GB2287955A - High specific strength, heat resistant Ni-Ti base alloy - Google Patents
High specific strength, heat resistant Ni-Ti base alloy Download PDFInfo
- Publication number
- GB2287955A GB2287955A GB9504882A GB9504882A GB2287955A GB 2287955 A GB2287955 A GB 2287955A GB 9504882 A GB9504882 A GB 9504882A GB 9504882 A GB9504882 A GB 9504882A GB 2287955 A GB2287955 A GB 2287955A
- Authority
- GB
- United Kingdom
- Prior art keywords
- alloy
- heat resistant
- specific strength
- high specific
- strength
- 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
Links
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 47
- 239000000956 alloy Substances 0.000 title claims abstract description 47
- 229910001000 nickel titanium Inorganic materials 0.000 title claims abstract description 15
- KHYBPSFKEHXSLX-UHFFFAOYSA-N iminotitanium Chemical compound [Ti]=N KHYBPSFKEHXSLX-UHFFFAOYSA-N 0.000 title abstract 2
- 239000000203 mixture Substances 0.000 claims abstract description 9
- 229910000765 intermetallic Inorganic materials 0.000 claims description 6
- 150000001875 compounds Chemical class 0.000 claims description 4
- 229910052804 chromium Inorganic materials 0.000 abstract description 4
- 229910052735 hafnium Inorganic materials 0.000 abstract description 4
- 229910052702 rhenium Inorganic materials 0.000 abstract description 4
- 229910052750 molybdenum Inorganic materials 0.000 abstract description 3
- 229910052758 niobium Inorganic materials 0.000 abstract description 3
- 229910052715 tantalum Inorganic materials 0.000 abstract description 3
- 229910052721 tungsten Inorganic materials 0.000 abstract description 3
- 229910052720 vanadium Inorganic materials 0.000 abstract description 3
- 229910052796 boron Inorganic materials 0.000 abstract description 2
- 229910052726 zirconium Inorganic materials 0.000 abstract description 2
- 229910052799 carbon Inorganic materials 0.000 abstract 1
- 229910000601 superalloy Inorganic materials 0.000 description 16
- 239000000463 material Substances 0.000 description 7
- 238000006467 substitution reaction Methods 0.000 description 5
- 239000000654 additive Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 229910001247 waspaloy Inorganic materials 0.000 description 3
- 230000000996 additive effect Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000003779 heat-resistant material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 238000007711 solidification Methods 0.000 description 2
- 230000008023 solidification Effects 0.000 description 2
- 229910017709 Ni Co Inorganic materials 0.000 description 1
- 229910001005 Ni3Al Inorganic materials 0.000 description 1
- 229910009972 Ti2Ni Inorganic materials 0.000 description 1
- 229910010038 TiAl Inorganic materials 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 238000012669 compression test Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000004663 powder metallurgy Methods 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 229910001285 shape-memory alloy Inorganic materials 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 230000000930 thermomechanical effect Effects 0.000 description 1
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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
High specific strength, heat resistant Ni-Ti base alloy. The alloy has a nominal composition expressed NiaTibAlc (where a, b, and c are atom% fractions, a+b+c=100, a=from 45 to 60 and 0.5 </= c </= 18). Cr, Co, Mo, W, Hf, Nb, Ta, Re, V, B, C and Zr may be present singly or severally.
Description
HIGH SPECIFIC STRENGTH, HEAT RESISTANT NiTi-BASE ALLOYS
The present- invention relates to a high specific strength, heat resistant alloy. More specifically, the present invention relates to a heat resistant NiTi-base alloy having high specific strength preferably applicable to structural members requiringhigh specific strength at a wide range of from relatively low temperatures to high.
The materials used in jet engine blades and disks as well as fuselage materials are subjected to extreme temperature gradients. For example, the outer disk material experiences temperatures exceeding 600C , while the inner temperature may be a relatively cool 200'C, Therefore, the alloy used in these areas must be strong in a wide temperature range. The Ni base superalloys having high strength at high temperatures have been adopted as those materials up to now, but these superalloys have a serious defect in that their strength at relatively low temperatures is low. In particular, their specific weight is so high by 7.9-9,0 that tremendous centrifugal stress is loaded to inner areas of materials rotating at low temperatures.
There is a limit to use the Ni base superalloys. At the same -time, these alloys tend to make jet engines heavier.
In terms of'rolume1 turbine disks are particularly large, so it is necessary to reduce specific weight to achieve reduction in weight.
Recently, some proposal has been made in which a TiAl intermetallic compound having small specific weight of 3.9 is applied. This intermetallic compound, however, has low strength at low temperatures around room temperature (350 530MPa against 0.2X proof stress) and its specific strength is, at best, equal to that of the Ni base superalloy (90 l36MPa/(g/cm3). The above-mentioned problem has remained unsolved.
The present invention provides a high specific strength, heat resistant alloy having a nominal composition expressed Ni aTibAic (where a, b, and c are atomX fractions, a+b+c=100, a=from 45 to 60 and 0.5# c < 18).
The present invention has been achieved based on the fact discovered by inventors that substitution of Al for a part of Ti in the NiTi intermetallic compound exclusively used for shape-memory alloys improves strength greatly both at high temperatures and at room temperature. Specific strength improved by the partial substitution of A1 for Ti is equal to that of the conventional Ni base superalloy at high temperatures around lOOO-C , and it is enhanced by two or three times at room temperature compared to that of the
Ni base superalloy. Specific weight, on the other hand, goes down 20% compared with that of the superalloy. Thisfact tells us that the alloy is useful for achieving reduction in weight.
The amount of Ni, or an atomX fraction expressed "a" in the nominal composition, is within a range in which harmful phases to cause toughness to deteriorate are not precipitated at all. If "s" exceeds beyond 60 atoms, harmful phases such as a Ni3Ti phase form easily.
Under 45 atom% of ale, a Ti2Ni harmful phase comes to form.
Toughness of the alloy decreases in both cases.
Addition of Al improves strength as well as oxidation resistance of the alloy, but if the amount of Al expressed "c" n the nominal composition exceeds i8 atoms, the amount of a NizAlTi type compound phase is so excessive that ductility deteriorates. The Al fraction is, therefore, limited to the range of 0.5# c# 18, preferably, 5 < c < 15.
The Ni2AlTi type compound precipitates in a sufficient amount under 5 atomX of "c", but the excessive amount beyond 15 atom% causes the amount of the Ni2TiAl type compound phase to slightly exceed, this influencing strength of the alloy.
With regard to the Al fraction, another preferable range is 0.5E c 5. The alloy substantially consists of a single phase of the NiTi type intermetallic compound within this range. This alloy is slightly inferior to the twophase alloy above-mentioned in strength, but its ductility is sufficient for the practical use. The Al fraction of below 0.5 atoms leads to low strength.
Several performancee of the alloys of the present invention may be further improved by the well-known manners for heat resistant materials. These manners are as follows:
1) Singular or plural elements selected from among
Co, Cr, Mo, W, Nb, Ta, Hf, Re and V may be added which are usually adopted for strengthening heat resistant materials.
2) Singular or plural elements, in general, effective for improving oxidation resistance and high temperature corrosion resistance, for example, Cr, Hf and Re, may be added to do so.
3) Singular or plural elements selected from among C,
B and Zr may be added which are famous for their effective function for improving grain boundary strength of polycrystalline materials.
4) Structure control may be conducted by the well known manner such as a directional solidification method, z single crystal solidification method and a powder metallurgy.
5) Microstructure control may be conducted by heat treatment such as solution heat treatment and subsequent annealing which are typically applied to the two-phase alloy. Thermo-mechanical treatment may be very effective to improve microstructure and mechanical properties.
At any rate, the alloy of the present invention may probably be fundamental to alloys with any additive as in the case of the conventional Ni base superalloy. The & i base superalloy mainly consists of two fundamental phases of Ni/Ni3Al and several additives are added.
Some embodiments of the present invention will now be described by way of example and with reference to accompanying drawing, in which:
Figure is a diagram illustrating the effect of substitution of Al in a NiTi system alloy on strength.
EXamplesl to 5 NiTi alloys and a series of alloys substituted by Al for Ti in the NiTi system were produced by melting. These compositions are shown in Table I together with compositions of the well-known Ni base superalloy. Specific weight of these alloys is also shown. The typical Ni base superalloys have specific weight of 7,9 to 8.2, but specific weight of the alloys of the present invention is 6.5 and goes down 20% compared with those of the conventional ones. This fact suggests it to us that weight of members such as turbine disks may be reduced by the alloy of the present invention.
Since the frame composition of the present invention consists of three elements of Ni, Ti and Al, the alloy holds Post down to produce compared with the conventional superalloys including several expensive additive elements.
Table 1
Alloy composition (atom%) Alloy Ni Co Cr Mo Al Ti C B Zr
Waspalloy balance 13.0 21.3 2.6 2.7 3.6 0.4 0,03 0.04 U500 balance 18.0 19.3 2.4 6.2 3.5 0.3 0.04 0.03
U700 balance 17.4 16.0 3.0 8.8 4.0 0.4 0.2
NiTi 49.8 - - - - 50.3 - -
Example 1 50.1 - - - 4.4 45.5 - -
2 50.1 - - - 7.1 42.8 - - -
3 50.7 - - - 8.4 40.9 - - -
4 50.8 - - - 11.0 38.2 - -
5 50.5 - - - 13.9 35.8 - -
Specific weight
Alloy Specific weight
Waspalloy 8.2
U500 7.9
U700 7.9
NiTi 6.5
Example 1 6.5
2 6.5
3 6.5
4 6.5
5 6.5
Subsequently, specimens having a column shape were prepared for a compression test and they, as cast materials, were subjected to strength test both at room temperature and at 1000 C . A hardness test was also carried out at room temperature. The results are shown in Table 2 together with published values of the fi base superalloys for comparison.
Table 2
Results of strength test
Hardness Strength Strength
at room temp. at room temp. at lOOO'C Alloy (Vickers) 0.2 Specific 0.2 Specific
proof strength proof strength
stress stress
Waspalloy - 795 97 78 9
U500 - 840 106 187 24
U700 - 965 122 269 34
NiTi 253 260 40 17 2
Example 1 408 1098 170 58 9
2 561 1645 255 139 22
3 642 2290 352 202 31
4 639 - - 247 38 5 730 - - 125 19
Unit 0.2 proof stress : MPa
Specific strength : MPa/(g/cm3)
As is clear from Table 2, partial substitution of Al for Ti in the NiTi alloy greatly enhances strength properties including hardness. For specific strength, the alloy of the present invention is equal to the conventional
Ni base superalloy at 1000 and far more excellent at room temperature. Rotary members such as turbine disks should require high specific strength at relatively low temperature range of from room temperature to 200*C as well as high temperature range. Since the alloy of the present invention has much higher strength at relatively low temperatures than the conventional Ni base superalloy does, a turbine made of the alloy may possibly bear centrifugal force. It is possible to rotate a turbine with a high speed and obtain high output performances. In addition, weight of the turbine is reduced because of small specific weight of the alloy. This alloy has significant effects on turbines for airplanes such as jet engines.
Expensive elements such as Co, Cr, Mo, W, Nb, Ta, Hf,
Re and V are optional additives for the alloy of the present invention, while they are essential for the conventional Ni base superalloy. This fact contributes to holding cost down.
Figure attached herewith shows the effect of substitution of Al in the NiTi system alloy on the strength of the alloy. It is clearly confirmed that replacement of
Al for Ti greatly improves strength of the NiTi alloys at 1oOO.c Ae d.ee ed in detail in the above, specific strength of the heat resistant NiTi-base alloy is enhanced by addition of Al.
It is needless to mention that the present invention is not limited to these embodiments.
Claims (6)
1. A high specific strength, heat resistant alloy having a nominal composition expressed NiaTiklC (where a, b, and c are atoms fractions, a+b+c=100, a=from 45 to 60 and 0.5s cs 18).
2. A high specific strength, heat resistant alloy as claimed in claim 1, wherein an Al fraction is from 5 to 15 atoms and said alloy is a two-phase alloy substantially consisting of a NiTi type intermetallic compound phase and a Ni2AlTi compound phase.
3. A high specific strength, heat resistant alloy as claimed in claim 1, wherein an Al fraction is from 0.5 to 5 atoms and said alloy substantially consists of a single phase of a NiTi intermetallic compound.
4. A high specific strength, heat resistant alloy as claimed in claim 1 substantially as hereinbefore described.
5. A high specific strength, heat resistant alloy substantially as hereinbefore described with reference to the examples.
6. A high specific strength, heat resistant alloy substantially as hereinbefore described with reference to the accompanying drawing.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6066435A JP2847177B2 (en) | 1994-03-11 | 1994-03-11 | NiTi-based high specific strength heat resistant alloy |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB9504882D0 GB9504882D0 (en) | 1995-04-26 |
| GB2287955A true GB2287955A (en) | 1995-10-04 |
| GB2287955B GB2287955B (en) | 1998-02-11 |
Family
ID=13315706
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9504882A Expired - Lifetime GB2287955B (en) | 1994-03-11 | 1995-03-10 | High specific strength, heat resistant NiTi-base alloys |
Country Status (2)
| Country | Link |
|---|---|
| JP (1) | JP2847177B2 (en) |
| GB (1) | GB2287955B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1629134A2 (en) * | 2003-03-25 | 2006-03-01 | Questek Innovations LLC | Coherent nanodispersion-strengthened shape-memory alloys |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107747020A (en) * | 2017-10-20 | 2018-03-02 | 裴寿益 | A kind of Titanium nickel aluminium molybdenum alloy material and preparation method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB560957A (en) * | 1941-10-28 | 1944-04-28 | Mond Nickel Co Ltd | Improvements relating to welding rods |
| GB1350468A (en) * | 1970-06-11 | 1974-04-18 | Furukawa Electric Co Ltd | Erosion-resisting alloys |
| GB1350094A (en) * | 1970-02-12 | 1974-04-18 | Furukawa Electric Co Ltd | Alloys |
| GB1413146A (en) * | 1971-09-07 | 1975-11-05 | Raychem Corp | Cryogenic mandrel expansion |
| GB1576533A (en) * | 1976-08-26 | 1980-10-08 | Bbc Brown Boveri & Cie | Shape memory alloys |
| EP0187452A1 (en) * | 1984-11-06 | 1986-07-16 | RAYCHEM CORPORATION (a Delaware corporation) | A method of processing a nickel/titanium-based shape memory alloy and article produced therefrom |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58157934A (en) * | 1982-03-13 | 1983-09-20 | Hitachi Metals Ltd | Shape memory alloy |
| JPH06322413A (en) * | 1993-04-02 | 1994-11-22 | Furukawa Electric Co Ltd:The | Method for joining niti shape memory alloy |
-
1994
- 1994-03-11 JP JP6066435A patent/JP2847177B2/en not_active Expired - Lifetime
-
1995
- 1995-03-10 GB GB9504882A patent/GB2287955B/en not_active Expired - Lifetime
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB560957A (en) * | 1941-10-28 | 1944-04-28 | Mond Nickel Co Ltd | Improvements relating to welding rods |
| GB1350094A (en) * | 1970-02-12 | 1974-04-18 | Furukawa Electric Co Ltd | Alloys |
| GB1350468A (en) * | 1970-06-11 | 1974-04-18 | Furukawa Electric Co Ltd | Erosion-resisting alloys |
| GB1413146A (en) * | 1971-09-07 | 1975-11-05 | Raychem Corp | Cryogenic mandrel expansion |
| GB1576533A (en) * | 1976-08-26 | 1980-10-08 | Bbc Brown Boveri & Cie | Shape memory alloys |
| EP0187452A1 (en) * | 1984-11-06 | 1986-07-16 | RAYCHEM CORPORATION (a Delaware corporation) | A method of processing a nickel/titanium-based shape memory alloy and article produced therefrom |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1629134A2 (en) * | 2003-03-25 | 2006-03-01 | Questek Innovations LLC | Coherent nanodispersion-strengthened shape-memory alloys |
| EP1629134A4 (en) * | 2003-03-25 | 2007-12-12 | Questek Innovations Llc | Coherent nanodispersion-strengthened shape-memory alloys |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2847177B2 (en) | 1999-01-13 |
| JPH07252563A (en) | 1995-10-03 |
| GB9504882D0 (en) | 1995-04-26 |
| GB2287955B (en) | 1998-02-11 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PE20 | Patent expired after termination of 20 years |
Expiry date: 20150309 |