CA2414019A1 - High temperature-resistant component - Google Patents

High temperature-resistant component Download PDF

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Publication number
CA2414019A1
CA2414019A1 CA 2414019 CA2414019A CA2414019A1 CA 2414019 A1 CA2414019 A1 CA 2414019A1 CA 2414019 CA2414019 CA 2414019 CA 2414019 A CA2414019 A CA 2414019A CA 2414019 A1 CA2414019 A1 CA 2414019A1
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CA
Canada
Prior art keywords
component
weight
superalloy
ruthenium
nickel
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.)
Abandoned
Application number
CA 2414019
Other languages
French (fr)
Inventor
Ralf Buergel
Winfried Esser
Joern Grossmann
Wolfgang Hermann
Hael Mughrabi
Juergen Preuhs
Florian Pyczak
Alfred Scholz
Robert Singer
Andreas Volek
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.)
Siemens AG
Doncasters Precision Castings Bochum GmbH
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Publication of CA2414019A1 publication Critical patent/CA2414019A1/en
Abandoned legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Crystals, And After-Treatments Of Crystals (AREA)

Abstract

High-temperature-resistant component, and process for producing the high-temperature-resistant component The invention relates to a high-temperature-resistant component (1) made from a nickel-base superalloy having the following composition, in percent by weight: 9-11%
of Cr, 3-5% of W, 0,5-2.5% of Mo, 3-5% of A1, 3-5% of Ti, 3-7% of Ta, 1-5% of Re, remainder nickel. The invention also relates to a corresponding component (1) with an alloy composition corresponding to the composition described above except for the rhenium content being replaced by 0.1-5% by weight of ruthenium.

Description

nescription High-temporatu~re-resistant component ~rhe invention relates L~ a high-tQrnperature--resp.stant component madelfrom a nickel-base superalloy.
DE 23 33 775 F3~Z has described a process for the heat treatment of a~ nickel alloy. The nickel alloy consists o.f, up to 0. 3% ~ of carbon, 11-~.5% of chromium, B-1.2% of cobalt, :1-2.5 of molybdenum. 3-10% of tungsten, 3.5-10% of taut lum, 3.5-4.5% of titanium, 3-9% of aluminum, 0. 05-0.025% of boron, 0.05-0.4% of zirconium, re finder nickel. Furthermore, the alloy additionally contains 0.01-3% oI hafnium, and a suitable heat treatment producQS a block-type carbide formation and a finely dispQrsed precipitation of an Ni3(A1,T1) phase. This document do~a not claim any addition of rhenium or. ruthenium.
US-A-5, 6J"1, 670 ~ has disclosed a rotor blade for a gas turbine. The ~ rotor b.l.ade has a singJ.e-crystalline platform area and a single-crystalline blade part. A
sprur.ing area of the blade is designed with a directionally olidificd Structure. The blade is cast from a superal vy which has the following composition, in percent by weight: up to 0.2% of carbon, 5-1.4% of chromium, 4-7% of aluminum, 2-15% of tungsten, 0_5-5%
of r..ilanium, up to 3$ of niobium, up to 6~ of molybdenum. up to 12% or~ tantalum, up to 10.5% of cobalt, up to .$ of hafnium, up to 4% of xhenium, up to 0.035% of bore , up to 0.035% o.f zirconium, remainder nickel. ThQSe fide range details are used to describe alloy composit:j ons which are in principle suitable for the gas turbin blade proposed, but do cwl indicate any composition ra ge that is suitable for achieving a particular res'stance to oxidation and corrpsion or strength.
EP 0 29~I 785 1 has disclosed a nickel-base superalloy for single cr stals. ~'he superalloy has the following composition, . n percent by weight: 6-15% of chromium, 5-12% of to ggten, 0.01-4'b of rhenium, 3-9% of tantalum, 0.5 2% of titanium. 4-7% at aluminum and optionally 0 5-3% of molybdenum. This superalloy produces both a high resistance to cracking at high temperatures nd a resistance to corrasi~rt. In order not to advers 1y affect the resistanc:o to c:~rrosion, tho titanium c~c~Lpnt must not exceed 2% by weight.
US-A-5,122,206 has described a nickel-base superalloy which has a articularly narrow coexistence zone for the solid ~nd liquid phases and is therefore particular7,y uitable for a single-crystal casting process. The lloy has tho following composition, in percent by w ight: 10-30'~ of chromium, 0.1-5% of niobium, 0.1-8 of titanium, 0.1-a% of aluminum, 0.05-~0 0..5% of copp r or, instead of copper, 0.1-3% of tantalum: in he former case, hafnium or rhenium may optionally als be presont in an amount of from 0.05-3~, and in the latter cage 0.05-0.5% of copper may also ba present ins ead of rhenium or hafnium. Furthermore, 75 0.05-3% of mo ybdenum ox tungsten may optionally also be present.
WO 01/09403 H1 describes a nickel-base alloy comprising 21-13% o.t eh omium, 3-5% of tungston, 0.5-2.5% of 30 molybdenum, 3-. % of aluminum, 3w5~5 of titanium, 3-7% of tantalum, 0-12 oL cobalt, 0-1% of niobium, 0-2% of hafnium, 0-1% f zircon~.um, 0-0.05% of boron, 0-0.2% of carbon, 1-5~ o rhenium, 0-5% of ruthenium, remainder.
nickel. The ormation of embrittling intermetallic 35 phases (Cr- an /or Re-containing precipitations), which is prompt~d b rhenium, 3.eadd to a reduction in thca service life,l since the brittle phases promote crank L~rmation.
The invrantion~ is basr~d on the object of providing a component mad from a nickel-base superalloy which has particularly avorable propert,ic~r~ with a view to its ability to wi hstand high temperatures, its resistance to oxidation and corrosion and its stability with respect to the ductiJ.ity~reducing formation of intermetallic; phases, together with a long service life.
According to he invention, the object relating to a component a.s chi.eved by the description of a high-temperature-re istant component m:~de from a nickol-base superalloy, t a composition of which comprises the following elem nts, in percent by weight:
9 -- 11~ of chr. mium, 3 - 5~ of lung ten, 0.5 - 2.5~s of olybdenum, 3 - Sø of alum num, 3 - 5~ of tits ium, 3 - 7$ of taut lum, 1 - 5~ oI rhen um, remainder nick 1 and impurities.
The composition of the superalloy of the given components has Lor the first time been specifiQd in such a way that the component has particularly favorable pry rties with rQgard Lo its ability to withstand hi h temperatures. its resistance to oxidal.ion and corrosion and with regard to stability with respect o the formation of ductility-reducing intermetallic bases. It was possible to discover the specif:.c compo ition described, which satisfies. the dPS:ired proper ies mentioned above to a surprisingly high degree, b means of extensive tests which preceded _ q the invention In particular, the invention is based on a chromium-ri h superalloy which acquires an a.ncreased strength thro gh the addition of rhenium. The formation of, embrittl.i. g i,ntermetallic phases (Cr-containing and/or Re-con.aining preaipitat.ian~), which is prom~Led by rhenium, s cone rolled by a chromium content of belaw 11~s .
The rhenium content is preferably at least 2~ by weight I.
IL is prefe able f.or the superalloy to contain ruthenium. Th addition of ruthenium makes it possible in particular Lo further reduce the likelihood of embrittling i termc:tal7ic phases being formed. The addition of ruthenjum has proven favorable in particular, for a rtlenium content of over 2~ by weight.
In this cas , the maximum ruthenium content is preferably 3~ by weight and Lhe: minimum ruthenium contQnt 0.1& by weight. The cobalt content us the superalloy is referably up to 12$ by weight.
It a.s preferable Lor the superalloy to contain at most l~s by weight o niobium.
Tt is preferable for. the superalloy optionally to contain at Iea t one of the followirrg elements:
0 - 2$ by weig t of hafnium, 0 - 1~ by weig t of z~.rconium, 0 - 0.05 by w fight of boron, 0 - 0.2~ by wei ht of carbon.
According to 1. a invention, the object relating to a Component is lso aohie~~d by the description of a high-temperatur -resistant component made from a 2.00121779 ' I - 5 -nicks l-ba.ee superdlloy, the composition of which comprises the,following elemQnts, in percent by weight;
9 - 11% of ch omium, 3 - 5% of tun s~ton, 0.5 - 2.5% of molyk~denum, 3 - 5~ of al inum, 3 - 5% of tit ium, 3 - 7% of tan alum, 0.1 - 5% of r thsnium, romaa.nder nic 7. and impurities.
The advantage of such a component will result ~n a corresponding way to the statements made above in connection wi h the advantages o:f the component which includes xhen um. Surprisingly, a particularly high abia.ity to w thsrand high temperatures can also be achieved by t a addition of ruthenium and without a rhenium Conten , while with the composition listed the registanc;e to oxidatlon/corrosion is also high at the game time.
It is prefer ble for the cobalt content of the superalloy to be less than 12~s by weight, while the niobium conte t is at moat 1% by weight. It is preferable for Lhe superalloy to contain 0-2~ by weight of hafnium and or 0-7.$ by weight of zirconium and/or 0-0.05% by weig t of boron and/or 0-0.2% by weight of ca rbon .
structure of ihi.s type, the grain boundaries are oriented subst dally along one axi 9. This results in a particularly igh strength along this axis.
The component ~refsrably has a directionally so~.idified grain structu e. In a directionally solidified It is prefer ble fo.r the r:~mponent to have a single-crystalli.ne s ructt~re. The single-crystalline structure avoids stren th-reducing grain boundaries in the component and results in a particularly high strength.
It is prefers le for the componEnt to be designed as a gas tuxbine b ade or vane. In particular a gas turbine blade or vane is subject to particularly high demands with regard t high-temper, ature strength and resisl:ance to oxidation/c rrosion.
l~he yes Curb ne blade or vane has been produced in directionally solidified form in a casting process, resulting in rain boundaries which are oriented along a blade or van. axis.
The gas turbine blade or vane has been produced from a nicke3.-base $uperalloy which has one of thQ
compositions.
In particu7.ar,' a cobalt content of between 6 and 10$
and a zirconi to contQnt of between 4 and 0.1% are advantageous.
Advantageous compositions axe given, for example, by:
~ Cr: 10.25%, ~o: 1.85%, W: 4.70, Co: 6.50%, Ti: 3.75%, Ta: 3.9%, 1. 3.3%, B: 0.0125$. 2r: 0.008%, Hf:
<0.01%: Re: .5%, remainder Ni.
~ Cr: 9.00%, M ; 1.85%, W: 9.70, Co: 6.50$, Ti: 3.75%, Ta: 3.9~k, . 3.3$, $: 0.0125$, Zr: 0.008~C, Hf:
<0.01%, Re: .5%, remainder Ni.
Cr: 10.75%, o: 1.85$r W: 4.70, Ca: 6.50%, Ti: 3.75~A, Ta: 3.9%, A : 3.3%, B: 0.0125%, Zr: 0.008, FIf:
<0.01%, Re: .5%, Ru: 2.0%, remainder Ni_ ~ Cr: 10.25%, Mo: 1.85%, W: 4.7U, Co: 8.50%, Ti: 3.75%, Ta: 3.9%, IA1: 3.3%, B: 0.0125%, Zr: 0.008%, Hf:
<0.01%, Ru: 1.5%, remainder Ni.
~ Cr: 10.75%, Mo: 1.85%, W: 4.70, Co: 8.50%, Ti: 3.?5~, Ta: 3.9%, A1: 3.3%, B: 0.012.5%, Zr: 0.008%, Ilf:
<0.01~, Ru: 3.75%, remainder Ni..
~ Cr: 10.25$, Mo: 1.85%, W: 4.'10, Ca: 8.50%, Ti: 3.75%, '1'a: 3.9%, A~; 3.3%, B: 0.0125%, Zr: 0.008%, Hf:
<O.U1~, Re: 2.00%, Ru: 2.h, remainder Ni.'

Claims (9)

1. A high-temperature-resistant component made from a nickel-base superalloy, the composition of which comprises the following elements, in percent by weight:
9 - 11% of chromium 3 - 5% of tungsten 0.5 - 2.5% of molybdenum 3 - 5% of aluminum 3 - 5% of titanium 3 - 7% of tantalum 0 - 12% of cobalt 0 - 1% of niobium 0 - 2% of hafnium 0 - 1% of zirconium 0 - 0.05% of boron 0 - 0.2% of carbon 1 - 5% of rhenium 0 - 5% of ruthenium, remainder Ni and impurities.
2. The component as claimed in claim 1, in which the rhenium content is at least 2% by weighs.
3. The component as claimed in claim 1, having a maximum ruthenium content of 3% by weight in the superalloy.
4. The component as claimed in claim 1 or 3, having a minimum ruthenium content of 0.1% by weight, in particular 0.5% by weight, in the superalloy.
5. A high-temperature-resistant component made from a nickel-base superalloy, the composition of which comprises the following elements, in percent by weight:

9 - 11% of chromium 3 - 5% of tungsten 0.5 - 2.3 % of molybdenum 3 - 5% of aluminum 3 - 5% of titanium 3 - 7% of tantalum 0 - 12% of cobalt 0 - 1% of niobium 0 - 2% of hafnium 0 - 1% of zirconium 0 - 0.05% of boron 0 - 0.2% of carbon 0.1 - 5% of ruthenium, remainder Ni and impurities.
6, The component as claimed in one of the preceding claims, which has a directionally solidified grain structure (9).
7. The component as claimed in one of claims 1 to 5, which has a single-crystalline structure.
8. The component as claimed in one of claims 1 to 5, which has an isotropic: distribution of the orientations of the grain Structure.
9. The component as claimed in one of the preceding claims, which is designed as a gas turbine blade or vane.
CA 2414019 2001-12-13 2002-12-13 High temperature-resistant component Abandoned CA2414019A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP01129743A EP1319729B1 (en) 2001-12-13 2001-12-13 High temperature resistant part, made of single-crystal or polycrystalline nickel-base superalloy
EP01129743.9 2001-12-13

Publications (1)

Publication Number Publication Date
CA2414019A1 true CA2414019A1 (en) 2003-06-13

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Country Status (4)

Country Link
EP (1) EP1319729B1 (en)
JP (1) JP2003193161A (en)
CA (1) CA2414019A1 (en)
DE (1) DE50112339D1 (en)

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