CN1150826A - Nickel-aluminium intermetallic basis alloy - Google Patents

Nickel-aluminium intermetallic basis alloy Download PDF

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Publication number
CN1150826A
CN1150826A CN95193622A CN95193622A CN1150826A CN 1150826 A CN1150826 A CN 1150826A CN 95193622 A CN95193622 A CN 95193622A CN 95193622 A CN95193622 A CN 95193622A CN 1150826 A CN1150826 A CN 1150826A
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atom
chromium
alloy
tantalum
nial
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CN95193622A
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CN1044493C (en
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格哈特·索瑟夫
本尼迪克特·佐莫
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Siemens AG
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Starc Co
Siemens AG
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    • 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
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A nickel-aluminium intermetallic basis alloy has a structure mainly made of the binary phase NiAl and further contains the elements chromium and tantalum. The total proportion of the elements chromium and tantalum amounts to maximum 12 % by atoms. The preferable content ranges lie from 0.3 to 3.8 % by atoms tantalum and from 1.0 to 9.0 % by atoms chromium. The nickel-aluminium intermetallic basis alloy is characterised in particular by a high oxidation resistance at high temperatures, such as 1350 DEG C. It is therefore suitable for producing pieces exposed to a high and continuous thermal stress, such as gas turbine blades. This high oxidation resistance allows additional anti-oxidation layers to be dispensed with.

Description

Intermetallic nickel-aluminum base alloy
The present invention relates to a kind of intermetallic nickel-aluminum base alloy, it has binary phase NiAl.In addition, the invention still further relates to the application of this intermetallic nickel-aluminum base alloy.
In DE-AS1812144, introduced a kind of high-intensity method made from nickel aluminum of good oxidation.By this method, nickel powder mixes with aluminium powder, then compacting and cooling strain, thus form a kind of self-supporting and unitary molded body with fibrous texture or layered structure.The composition of nickel is at least 80%, and the composition of aluminium is up to 20%.This unitary molded body is thermal distortion under each high temperature successively and then.In nickel, except the sosoloid of aluminium, also mainly form compound N i in this case 3Al.This sosoloid and compound N i 3Al can be proved by X-ray analysis.Adopt this method other the compound that between nickel and aluminium, what can produce, from design procedure, have no way of learning.
The objective of the invention is to improve a kind of thermomechanical property of alumel.Mainly be meant hot strength, scale resistance and thermal-shock resistance here.Another object of the present invention is the application that provides the alumel after doing so to improve.
The objective of the invention is to realize by a kind of intermetallic nickel-aluminum base alloy that it mainly contains binary phase NiAl and also additional in addition chromium and tantalum is arranged, wherein, the total content of chromium and tantalum is 12 atom % to the maximum.The composition of binary phase NiAl is preferably between 70 to the 95 atom %, especially between 85 to 90 atom %.The optimum content scope of tantalum or chromium is 0.3 to 3.8 atom % or 1.0 to 9.0 atom %.In such scope, preferably adopt the tantalum of 0.3 to 0.9 atom % and the chromium of 1.0 to 3 atom %, or the chromium of the tantalum of 1.7 to 3.0 atom % and 6.0 to 9.0 atom %.
The ratio of tantalum and chromium is preferably 1: 3 or is littler in this case.Adopt such ratio, the concentration of substitutional element reaches maximum value in NiAl.By adding tantalum and chromium, produce thick polynary Laves' phases on the crystal boundary of meeting binary phase NiAl in the intermetallic nickel aluminum base alloy and separate out, wherein have element Ni, Al, Cr and Ta.In addition, separate out tiny Laves' phases and α-chromium in NiAl crystal grain inside.In this case, organize best by the Laves' phases of 5 to 11 volume %, the precipitate of 3 to 10 volume % and all the other are formed for NiAl in NiAl.Confirmed already particularly advantageously to be, in tissue, contain the about 11 volume % Laves' phases on the crystal boundary add and in NiAl about 10 volume % precipitates and all the other be NiAl.
If in this alloy, additionally contain at least a element in iron, molybdenum, tungsten and the hafnium family, quantity each to 1 atom %, but total amount then can further be improved certain performance when being no more than 3 atom %.In addition, alloy may have the impurity that tracer element such as oxygen, nitrogen and sulphur and manufacturing cause.
By adding tantalum and chromium, form thick or thin polynary Laves' phases and the α-chromium mentioned by above-mentioned content range.These are separated out usually and can find on the wedge point (Zwickelpunkten) of different NiAl crystal grain.If alloying element tantalum or chromium are higher than illustrated amount, may cause with undesirable degree increase amount of separating out.When the volume content of Laves' phases increases too consumingly, form a kind of cellular tissue, wherein Laves' phases plays parent.Laves' phases content is excessive in tissue, intermetallic alloy is become fragile and very poor in processability.
One or more elements by adding iron, molybdenum, tungsten, niobium and hafnium family are respectively to 1 atom %, but total amount is no more than 3 atom %, and the intensity in the time of can obtaining short-time load increases.Certainly creep strength has reduced.By adding hafnium, after corrosion for the first time, impel and improve adhering to of zone of oxidation.
For reaching the purpose that proposes by the use that the present invention is directed to alloy, be member such as the gas turbine blade that NiAl base alloy is used to make structural member, the especially high-temperature load of internal combustion turbine.The member that internal combustion turbine is made by this basic alloy is turbine vane especially, because its high resistance of oxidation, thereby be particularly suitable for life-time service at high temperature, for example be higher than 1100 ℃, especially under 1350 ℃ situation.When adopting the member of this basic alloy system, different with super superalloy, according to different its not coatings of the additional band protective layer of needs that requires.Need not to lay the made turbine vane of extra play in the above by a kind of unified alloy composition, can produce very easily, compare, broken away from the difficulty that between each layer, connects with the turbine vane of forming by multilayer.
Generally speaking, this intermetallic nickel-aluminum base alloy also is suitable for as the material of making these article, that is, they must have in high strength, high heat resistance, good toughness, good scale resistance and the good heat resistanceheat resistant hits ability.Wherein, at room temperature, hot strength is higher than 600MPa when 0.2% yield-point.When 0.2% yield-point, the high-temperature capability under 800 ℃ is higher than 200MPa, and is higher than 90MPa in the time of 1000 ℃.Toughness is at least 7MPa/m, and oxidation-resistance is 5*10 at the order of magnitude -14g 2Cm -4S.
Below by means of describing this intermetallic nickel-aluminum base alloy for example in detail.
The alloying constituent of being studied (by atomic percent) is illustrated in the following table 1.
Table 1
???Ni ??Al ??Ta ??Cr Other
SSM364 ?45.00 ?45.00 ?2.50 ?7.5
VA2823 ?44.50 ?44.50 ?2.50 ?8.00 0.39Fe，0.105C
USM?2823 ?44.40 ?43.90 ?2.90 ?8.50 0.14Fe，0.02D
USM?2922 ?45.00 ?45.00 ?2.00 ?8.00
PM?75/76 ?44.10 ?44.10 ?2.40 ?7.70 0.09Fe，0.06C，0.09O，33ppm?N，14ppm?S
VA892/SP75 ?44.50 ?45.20 ?2.53 ?7.60 90ppm?Hf，0.04C，20ppm?S，61ppm?o
Structure that is grain size, the distribution of precipitate and the size of precipitate of tissue alter a great deal with production process.Manufacturing route (PM) by thermodynamics processing, extruding (SP) or use powder metallurgy can make being evenly distributed of Laves' phases particulate.
The mechanical property of alloy and selected manufacturing processed are closely related.Follow following manufacturing route for this alloy:
-directional freeze as far as possible generates flawless tissue by pouring technology.The process parameter of process parameter and super superalloy corresponding (referring to U.Paul, VDI-progress report Nr.264, VDI press),
-powder metallurgy: by being blown into rare gas element, and then well is suppressed 1250 ℃ of hot down equipressures,
-1250 ℃ of down extruding, make homogeneous microstructureization and be adjusted into the crystal grain diameter size of regulation,
-in stressed condition and 1100 ℃ of following hot pressing of multiaxis.
The directional freeze sample has clear and definite higher-strength, and for example the material of extruding has that reduced or very low intensity.Different alloy and 0.2% yield-point of NiAl in dump test of 2 expressions of tabulating down.
Table 2
Temperature, (by ℃) alloy designations: ???23 200 ??400 ??600 ??800 ??900 ??1000 ?1100 ??1200
SSm?364 ??650 ??520 ??451 ??201 ??146 ???94 ??60 ???46
VA2823 ??640 ??524 ??414 ??264 ??137 ??83
USM?2823 ??1501 ??1494 ??584 ??404 ??186 ??125 ???88
PM?75 ??814 ??593 ??456 ??284 ??126 ??65
PM?76 ??869 ??562 ??466 ??275 ??113 ??51
VA892 ??133
SP?75 ??730 ??581 ??344 ??294 ??113 ??69
Table 3 is illustrated in the creep strength (pressing MPa) that is studied alloy in the compression testing (in the stable creep strengths of 1000 ℃ and 1100 ℃ of following secondaries as the function of strain rate by [pressing l/S]).
Table 3
Strain rate is pressed (l/s) alloy designations: 1.00E-08 at 1000 ℃ 1.00E-07 at 1000 ℃ 1.00E-06 at 1000 ℃ 1.00E-08 at 1100 ℃ 1.00E-07 at 1100 ℃ 1.00E-06 at 1100 ℃
Ssm?364 19.90 36.10 55.50 14.60 20.00 34.60
VA/SM 16.50 23.20 33.40
USM 2823 (foundry goods) 79.00 98.00 28.50 32.80 39.00
PM?75 13.90 22.90 36.80 17.50
PM?76 11.20 19.90 338.80 11.00
SP?75 10.00 18.00 33.90 11.10
The creep strength of this alloy is higher than the creep strength of similar intermetallic phase, for example is higher than the creep strength of the NiAl or the NiAlCr alloy of binary.
Table 4a has listed the comparison to NiAl alloy and NiAl-Ta-Cr alloy 0.2% Yield point (pressing MPa) in compression testing of traditional super superalloy, binary.
Table 4a
Temperature: Super superalloy ??Ni 50Al 50 NiAl-Ta-Cr foundry goods/PM75
????900℃ ????424 ????47 ?????345/205
????1000℃ ????135 ????26 ?????186/126
????1100℃ ????28 ????18 ?????125/65
Relevant 0.2% Yield point, last illness that has not attacked the vital organs of the human body is real to have superiority by alloy of the present invention when temperature is higher than 1000 ℃.
The 4b that tabulates down listed the NiAl alloy of super superalloy, binary and the NiAl-Ta-Cr alloy invented in compression testing when ε=10 -7The comparison of stable creep strength (pressing MPa) during l/S.
Table 4b
Temperature: ????Ni 50Al 50 ????NiAl-Ta-Cr ????2823/2922 ???NiAl-Ta-Cr ????PM75/SP75
????1000℃ ?????13 ?????79/89 ?????23/19
????1100℃ ?????n.b. ?????33/33 ?????10/6
????1200℃ ?????n.b. ?????/21
Abbreviation n.b in the table is that the relevant value of expression is not determined.
Compare with traditional super superalloy, the advantage of NiAl-Ta-Cr alloy is that even be higher than 1050 ℃ to 1150 ℃, it still has enough intensity.Do not have the unexpected decline of intensity in this alloy, the unexpected decline of this intensity is loose owing to solid phase.
The NiAl-Ta-Cr alloy that the powder metallurgy program of the various potteries of table 5 expression is produced is by the known K of industrial data ICThe comparison of value.
Table 5
The NiAl foundry goods The NiAl-Ta-Cr foundry goods ??NiAl-Ta-Cr?PM ?NiAl-Ta-Cr?SP ?SiC
KIC/MPa?m ?????4-5 * ???????4.5 ????????8 ??????8-11 ?4.6
* Reu β, Ph D dissertation, northern Lay mattress-Westfalen-Aachen worker is big
The toughness of intermetallic NiAl base alloy is more far better than the data that the NiAl and the SiC of binary records.
It is 5*10 that this alloy has the order of magnitude -14g 2Cm -4The good oxidation-resistance of S, therefore, it is identical or better with the oxidation-resistance of the NiAl of binary.Compare the layer that at high temperature do not need protection, for example stupalith protective layer with super superalloy.Thereby avoided the connectivity problem between pottery and metal part branch.
Enough thermal shock resistances have been given.Alloy has been accomplished after 500 temperature cycle not infringement of material in the time of 1350 ℃.

Claims (12)

1, a kind of intermetallic nickel-aluminum base alloy, its tissue mainly is made up of binary phase NiAl, and chromium and tantalum are arranged, and wherein these two kinds of elemental chromium and tantalum content are up to 12 atom %.
2, according to the described alloy of claim 1, it is characterized in that: binary phase NiAl amounts in tissue and accounts for 70 atom % to 95 atom %, especially 85 atom % to 90 atom %.
3, according to claim 1 or 2 described alloys, it is characterized in that: it contains the tantalum of 0.3 atom % to 3.0 atom % and the chromium of 1.0 atom % to 9.0 atom %.
4, according to the described alloy of claim 3, it is characterized in that: it contains the tantalum of 0.3 atom % to 0.9 atom % and the chromium of 1.0 atom % to 3.0 atom %.
5, according to the described alloy of claim 3, it is characterized in that: it contains the tantalum of 0.7 atom % to 3.0 atom % and the chromium of 6.0 atom % to 9.0 atom %.
6, according to the described alloy of above-mentioned each claim, it is characterized in that: it contains proportional is 1: 3 or littler tantalum and chromium.
7, according to the described alloy of above-mentioned each claim, it is characterized in that: have thick Laves' phases precipitate at least some NiAl crystal boundaries, and have tiny Laves' phases precipitate and α chromium in some nickel-aluminium grain inside at least.
According to the described alloy of claim 7, it is characterized in that 8, its tissue contains the thick Laves' phases precipitate of 5 to 10 volume %, tiny Laves' phases precipitate and the α chromium of 3 to 10 volume % is arranged in NiAl.
9, according to the described alloy of claim 8, it is characterized in that, it be organized in Laves' phases that 11 volume % are arranged on the crystal boundary face approximately and the precipitate that 10 volume % are arranged approximately in the NiAl of binary.
10, according to the described alloy of above-mentioned each claim, it is characterized in that: it contains a kind of element from iron, molybdenum, tungsten, niobium and hafnium family at least, and its content is respectively to 1 atom %, but total amount is no more than 3 atom %.
11, the application of intermetallic nickel-aluminum base alloy, this alloy mainly contains the NiAl of binary phase and element tantalum and chromium is arranged, wherein, the total composition of tantalum and chromium is up to 12 atom %, it is applied to as the material of making the gas turbine structure member, for example gas turbine operation blade and gas turbine turning vane.
12, use alloy according to each described composition in the claim 1 to 10 as the material of making member, this alloy has 0.2% yield-point under the room temperature to be higher than the high strength of 600MPa, 0.2% yield-point is higher than 200MPa in the time of 800 ℃, is higher than the high high-temperature capability of 90MPa in the time of 1000 ℃, K ICAt least the excellent toughness of 7MPa/m, 5*10 -14g 2Cm -4The good oxidation of S, and good thermal-shock resistance.
CN95193622A 1994-05-21 1995-05-19 Nickel-aluminium intermetallic basis alloy Expired - Fee Related CN1044493C (en)

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DE4417936A DE4417936C1 (en) 1994-05-21 1994-05-21 Nickel aluminum alloy
DEP4417936.7 1994-05-21

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CN1044493C CN1044493C (en) 1999-08-04

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JP (1) JPH10500453A (en)
KR (1) KR100359187B1 (en)
CN (1) CN1044493C (en)
CZ (1) CZ342696A3 (en)
DE (2) DE4417936C1 (en)
RU (1) RU2148671C1 (en)
WO (1) WO1995032314A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN100422369C (en) * 2006-12-13 2008-10-01 北京航空航天大学 Ti-modified NiAl-Cr(Mo) polyphase eutectic intermetallic compound
CN104073688A (en) * 2014-06-19 2014-10-01 湖南科技大学 Application of NiAl-2.5Ta-7.5Cr alloy as self-lubricating wear-resistant material under alkali corrosion working condition
CN104294328A (en) * 2014-10-23 2015-01-21 上海应用技术学院 Nickel-molybdenum-aluminum-rare earth coating and preparation method thereof
CN115595486A (en) * 2022-10-14 2023-01-13 中国科学院金属研究所（Cn） Wear-resistant cutting coating for blade tip of high-temperature turbine blade and preparation method and application thereof

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE521471C2 (en) 2001-03-27 2003-11-04 Koncentra Holding Ab Piston ring and coating on a piston ring comprising a composite material of a ceramic and an intermetallic compound
BR102013019686B1 (en) 2013-08-01 2020-11-03 Mahle Metal Leve S/A piston ring and its manufacturing process
DE102017109156A1 (en) 2016-04-28 2017-11-02 Hochschule Flensburg High-temperature resistant material and its production

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1812144C3 (en) * 1967-12-06 1974-04-18 Cabot Corp., Boston, Mass. (V.St.A.) Process for the production of a high-strength nickel-aluminum material
US5116691A (en) * 1991-03-04 1992-05-26 General Electric Company Ductility microalloyed NiAl intermetallic compounds

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN100422369C (en) * 2006-12-13 2008-10-01 北京航空航天大学 Ti-modified NiAl-Cr(Mo) polyphase eutectic intermetallic compound
CN104073688A (en) * 2014-06-19 2014-10-01 湖南科技大学 Application of NiAl-2.5Ta-7.5Cr alloy as self-lubricating wear-resistant material under alkali corrosion working condition
CN104073688B (en) * 2014-06-19 2016-08-17 湖南科技大学 A kind of NiAl-2.5Ta-7.5Cr alloy is as the application of self-lubricating abrasion-proof material under caustic corrosion operating mode
CN104294328A (en) * 2014-10-23 2015-01-21 上海应用技术学院 Nickel-molybdenum-aluminum-rare earth coating and preparation method thereof
CN104294328B (en) * 2014-10-23 2017-02-01 上海应用技术学院 Nickel-molybdenum-aluminum-rare earth coating and preparation method thereof
CN115595486A (en) * 2022-10-14 2023-01-13 中国科学院金属研究所（Cn） Wear-resistant cutting coating for blade tip of high-temperature turbine blade and preparation method and application thereof
CN115595486B (en) * 2022-10-14 2024-03-22 中国科学院金属研究所 Wear-resistant cutting coating for blade tips of high-temperature turbine blades and preparation method and application thereof

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KR100359187B1 (en) 2003-01-24
KR970703438A (en) 1997-07-03
RU2148671C1 (en) 2000-05-10
EP0760869B1 (en) 2001-04-25
JPH10500453A (en) 1998-01-13
WO1995032314A1 (en) 1995-11-30
DE59509221D1 (en) 2001-05-31
CN1044493C (en) 1999-08-04
DE4417936C1 (en) 1995-12-07
EP0760869A1 (en) 1997-03-12
CZ342696A3 (en) 1997-08-13

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