GB2354257A - A high temperature titanium-aluminium alloy - Google Patents
A high temperature titanium-aluminium alloy Download PDFInfo
- Publication number
- GB2354257A GB2354257A GB0017057A GB0017057A GB2354257A GB 2354257 A GB2354257 A GB 2354257A GB 0017057 A GB0017057 A GB 0017057A GB 0017057 A GB0017057 A GB 0017057A GB 2354257 A GB2354257 A GB 2354257A
- Authority
- GB
- United Kingdom
- Prior art keywords
- alloy
- temperature
- strength
- alloys
- aluminium alloy
- 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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Links
- 229910000838 Al alloy Inorganic materials 0.000 title abstract 2
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 title abstract 2
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 39
- 239000000956 alloy Substances 0.000 claims abstract description 39
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 21
- 229910052796 boron Inorganic materials 0.000 claims abstract description 20
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 15
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 11
- 239000000203 mixture Substances 0.000 claims abstract description 9
- 229910052763 palladium Inorganic materials 0.000 claims abstract description 9
- 229910052715 tantalum Inorganic materials 0.000 claims abstract description 9
- 229910052727 yttrium Inorganic materials 0.000 claims abstract description 9
- 229910052726 zirconium Inorganic materials 0.000 claims abstract description 9
- 229910052758 niobium Inorganic materials 0.000 claims abstract description 7
- 229910052748 manganese Inorganic materials 0.000 claims abstract description 6
- 229910010038 TiAl Inorganic materials 0.000 claims description 11
- 238000007792 addition Methods 0.000 description 12
- 230000003647 oxidation Effects 0.000 description 9
- 238000007254 oxidation reaction Methods 0.000 description 9
- 239000010936 titanium Substances 0.000 description 9
- 230000000052 comparative effect Effects 0.000 description 5
- 229910000765 intermetallic Inorganic materials 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 230000001681 protective effect Effects 0.000 description 4
- 238000005275 alloying Methods 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 238000001513 hot isostatic pressing Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000001000 micrograph Methods 0.000 description 3
- 238000007711 solidification Methods 0.000 description 3
- 230000008023 solidification Effects 0.000 description 3
- 229910021324 titanium aluminide Inorganic materials 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- 150000003608 titanium Chemical class 0.000 description 2
- 229910000951 Aluminide Inorganic materials 0.000 description 1
- 229910018516 Al—O Inorganic materials 0.000 description 1
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- OQPDWFJSZHWILH-UHFFFAOYSA-N [Al].[Al].[Al].[Ti] Chemical compound [Al].[Al].[Al].[Ti] OQPDWFJSZHWILH-UHFFFAOYSA-N 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 229910052735 hafnium Inorganic materials 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 229910052720 vanadium Inorganic materials 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C14/00—Alloys based on titanium
Abstract
A titanium-aluminium alloy having the following composition:<BR> <BR> Ti<SB>x</SB>El<SB>y</SB>Me<SB>z</SB>Al<SB>1(x+y+z)</SB><BR> <BR> where El is a combination of two elements selected from B, Si and Ge and Me is Cr, Mn, Nb, Pd, Ta, W, Y, Zr wherein the following relationships apply: <UL ST="0"> <LI>.46 & x & 0.54; <LI>.001 & y & 0.015 for El = Si and Me = W; <LI>.001 & y & 0.015 for El = Ge and Me = Cr, Ta, W; <LI>< y & 0.02 for El = Ge and Me = Pd, Y, Zr; <LI>.0001 & y & 0.01 for El = B; <LI>.01 < z & 0.04 if Me = a single element; <LI>.01 < z & 0.08 if Me = two or more elements; <LI>.46 & (x + y + z) & 0.54. </UL> One particular alloy comprises (in atomic %): Al 47 %, W 2 %, Si 0.5 %, B 0.5 % with the balance being Ti.
Description
2354257 High-temperature alloy
Technical field
The invention relates to a high-temperature alloy for thermal machines, based on intermetallic compounds which are suitable for controlled solidification and supplement the conventional nickel based superalloys.
it relates to an improvement to the alloys which are based on an intermetallic compound of the titanium aluminide TiAl type, with further additions which increase the strength, toughness and ductility as well as the resistance to oxidation and the creep rupture strength.
Prior Art
Intermetallic compounds of titanium with 20 aluminium have a number of interesting properties which make them appear attractive structural materials in the medium and relatively high temperature ranges. These properties include, inter alia, their lower density compared to superalloys. However, their brittleness represents a drawback to their being used in the present form. This can be improved by certain additions.
For example, it has been proposed, by adding, as alternatives, Cr, B, V, Si, Ta, as well as Mn, W, Mo, Nb, Hf or (Ni+Si), on the one hand to reduce the brittleness and, on the other hand, to achieve as high a strength as possible in the temperature range of interest between room temperature and operating temperature. Moreover, a sufficiently high resistance to oxidation was desired. However, these aims were only partially achieved.
The heat resistance, in particular, of the known aluminides leaves something to be desired. In accordance with the relatively low melting point of 2 these materials, the strength, in particular the creep rupture strength, is unsatisfactory in the upper temperature range.
US 3 203 794 has disclosed a TiAl high- temperature alloy containing 37% by weight Al, 1% by weight Zr, remainder Ti. The relatively small addition of Zr means that this alloy has properties similar to those of pure TiAl.
EP-AI-O 363 598 has disclosed a high- temperature alloy which is based on TiAl and contains additions of Si and Nb, whereas EP-Al-O 405 134 has disclosed a high- temperature alloy which is based on TiAl with additions of Si and Cr.
However, these known modified intermetallic compounds do not satisfy the technical requirements.
Therefore, in order to improve the properties, EP-BI-O 4S5 005 specified a high-temperature alloy based on doped TiAl of the following chemical composition:
Ti,,EIYMezAll-(x+y+z)f where El = B, Ge or Si and Me = Cr, Mn, Nb, Pd, Ta, W, Y, Zr, and the following relationships apply:
0.46:5 x:5 0.54, 0.001:!- y 0.015 for El = Si and Me = W 0.001:5 y 0.015 for El = Ge and Me = Cr, Ta, W 0 < y:! 0.02 for El = Ge and Me = Pd, Y, Zr 0.0001:! y:5 0.01 for El = B 0.01 < z:5 0.04 if Me = a single element, 0.01 < z:5 0.08 if Me = two or more individual elements and 0.46:5 (x + y + z):5 0.54.
Adding W, Cr, Mn, Nb, Y, Zr, Pd to the alloy increases the hardness and strength with respect to the TiAl base alloy. Adding B increases the ductility. Si increases the resistance to oxidation. The range in which these modified titanium aluminides are used extends to temperatures between 6000C and 10000C.
3 A further improvement in particular to the creep rupture strength and the resistance to oxidation is desirable.
Description of the invention
The invention seeks to further improve the high-temperature alloys described in EP-Bl-O 455 005. It is based on the object of specifying a lightweight alloy with improved resistance to oxidation and corrosion at elevated temperatures and, at the same time, a high heat resistance and good toughness in the range from 600 to 1000C, which is suitable for controlled solidification and essentially comprises an intermetallic compound with a high melting point.
According to the invention, this is achieved by the fact that the high temperature alloy for a highly mechanically loaded component of a thermal machine based on doped TiAl exhibits the following composition:
Ti,ElyMezAll-(x+y+z), where El = in each case a combination of two elements selected from the group consisting of B, Si, Ge, and Me = Cr, Mn, Nb, Pd, Ta, W, Y, Zr, and the following relationships apply:
0.46:5 x:5 0.54, 0.001:5 y:5 0.015 for El = Si and Me = W 0.001:5 y:5 0.015 for El = Ge and Me = Cr, Ta, W 0 < y:5 0.02 for El = Ge and Me = Pd, Y, Zr 0.0001:5 y:5 0.01 for El = B 0.01 < z:5 0.04 if Me = a single element, 0.01 < z:5 0.08 if Me = two or more individual elements and 0.46:5 (x + y + z):5 0.54.
The core feature of the invention is the addition of in each case two elements from the group consisting of B, Si, Ge in the said ranges to the 4 alloys which are otherwise already known from EP-Bl-O 455 005 but in which, in contrast to the present invention, there is always only one element from the group consisting of B, Si, Ge.
The advantages of the invention consist in the fact that it is possible, by combining the alloying elements B + Si, B + Ge and Ge + Si, on the one hand to produce a fine-grained microstructure, and thus to increase the toughness and creep rupture strength, and, on the other hand, to achieve a good resistance to oxidation.
It is particularly expedient if the alloy consists of 47 at.% Al, 2 at.% W, 0.5 at.% Si, 0.5 at. % B, remainder Ti. W increases the strength of the TiAl base alloy but results in a loss of toughness. This is balanced out again by the addition of B, since boron leads to a very fine-grained, tough microstructure. The addition of 0.5 at.% Si increases the creep strength properties and the resistance to oxidation, resulting in an excellent combination of properties in the high- temperature alloy for components which are subjected to high mechanical and thermal loads.
Brief description of the drawing
An exemplary embodiment of the invention is illustrated in the drawing, in which:
Fig. 1 shows a micrograph of the structure of an alloy Ll according to the invention of the following composition: Al 47 at.%, W 2 at.%, Si 0.5 at.%, B 0.5 at.%, remainder Ti; Fig. 2 shows a micrograph of the structure of a comparative alloy VLl of the following composition: Al 47 at.%, W 2 at.%, B 0.5 at.%, remainder Ti; Fig. 3 a micrograph of the structure of a comparative alloy VL2 of the following composition: Al 47 at.%, W 2 at.%, Si 0.5 at.%, remainder Ti; Fig. 4 shows a graph illustrating the yield strength as a function of temperature for the alloys Ll and VL2; Fig. 5 shows a graph illustrating the tensile strength as a function of temperature for the alloys Ll and VL2; Fig. 6 shows a graph illustrating the elongation as a function of temperature for the alloys Ll and VL2.
Ways of carrying out the invention The invention is explained in more detail below with reference to an exemplary embodiment and Figures I to 6.
In an electric arc furnace, alloys of the following composition (in at.%) were melted under argon as protective gas, Ll representing an alloy according to the invention and Ul and VL2 representing comparative alloys:
Alloy Al W Si B Ti Ll 47 2 0.5 0.5 Remainder VL1 47 2 - 0.5 Remainder L2 47 2 0.5 - Remainder The individual elements with a purity of 99.99% were used as starting materials. The molten alloy was in each case cast to give a blank casting with a diameter of approx. 50 mm and a height of approx. 70 mm. These blanks were melted again under protective gas and, again, under protective gas, were made to solidify in the form of rods with a diameter of approx.
6 9 mm and a length of approx. 70 mm. These rods were subjected to HIP (HOT ISOSTATIC PRESSING) and heat treatment and were then processed into tensile specimens. The HIP treatment was carried out for 4 hours at a temperature of 12600C and under a pressure of 172 MPa. The heat treatment was carried out under protective gas with the following parameters: 1350OC/ 1 h + 1000OC/6 h.
By optimizing the heat treatment it is possible to further improve the mechanical properties, in addition to an improvement by controlled solidification, for which alloys of this nature are particularly suitable.
The addition of W leads to an increase in 1S strength compared to pure TiAl alloys but to a loss of ductility. B increases the ductility and Si increases the resistance to oxidation. Figures 1 to 3 show the microstructure of the alloys Ll, VLl and VL2. 20 The microstructure of the alloy Ll according to the invention (Fig. 1) is extremely fine-grained. It is very similar to the microstructure of the comparative alloy VL1 (Fig. 2), which is alloyed with B, while Ll is alloyed with B and Si. By contrast, the comparative alloy VL2, which is alloyed with Si, has a very coarsegrained microstructure (Fig. 3).
Figs. 4 to 6 portray diagrams for the alloys Ll and VL2, showing the values determined in the tensile test for the yield strength, the tensile strength and the extension as a function of temperature. The alloy Ll according to the invention has a higher yield strength, as well as a higher tensile strength and elongation, both at room temperature and at temperatures above 600C.
These excellent properties are attributable to the combination of the alloying elements B and Si. The addition of 0.5 at.% B practically makes up for the losses of ductility caused by the W. There is no need to add more than 1 at.% B. The addition of 0.5 at.% Si, 7 in combination with the other alloying elements, increases the resistance to heat and oxidation.
The modified titanium aluminides are advantageously employed at a temperature range of between 600 and 1000C.
Naturally, the invention is not limited to the exemplary embodiment shown. Like B, Ge makes the grains in the microstructure finer. Since the effect of Ge is somewhat weaker in this respect than that of B, it is necessary to add larger quantities of Ge, but adding more than 1.5 at.% Ge serves no purpose. The simultaneous addition of Ge and Si in the abovementioned proportions leads to similarly good combinations of properties in the material to those achieved with the above-described combination of B and Si.
8
Claims (2)
1. High-temperature alloy for a highly mechanically loaded component of a thermal machine, based on doped TiAl of the following composition:
Ti,,EIYMezA-11-(x+y+z) where El = in each case a combination of two elements selected from the group consisting of B, Si, Ge, and Me = Cr, Mn, Nb, Pd, Ta, W, Y, Zr, and the following relationships apply:
0.46:5 x:5 0.54, 0.001:5 y:5 0.015 for El = Si and Me = W 0.001 y:5 0.015 for El = Ge and Me = Cr, Ta, W 0 < y 0.02 for El = Ge and Me = Pd, Y, Zr 0.0001:5 y:5 0.01 for El = B 0.01 < z:5 0.04 if Me = a single element, 0.01 < z: 0.08 if Me = two or more individual elements and 0.46:5 (x + y + z):5 0.54.
2. High-temperature alloy according to Claim 1, of the following composition:
Al = 47 at.% W = 2 at.% Si = 0.5 at.% B = 0.5 at.% Remainder Ti.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE1999133633 DE19933633A1 (en) | 1999-07-17 | 1999-07-17 | High temperature titanium alloy for highly-stressed components of heat engines, comprises titanium, aluminum, and e.g. boron silicon and e.g. tungsten |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB0017057D0 GB0017057D0 (en) | 2000-08-30 |
| GB2354257A true GB2354257A (en) | 2001-03-21 |
Family
ID=7915171
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB0017057A Withdrawn GB2354257A (en) | 1999-07-17 | 2000-07-11 | A high temperature titanium-aluminium alloy |
Country Status (2)
| Country | Link |
|---|---|
| DE (1) | DE19933633A1 (en) |
| GB (1) | GB2354257A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220017995A1 (en) * | 2019-05-23 | 2022-01-20 | Ihi Corporation | TiAl ALLOY AND METHOD OF MANUFACTURING THE SAME |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10049026A1 (en) * | 2000-10-04 | 2002-04-11 | Alstom Switzerland Ltd | High temperature alloy |
| DE102009027019B4 (en) * | 2009-05-13 | 2011-01-05 | Manfred Renkel | Implant of intermetallic titanium-aluminide alloys |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0455005A1 (en) * | 1990-05-04 | 1991-11-06 | Asea Brown Boveri Ag | High temperature alloy for engine components, based on modified titanium aluminide |
| US5196162A (en) * | 1990-08-28 | 1993-03-23 | Nissan Motor Co., Ltd. | Ti-Al type lightweight heat-resistant materials containing Nb, Cr and Si |
| JPH10298127A (en) * | 1997-04-24 | 1998-11-10 | Chisso Corp | Fluoroalkyl ether compound, liquid crystal composition, and liquid crystal element |
| US5908516A (en) * | 1996-08-28 | 1999-06-01 | Nguyen-Dinh; Xuan | Titanium Aluminide alloys containing Boron, Chromium, Silicon and Tungsten |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1179006B (en) * | 1952-12-18 | 1964-10-01 | Crucible Steel Internat | Titanium alloys |
| US3203794A (en) * | 1957-04-15 | 1965-08-31 | Crucible Steel Co America | Titanium-high aluminum alloys |
| US4983357A (en) * | 1988-08-16 | 1991-01-08 | Nkk Corporation | Heat-resistant TiAl alloy excellent in room-temperature fracture toughness, high-temperature oxidation resistance and high-temperature strength |
| US5045406A (en) * | 1989-06-29 | 1991-09-03 | General Electric Company | Gamma titanium aluminum alloys modified by chromium and silicon and method of preparation |
| US5226985A (en) * | 1992-01-22 | 1993-07-13 | The United States Of America As Represented By The Secretary Of The Air Force | Method to produce gamma titanium aluminide articles having improved properties |
| DE4215194C2 (en) * | 1992-05-08 | 1995-06-29 | Abb Patent Gmbh | Highly heat-resistant material |
| DE4219469A1 (en) * | 1992-06-13 | 1993-12-16 | Asea Brown Boveri | Component subject to high temperatures, in particular turbine blade, and method for producing this component |
| US5417781A (en) * | 1994-06-14 | 1995-05-23 | The United States Of America As Represented By The Secretary Of The Air Force | Method to produce gamma titanium aluminide articles having improved properties |
| USH1659H (en) * | 1995-05-08 | 1997-07-01 | The United States Of America As Represented By The Secretary Of The Air Force | Method for heat treating titanium aluminide alloys |
| US5653828A (en) * | 1995-10-26 | 1997-08-05 | National Research Council Of Canada | Method to procuce fine-grained lamellar microstructures in gamma titanium aluminides |
-
1999
- 1999-07-17 DE DE1999133633 patent/DE19933633A1/en not_active Withdrawn
-
2000
- 2000-07-11 GB GB0017057A patent/GB2354257A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0455005A1 (en) * | 1990-05-04 | 1991-11-06 | Asea Brown Boveri Ag | High temperature alloy for engine components, based on modified titanium aluminide |
| US5196162A (en) * | 1990-08-28 | 1993-03-23 | Nissan Motor Co., Ltd. | Ti-Al type lightweight heat-resistant materials containing Nb, Cr and Si |
| US5908516A (en) * | 1996-08-28 | 1999-06-01 | Nguyen-Dinh; Xuan | Titanium Aluminide alloys containing Boron, Chromium, Silicon and Tungsten |
| JPH10298127A (en) * | 1997-04-24 | 1998-11-10 | Chisso Corp | Fluoroalkyl ether compound, liquid crystal composition, and liquid crystal element |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220017995A1 (en) * | 2019-05-23 | 2022-01-20 | Ihi Corporation | TiAl ALLOY AND METHOD OF MANUFACTURING THE SAME |
Also Published As
| Publication number | Publication date |
|---|---|
| DE19933633A1 (en) | 2001-01-18 |
| GB0017057D0 (en) | 2000-08-30 |
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| Date | Code | Title | Description |
|---|---|---|---|
| 732E | Amendments to the register in respect of changes of name or changes affecting rights (sect. 32/1977) | ||
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |