (de) 1992-10-29

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