EP1505165A1 - Legierungen für Verwendung bei hohen Temperaturen, daraus hergestellte Gegenstände und Verfahren zum Reparieren von Gegenständen - Google Patents

Legierungen für Verwendung bei hohen Temperaturen, daraus hergestellte Gegenstände und Verfahren zum Reparieren von Gegenständen Download PDF

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Publication number
EP1505165A1
EP1505165A1 EP04254572A EP04254572A EP1505165A1 EP 1505165 A1 EP1505165 A1 EP 1505165A1 EP 04254572 A EP04254572 A EP 04254572A EP 04254572 A EP04254572 A EP 04254572A EP 1505165 A1 EP1505165 A1 EP 1505165A1
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EP
European Patent Office
Prior art keywords
alloy
article
ruthenium
chromium
component
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.)
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Application number
EP04254572A
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English (en)
French (fr)
Inventor
Ji-Cheng Zhao
Melvin Robert Jackson
Liang Jiang
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General Electric Co
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General Electric Co
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Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP1505165A1 publication Critical patent/EP1505165A1/de
Withdrawn legal-status Critical Current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
    • C22C5/00—Alloys based on noble metals
    • C22C5/04—Alloys based on a platinum group metal

Definitions

  • the present invention relates to materials designed to withstand high temperatures. More particularly, this invention relates to heat-resistant alloys for high-temperature applications, such as, for instance, gas turbine engine components of aircraft engines and power generation equipment. The present invention further relates to methods for repairing articles for high temperature applications.
  • nickel-based superalloy is widely accepted in the art to mean that the element upon which the alloy is “based” is the single largest elemental component by atom fraction in the alloy composition.
  • conventional superalloys used in gas turbine airfoils often operate at the upper limits of their practical service temperature range.
  • bulk average airfoil temperatures range from about 900°C to about 1000°C, while airfoil leading and trailing edge and tip temperatures can reach about 1150°C or more. At such elevated temperatures, the oxidation process consumes conventional superalloy parts, forming a weak, brittle metal oxide that is prone to chip or spall away from the part.
  • the performance of alloys commonly used for repair is comparable or inferior to that of the material of the original component, depending upon the microstructure of the repaired material, its defect density due to processing, and its chemistry.
  • the original edge material is made of the same material as the rest of the original blade, often a superalloy based on nickel or cobalt. Because this material was selected to balance the design requirements of the entire blade, it is generally not optimized to meet the special local requirements demanded by conditions at the airfoil leading or trailing edges. However, maximum temperatures, such as those present at airfoil tips and edges, are expected in future applications to be over about 1300°C, at which point many conventional superalloys begin to melt. Clearly, new materials for repair and manufacture must be developed to improve the performance of repaired components and to exploit efficiency enhancements available to new components designed to operate at higher turbine operating temperatures.
  • One embodiment is an alloy comprising, in atom percent, at least about 50% rhodium (Rh); at least about 5% of a metal selected from the group consisting of platinum (Pt), palladium (Pd), and combinations thereof; from about 5% to about 24% ruthenium (Ru); and from about 1% to about 40% chromium (Cr); wherein the alloy comprises less than about 50% by volume of an A3-structured phase, and wherein the quantity defined by the expression ([Cr] + 2[Ru]) is in the range from about 25% to about 50%, where [Ru] and [Cr] are the atom percentages of ruthenium and chromium in the alloy, respectively.
  • Another embodiment is an article for use in a high temperature, oxidative environment, comprising the alloy of the present invention.
  • a third embodiment is a method for repairing an article.
  • the method comprises providing an article, providing a repair material comprising the alloy of the present invention, and joining the repair material to the article.
  • the description herein employs examples taken from the gas turbine industry, particularly the portions of the gas turbine industry concerned with the design, manufacture, operation, and repair of aircraft engines and power generation turbines.
  • the scope of the invention is not limited to only these specific industries, as the embodiments of the present invention are applicable to many and various applications that require materials resistant to high temperature and aggressive environments.
  • the temperature range of interest where statements and comparisons are made concerning material properties is from about 1000°C to about 1300°C.
  • the term "high temperature” as used herein refers to temperatures above about 1000°C.
  • the alloy of the present invention balances several competing material requirements, including, for example, cost, strength, ductility, and oxidation resistance.
  • the alloy comprises, in atom percent, at least about 50% rhodium (Rh), at least about 5% of a metal selected from the group consisting of platinum (Pt), palladium (Pd), and combinations thereof, from about 5% to about 24% ruthenium (Ru), and from about 1% to about 40% chromium (Cr).
  • the alloy comprises less than about 50% by volume of an A3-structured phase, which is a solid solution containing, among other elements, Ru and Cr, and is commonly referred to in the art as "epsilon phase," or ⁇ .
  • the composition of the alloy is maintained such that a quantity defined by the expression ([Cr] + 2[Ru]) is in the range from about 25% to about 50%, where [Ru] and [Cr] are the atom percentages of ruthenium and chromium in the alloy, respectively.
  • the present inventors have discovered a material having suitable high temperature strength (due to solution strengthening obtained from the alloying elements, and in some cases further strengthening due to the presence of the A3-structured phase) with sufficient ductility (due to the substantial proportion of the A1-structured phase) to be formed into useful shapes.
  • the cost of the alloy is reduced by adding these alloying elements to the Rh without reducing the oxidation resistance of the material below required levels.
  • Pd is less expensive and less dense than Pt, and so in many applications where weight and cost are important considerations, optimal compositions often minimize the use of Pt in favor of Pd. However, Pt may be used in place of some or all of the Pd addition where very high environmental resistance is desired above all other characteristics.
  • the mix of the above properties and others such as modulus of elasticity can be controlled by varying the relative proportions of constituent elements.
  • Cr additions tend to lower the alloy density while increasing the thermal expansion coefficient
  • Ru additions tend to increase strength and modulus.
  • maintaining the Cr and Ru in accordance with the expression described above controls the amount of A3-structured phase in the alloy, allowing further control over the strength and ductility of the material.
  • the alloy comprises, in atom percent, from about 7% to about 20% ruthenium, and from about 1% to about 25% chromium.
  • the alloy comprises, in atom percent, from about 8% to about 20% ruthenium, and from about 1% to about 10% chromium. Maintaining alloy composition within these ranges tends to minimize the amount of A3-structured phase, thereby maximizing the ductility, and therefore the formability, of the alloy.
  • Alloys set forth herein as embodiments of the present invention are suitable for production using any of the various known methods of metal production and forming.
  • Conventional casting, powder metallurgical processing, directional solidification, and single-crystal solidification are non-limiting examples of methods suitable for forming ingots of these alloys.
  • Thermal and thermo-mechanical processing techniques common in the art for the formation of other alloys, including, for instance, forging and heat treating, are suitable for use in manufacturing and strengthening the alloys of the present invention.
  • the article comprises the alloy described above.
  • the article may be one that has been repaired, or it may be a newly manufactured article.
  • the article comprises a component of a gas turbine engine, such as, for example, a turbine blade, vane, or a combustor component.
  • a vane or a blade comprises an airfoil 10, which comprises multiple component sections, including a blade tip 11 (in the case where the component is a blade), a leading edge 12, and a trailing edge 13.
  • the alloy of the present invention may be suitably disposed anywhere on the component, including, in certain embodiments, at one or more of the above component sections.
  • the article comprises a coating disposed on a substrate, and the coating comprises the alloy.
  • the alloy of the present invention minimizes certain drawbacks of alloys comprising significant amounts of platinum group metals such as, for example, ruthenium, rhodium, and palladium, including their high cost and high density in comparison to conventional airfoil materials.
  • These drawbacks have a reduced effect on the overall component because the comparatively expensive and dense alloy (relative to conventional superalloys) comprises only a fraction of the overall surface area of the component. The properties of the component are thus "tailored" to the expected localized environments, reducing the need for compromise during the design process and increasing the expected operating lifetimes for new and repaired components.
  • a further embodiment of the present invention is a method for repairing an article.
  • an article in this method, comprises a component of a gas turbine engine, including, for example, a blade, a vane, or a combustion component.
  • a repair material is provided, and this repair material comprises the alloy described above for previous embodiments of the present invention.
  • This repair material is joined to the article. In some embodiments, joining is accomplished, at least in part, by disposing a coating comprising the repair material onto the article being repaired. Suitable methods for disposing the coating include, for example, thermal spraying, plasma spraying, HVOF spraying, and laser deposition.
  • the repair material is joined to the substrate by one or more conventional joining processes, including, for example, welding, brazing, or diffusion bonding. Regardless of whether the repair material is in the form of a coating or a solid section, it may be disposed at any section of the article deemed to require the performance characteristics of the repair material. These sections include, for example, the leading and trailing edges of airfoils, and blade tips.

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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)
  • Manufacture And Refinement Of Metals (AREA)
EP04254572A 2003-08-07 2004-07-30 Legierungen für Verwendung bei hohen Temperaturen, daraus hergestellte Gegenstände und Verfahren zum Reparieren von Gegenständen Withdrawn EP1505165A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US10/636,407 US20050031482A1 (en) 2003-08-07 2003-08-07 Alloys for high temperature applications, articles made therefrom, and method for repair of articles
US636407 2003-08-07

Publications (1)

Publication Number Publication Date
EP1505165A1 true EP1505165A1 (de) 2005-02-09

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EP04254572A Withdrawn EP1505165A1 (de) 2003-08-07 2004-07-30 Legierungen für Verwendung bei hohen Temperaturen, daraus hergestellte Gegenstände und Verfahren zum Reparieren von Gegenständen

Country Status (6)

Country Link
US (1) US20050031482A1 (de)
EP (1) EP1505165A1 (de)
JP (1) JP2005054271A (de)
BR (1) BRPI0403208A (de)
CA (1) CA2476014A1 (de)
SG (1) SG109007A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2514361C1 (ru) * 2013-06-14 2014-04-27 Юлия Алексеевна Щепочкина Сплав

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7208232B1 (en) * 2005-11-29 2007-04-24 General Electric Company Structural environmentally-protective coating
RU2502815C1 (ru) * 2012-12-18 2013-12-27 Юлия Алексеевна Щепочкина Сплав для изготовления монет
GB201620687D0 (en) * 2016-12-05 2017-01-18 Johnson Matthey Plc Rhodium alloys

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6582534B2 (en) * 2001-10-24 2003-06-24 General Electric Company High-temperature alloy and articles made therefrom

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0025200D0 (en) * 2000-10-13 2000-11-29 Xeikon Nv Toner composition
US6623692B2 (en) * 2001-08-29 2003-09-23 General Electric Company Rhodium-based alloy and articles made therefrom
US6554920B1 (en) * 2001-11-20 2003-04-29 General Electric Company High-temperature alloy and articles made therefrom

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6582534B2 (en) * 2001-10-24 2003-06-24 General Electric Company High-temperature alloy and articles made therefrom

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2514361C1 (ru) * 2013-06-14 2014-04-27 Юлия Алексеевна Щепочкина Сплав

Also Published As

Publication number Publication date
US20050031482A1 (en) 2005-02-10
CA2476014A1 (en) 2005-02-07
SG109007A1 (en) 2005-02-28
BRPI0403208A (pt) 2005-05-24
JP2005054271A (ja) 2005-03-03

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