CN101768684A - High temperature titanium alloy and surface modification method thereof - Google Patents
High temperature titanium alloy and surface modification method thereof Download PDFInfo
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- CN101768684A CN101768684A CN200810246875A CN200810246875A CN101768684A CN 101768684 A CN101768684 A CN 101768684A CN 200810246875 A CN200810246875 A CN 200810246875A CN 200810246875 A CN200810246875 A CN 200810246875A CN 101768684 A CN101768684 A CN 101768684A
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Abstract
The invention relates to a high temperature titanium alloy and a surface modification method thereof, in particular relating to a high temperature titanium alloy containing rare earth elements and a surface modification method thereof. The alloy in the invention comprises the following raw materials: 5.5-7wt% of Al, 0.5-3wt% of Sn and/or Ga, 0.08-0.2wt% of O, 7.5-8.5 wt% of [Al], 0.45-0.55wt% of Si, 4-5.5wt% of Zr or Hf, 0.3-0.5wt% of Mo, 0.3-0.5wt% of Nb and/or Ta, 0.6-0.85wt% of rare earth elements Y, Nd or Er and the balance titanium. The tensile strength of the alloy in the invention at room temperature is not lower than 1100MPa, the tensile strength at the high temperature of 650 DEG C is not lower than 650MPa; and surface modification is carried out on the high temperature titanium alloy in the invention by adopting the method of ion implantation, and the high temperature property of the alloy can be greatly improved after surface modification.
Description
Technical field
The present invention relates to a kind of high-temperature titanium alloy and surface modifying method thereof, particularly a kind of high-temperature titanium alloy and surface modifying method thereof that contains rare earth element.
Background technology
Development big thrust loading and long-life aircraft engine are one of aviation aircraft important goals of constantly developing pursuit.Requirements such as high temperature resistant, height ratio is strong, antifatigue, corrosion-resistant, long lifetime and low cost become the standard of aircraft engine selection.
More use nickel-base alloy of high-temperature component and ferrous alloy in the gas turbine engine, though its use temperature is high, maximum shortcoming is that density is too big.And high-temperature titanium alloy is except that having higher use temperature, and its biggest advantage is to have low density and high specific tenacity.Present studies show that, though nickel-base alloy Inconel718 and In-100 high-temperature mechanical property absolute value are higher than high-temperature titanium alloy, as considers bulkfactor, and the nickel-base alloy performance is starkly lower than high-temperature titanium alloy.Therefore with respect to Ni-based and iron-base superalloy, but just weight reduction and improve thrust-weight ratio of the use of titanium alloy.
Because there is problem of oxidation in alloy inevitably at high temperature, thereby has strengthened its plasticity decline degree.Along with the raising of alloy to use temperature, problem of oxidation can be more outstanding, has a strong impact on the use of alloy.It is very difficult to improve antioxidant property from the angle of alloying, therefore, adopts the high-temperature oxidation resistance that the method for surface modification can effective raising high-temperature titanium alloy, and then improves the use properties of superalloy.
The method of ion implantation surfacecti proteon is to adopt high energy ion beam bombardment material surface, and physics or chemical effect by injection process itself and injection element reach the purpose of improving material property.Because this process has coating to produce, so the size of part and overall performance do not change, there is not bonding force in ion implantation surface yet, unrelieved stress, and problem such as tissue deterioration.Therefore, ion implantation method is to improve high-temperature titanium alloy surface stability efficient ways.
Therefore, provide a kind of raising to be applied to aircraft engine etc. high temperature resistant, that the long lifetime requires environment is arranged, and improve the use temperature of high-temperature titanium alloy and high-temperature titanium alloy of duration of service and preparation method thereof, just become the problem that this technical field urgent need will solve.
Summary of the invention
One of purpose of the present invention provides a kind of high-temperature titanium alloy that aircraft engine etc. has the environment high temperature resistant, that the long lifetime requires that is applied to.
Above-mentioned purpose of the present invention reaches by the following technical programs:
A kind of high-temperature titanium alloy comprises:
5.5-7 the aluminium of weight % (Al);
0.5-3 the tin of weight % (Sn) and/or gallium (Ga);
0.08-0.2 the oxygen of weight % (O), and [Al] is 7.5～8.5;
0.45 the silicon of～0.55 weight % (Si);
The Zr of 4～5.5 weight % or Hf;
0.3 the Mo of～0.5 weight %;
0.3 the Nb of～0.5 weight % and/or Ta;
0.6 the rare earth element y of～0.85 weight %, Nd or Er;
Surplus is a titanium.
Definition Al equivalent is: [Al]=Al%+0.46 * Sn%+0.42 * Ga%+6.7 * O%
Al%: be the weight percentage of Al element;
Sn%: be the weight percentage of Sn element;
Ga%: be the weight percentage of Ga element;
O%: be the weight percentage of O element.
In the alloy of the present invention, the titanium alloy control routinely of all the other gaps and impurity element.
Alloy of the present invention utilizes vacuum consumable smelting, skull melting, beam-plasma melting, electron beam melting or shower furnace melting method to carry out melting; The ingot casting of alloy of the present invention carries out centre forging or rolling in the above cogging of transformation temperature, makes excellent base.Rod base 100～150 ℃ of scope internal heating on transformation temperature adopt rolling then or the forging and molding method is made bar, and bar adopts direct aging to handle.
Another object of the present invention provides a kind of surface modifying method of above-mentioned high-temperature titanium alloy.
Above-mentioned purpose of the present invention reaches by the following technical programs:
A kind of surface modifying method of high-temperature titanium alloy is characterized in that: adopt ion implantation method that described high-temperature titanium alloy is carried out surface modification, wherein ion implantation amount is Nb or Ta 3 * 10
15-3 * 10
18Ions/cm
2, injecting voltage: 30-60V, electric current: 1-5mA.
Advantage of the present invention is:
1, alloy at room temperature tensile strength of the present invention is not less than 1100MPa, and 650 ℃ high temperature tensile strength is not less than 650MPa.
2, high temperature resistant, the antifatigue of alloy of the present invention, long lifetime, adapt to the use under the hot environment.
3, high-temperature titanium alloy has improved the high-temperature oxidation resistance of high-temperature titanium alloy through surface modification, and then improves the use properties of high-temperature titanium alloy.
The present invention will be further described below by embodiment, but and do not mean that limiting the scope of the invention.
Embodiment
Embodiment 1
Commercially available titanium sponge, zirconium sponge, fine aluminium, pure silicon, aluminium molybdenum master alloy, aluminium neodymium master alloy, titanium niobium tantalum master alloy and aluminium tin master alloy are pressed the composition proportion (weight percent of table 1, be prepared into electrode block down together), electrode block is welded into vacuum consumable electrode in the vacuum plasma case, carry out three vacuum consumable smeltings then and make ingot casting.Ingot casting cogging on transformation temperature is forged, and through making the rolling excellent base of φ 35mm after middle the forging, after excellent base is heated to 1150 ℃, is rolled into φ 15mm bar on open-train mill.
The bar that is rolled into carries out Mechanics Performance Testing by the requirement of GB/T228-2002 after handling through heat treating regime listed in the table 2, and its mechanical property sees Table 2.After the bar that is rolled into passes through ion implantation and heat treatment process listed in the table 3, keep oxide skin to carry out Mechanics Performance Testing, its performance sees Table 3.
Table 1
| Chemical ingredients | ??Al | ??Sn | ??Zr | ??Mo | ??Nb | ??Ta | ??Nd | ??Si | ??O | ??C | ??H | ??N | ??Ti |
| Content | ??6 | ??3 | ??5.5 | ??0.42 | ??0.3 | ??0.2 | ??0.6 | ??0.45 | ??0.08 | ??0.05 | ??0.005 | ??0.006 | Surplus |
Table 2
Table 3
Rm represents tensile strength in the table 2,3, Rp
0.2, the expression yield strength, A represents unit elongation, Z presentation surface shrinkage.Through after the ion implantation technology, the high-temperature behavior of alloy obviously improves.
Embodiment 2
Commercially available titanium sponge, pure hafnium, fine aluminium, pure silicon, aluminium molybdenum master alloy, aluminium yttrium master alloy, titanium niobium master alloy, gallium aluminium master alloy and aluminium tin master alloy are prepared into electrode block by the composition proportion of table 4, electrode block is welded into vacuum consumable electrode in the vacuum plasma case, carry out three vacuum consumable smeltings then and make ingot casting.Ingot casting cogging on transformation temperature is forged, and through making the rolling excellent base of φ 35mm after middle the forging, after excellent base is heated to 1150 ℃, is rolled into φ 15mm bar on open-train mill.
The bar that is rolled into carries out Mechanics Performance Testing by the requirement of GB/T228-2002 after handling through heat treating regime listed in the table 5, and its mechanical property sees Table 5.After the bar that is rolled into passes through ion implantation and heat treatment process listed in the table 6, keep oxide skin to carry out Mechanics Performance Testing, its performance sees Table 6.
The formulated component of table 4 embodiment 2 interalloies
| Chemical ingredients | ??Al | ??Sn | ??Ga | ??Hf | ??Mo | ??Nb | ??Y | ??Si | ??O | ??C | ??H | ??N | ??Ti |
| Content | ??6.9 | ??0.5 | ??0.5 | ??4 | ??0.32 | ??0.32 | ??0.7 | ??0.5 | ??0.10 | ??0.05 | ??0.005 | ??0.006 | Surplus |
The mechanical property of bar among table 5 embodiment 2
The mechanical property of bar after ion implantation among table 6 embodiment 2
Embodiment 3
Commercially available titanium sponge, zirconium sponge, fine aluminium, pure silicon, aluminium molybdenum master alloy, aluminium erbium master alloy, titanium niobium master alloy and aluminium tin master alloy are prepared into electrode block by the composition proportion of table 7, electrode block is welded into vacuum consumable electrode in the vacuum plasma case, carry out three vacuum consumable smeltings then and make ingot casting.Ingot casting cogging on transformation temperature is forged, and through making the rolling excellent base of φ 35mm after middle the forging, after excellent base is heated to 1150 ℃, is rolled into φ 15mm bar on open-train mill.
The bar that is rolled into carries out Mechanics Performance Testing by the requirement of GB/T228-2002 after handling through heat treating regime listed in the table 8, and its mechanical property sees Table 8.After the bar that is rolled into passes through ion implantation and heat treatment process listed in the table 9, keep oxide skin to carry out Mechanics Performance Testing, its performance sees Table 9.
Table 7
| Chemical ingredients | ??Al | ??Sn | ??Ga | ??Hf | ??Mo | ??Nb | ??Y | ??Si | ??O | ??C | ??H | ??N | ??Ti |
| Content | ??5.5 | ??2.5 | ??0.5 | ??5.5 | ??0.5 | ??0.5 | ??0.6 | ??0.5 | ??0.20 | ??0.05 | ??0.005 | ??0.006 | Surplus |
Table 8
Table 9
Embodiment 4
Commercially available titanium sponge, zirconium sponge, fine aluminium, pure silicon, aluminium molybdenum master alloy, aluminium erbium master alloy, titanium niobium master alloy and aluminium tin master alloy are prepared into electrode block by the composition proportion of table 10, electrode block is welded into vacuum consumable electrode in the vacuum plasma case, carry out three vacuum consumable smeltings then and make ingot casting.Ingot casting cogging on transformation temperature is forged, and through making the rolling excellent base of φ 35mm after middle the forging, after excellent base is heated to 1150 ℃, is rolled into φ 15mm bar on open-train mill.
The bar that is rolled into carries out Mechanics Performance Testing by the requirement of GB/T228-2002 after handling through heat treating regime listed in the table 11, and its mechanical property sees Table 11.After the bar that is rolled into passes through ion implantation and heat treatment process listed in the table 12, keep oxide skin to carry out Mechanics Performance Testing, its performance sees Table 12.
Table 10
| Chemical ingredients | ??Al | ??Sn | ??Zr | ??Mo | ??Nb | ??Er | ??Si | ??O | ??C | ??H | ??N | ??Ti |
| Content | ??5.0 | ??3 | ??5 | ??0.5 | ??0.5 | ??0.85 | ??0.55 | ??0.13 | ??0.05 | ??0.005 | ??0.006 | Surplus |
Table 11
Table 12
Embodiment 5
Commercially available titanium sponge, zirconium sponge, fine aluminium, pure silicon, aluminium molybdenum master alloy, aluminium neodymium master alloy, titanium niobium tantalum master alloy and aluminium tin master alloy are pressed the composition proportion (weight percent of table 13, be prepared into electrode block down together), electrode block is welded into vacuum consumable electrode in the vacuum plasma case, carry out three vacuum consumable smeltings then and make ingot casting.Ingot casting cogging on transformation temperature is forged, and through making the rolling excellent base of φ 35mm after middle the forging, after excellent base is heated to 1150 ℃, is rolled into φ 15mm bar on open-train mill.
The bar that is rolled into carries out Mechanics Performance Testing by the requirement of GB/T228-2002 after handling through heat treating regime listed in the table 14, and its mechanical property sees Table 14.After the bar that is rolled into passes through ion implantation and heat treatment process listed in the table 15, keep oxide skin to carry out Mechanics Performance Testing, its performance sees Table 15.
Table 13
| Chemical ingredients | ??Al | ??Sn | ??Zr | ??Mo | ??Nb | ??Ta | ??Nd | ??Si | ??O | ??C | ??H | ??N | ??Ti |
| Content | ??6 | ??3 | ??5.5 | ??0.42 | ??0.24 | ??0.26 | ??0.6 | ??0.45 | ??0.09 | ??0.05 | ??0.005 | ??0.006 | Surplus |
Table 14
Table 15
Claims (5)
1. high-temperature titanium alloy comprises:
5.5-7 the Al of weight %;
0.5-3 the Sn of weight % and/or Ga;
0.08-0.2 0 of weight %, and [Al] value is 7.5～8.5;
0.45 the Si of～0.55 weight %;
The Zr of 4～5.5 weight % or Hf;
0.3 the Mo of～0.5 weight %;
0.3 the Nb of～0.5 weight % and/or Ta;
0.6 the rare earth element y of～0.85 weight %, Nd or Er;
Surplus is a titanium.
2. high-temperature titanium alloy according to claim 1 is characterized in that: described [Al]=Al weight %+0.46 * Sn weight %+0.42 * Ga weight %+6.7 * 0 weight %.
3. high-temperature titanium alloy according to claim 1 is characterized in that: described high-temperature titanium alloy also contains C, H, N element, the titanium alloy control routinely of its content.
4. the surface modifying method of each described high-temperature titanium alloy of claim 1-3, it is characterized in that: adopt ion implantation method that described high-temperature titanium alloy is carried out surface modification, wherein ion implantation amount is Nb or Ta3 * 10
15-3 * 10
18Ions/cm
2, injecting voltage: 30-60V, electric current: 1-5mA.
5. the surface modifying method of high-temperature titanium alloy according to claim 4, it is characterized in that: described ion implantation amount is Nb or Ta 6 * 10
15-3 * 10
18Ions/cm
2, injecting voltage: 35-55V, electric current: 3.5-5mA.
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| CN102605326A (en) * | 2011-01-25 | 2012-07-25 | 鸿富锦精密工业（深圳）有限公司 | Shell and manufacturing method thereof |
| CN102888583A (en) * | 2012-10-29 | 2013-01-23 | 中国科学院上海硅酸盐研究所 | CoNiCrAlY coating and production process and application thereof |
| JP2014208873A (en) * | 2013-03-29 | 2014-11-06 | 独立行政法人物質・材料研究機構 | High-strength titanium alloy having excellent oxidation resistance and compressor component using the same |
| CN104532059A (en) * | 2014-12-16 | 2015-04-22 | 中国航空工业集团公司北京航空材料研究院 | Rare-earth containing high-temperature titanium alloy and preparation method thereof |
| CN104745870A (en) * | 2015-04-14 | 2015-07-01 | 张岗 | Artificial joint |
| CN105734339A (en) * | 2014-12-06 | 2016-07-06 | 沈阳市亨运达钛业开发有限公司 | High-temperature-resistant titanium alloy bar and preparation method thereof |
| CN105755413A (en) * | 2015-04-14 | 2016-07-13 | 张岗 | Artificial joint heat treatment method |
| CN105838923A (en) * | 2016-05-31 | 2016-08-10 | 大连理工大学 | High-strength and high-plasticity titanium alloy with resistance to high-temperature oxidation at 800 DEG C |
| CN106801164A (en) * | 2015-11-26 | 2017-06-06 | 北京有色金属研究总院 | A kind of Short-time high-temperature high-strength titanium alloy and preparation method thereof |
| CN107058804A (en) * | 2017-04-19 | 2017-08-18 | 中国航发北京航空材料研究院 | A kind of high-temperature titanium alloy of high heat-intensity |
| WO2018076985A1 (en) * | 2016-10-25 | 2018-05-03 | 林海英 | Titanium alloy and preparation method therefor |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102605326A (en) * | 2011-01-25 | 2012-07-25 | 鸿富锦精密工业（深圳）有限公司 | Shell and manufacturing method thereof |
| CN102888583A (en) * | 2012-10-29 | 2013-01-23 | 中国科学院上海硅酸盐研究所 | CoNiCrAlY coating and production process and application thereof |
| CN102888583B (en) * | 2012-10-29 | 2014-09-10 | 中国科学院上海硅酸盐研究所 | CoNiCrAlY coating and production process and application thereof |
| JP2014208873A (en) * | 2013-03-29 | 2014-11-06 | 独立行政法人物質・材料研究機構 | High-strength titanium alloy having excellent oxidation resistance and compressor component using the same |
| CN105734339A (en) * | 2014-12-06 | 2016-07-06 | 沈阳市亨运达钛业开发有限公司 | High-temperature-resistant titanium alloy bar and preparation method thereof |
| CN104532059A (en) * | 2014-12-16 | 2015-04-22 | 中国航空工业集团公司北京航空材料研究院 | Rare-earth containing high-temperature titanium alloy and preparation method thereof |
| CN104745870A (en) * | 2015-04-14 | 2015-07-01 | 张岗 | Artificial joint |
| CN105755413A (en) * | 2015-04-14 | 2016-07-13 | 张岗 | Artificial joint heat treatment method |
| CN106801164B (en) * | 2015-11-26 | 2019-03-08 | 北京有色金属研究总院 | A kind of Short-time high-temperature high-strength titanium alloy and preparation method thereof |
| CN106801164A (en) * | 2015-11-26 | 2017-06-06 | 北京有色金属研究总院 | A kind of Short-time high-temperature high-strength titanium alloy and preparation method thereof |
| CN105838923A (en) * | 2016-05-31 | 2016-08-10 | 大连理工大学 | High-strength and high-plasticity titanium alloy with resistance to high-temperature oxidation at 800 DEG C |
| CN105838923B (en) * | 2016-05-31 | 2017-11-07 | 大连理工大学 | A kind of high-strength plasticity titanium alloy of anti-800 DEG C of high-temperature oxydations |
| WO2018076985A1 (en) * | 2016-10-25 | 2018-05-03 | 林海英 | Titanium alloy and preparation method therefor |
| CN107058804A (en) * | 2017-04-19 | 2017-08-18 | 中国航发北京航空材料研究院 | A kind of high-temperature titanium alloy of high heat-intensity |
| CN113355560A (en) * | 2021-08-10 | 2021-09-07 | 北京煜鼎增材制造研究院有限公司 | High-temperature titanium alloy and preparation method thereof |
| CN113355560B (en) * | 2021-08-10 | 2021-12-10 | 北京煜鼎增材制造研究院有限公司 | High-temperature titanium alloy and preparation method thereof |
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Open date: 20100707 |