CN103014412A - Composite heat-resistant titanium alloy - Google Patents
Composite heat-resistant titanium alloy Download PDFInfo
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- CN103014412A CN103014412A CN2011102891755A CN201110289175A CN103014412A CN 103014412 A CN103014412 A CN 103014412A CN 2011102891755 A CN2011102891755 A CN 2011102891755A CN 201110289175 A CN201110289175 A CN 201110289175A CN 103014412 A CN103014412 A CN 103014412A
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Abstract
The invention discloses a composite heat-resistant titanium alloy. The alloy comprises the following raw materials by weight percent: 4-8% of aluminium, 1-7% of tin, 2-8% of zirconium, 0.25-4% of tungsten, 0.1-0.5% of silicon, 0.2-2.5% of niobium and the balance of titanium and inevitable impurities. The titanium alloy has the excellent characteristics shown in the specification.
Description
Technical field
The present invention relates to a kind of heat-resistant titanium alloy, particularly relate to a kind of heat-resistant titanium alloy of the titanium alloy component for the manufacture of using under the various hot environments.
Background technology
Heat-resistant titanium alloy is to make for example necessary advanced material of aircraft engine of contemporary high performance aircraft material, along with improving constantly of motor performance, the performance of heat-resistant titanium alloy has also been proposed more and more higher requirement.
CN1031721A discloses the heat-resistant titanium alloy that a kind of maximum operation (service) temperature can reach 550 ℃, it is characterized in that adopting rear earth element nd (Nd) to make titanium alloy strengthen and improve the antioxidant property of titanium alloy surface.The composition range of alloy is: aluminium 2.5～7; Tin 2～11; Zirconium 0.5～5; Molybdenum 0.2～2; Silicon 0.08～0.5; Neodymium 0.2～2.5; The titanium surplus, its optimal components scope is aluminium 4.5～6.5; Tin 3～6; Zirconium 1～3; Molybdenum 0.5～1.5; Silicon 0.1～0.3; Neodymium 0.5～1.5; The titanium surplus.It is said that this heat-resistant titanium alloy still maintains the over-all propertieies such as good high-temperature tensile strength, creep strength and thermostability under 550 ℃.
Advanced aero engine requires the use temperature of titanium alloy will reach 600 ℃ at present, and the ultimate-use temperature of conventional titanium alloy is exactly 600 ℃, some performance of alloy sharply worsens under this temperature, and especially creep-resistant property and thermal stability can't satisfy service requirements.
High-temperature titanium alloy is mainly used in space flight, aviation etc. and requires resistant to elevated temperatures field.Harsh to the requirement of high-temperature titanium alloy such as aircraft engine, it requires material to have the coupling of good room-temperature property, hot strength, creep property, thermostability, fatigue property and fracture toughness property etc.The raising of material at high temperature performance is depended in the raising of motor performance to a great extent, and engine design slip-stick artist is also more and more higher to the requirement of high-temperature titanium alloy performance.The alloys such as IMI834 (Britain), Ti-1100 (U.S.), BT36 (Russia) have been applied to aerospace field as 600 ℃ of titanium alloys, China is also fruitful in this regard, and development has obtained Ti60, Ti600 and the Burn-Resistant Titanium Alloy Ti40 of 600 ℃ of uses.
The people such as Mao Xiaonan are in " Rare Metals Materials and engineering ", in June, 2004, the 6th phase of the 33rd volume, 620-623, write articles " the Properties and Microstructure features of TP 650 granule intensified titanium-base compound materials ", the TP650 alloy is expected to become 650 ℃ of titanium alloys, has easy processing, low cost, stable interface, heat-proof corrosion-resistant, the characteristics such as wear-resisting, but its intensity of 700 ℃ only is equivalent to IMI834 and Ti1100 650 ℃ intensity, and its heat resisting temperature can't further improve.Present 700 ℃ of Typical Representatives with the titanium material are Ti
3The Al base intermetallic compound is characterized in specific tenacity high ratio modulus height and flame resistant, but temperature-room type plasticity and fracture toughness property are low.Yet, with 600 ℃ of high-temperature titanium alloys of external acquisition practical application relatively, domestic 600 ℃ of high-temperature titanium alloy over-all propertieies with abroad remain in gap, can not satisfy the demand of national space flight, aviation field.The thermostability of titanium alloy between 600 ℃-700 ℃ is mainly concerned with fragility phase Ti
3X (X=Al, Ge, In, Sn etc.) separates out, and usually adopts the method that improves the alloy use temperature by improving alloy content might cause fragility phase Ti
3X separates out, thereby falls low-alloyed thermostability.Should control kind and the content of alloying element, avoid occurring the deterioration of thermostability.
The novel heat-resistant titanium alloy of excellent properties is still expected to have in this area.
Summary of the invention
The objective of the invention is for above-mentioned the deficiencies in the prior art, provide a kind of when use temperature reaches 600 ℃, its creep-resistant property and thermal stability still can satisfy the heat-resistant titanium alloy of service requirements.
To achieve these goals, the technical solution used in the present invention is: a kind of heat-resistant titanium alloy is characterized in that this alloy is comprised of the raw material of following weight percentage:
Aluminium 4%～8%, tin 1%～7%, zirconium 2%～8%,
Tungsten 0.25%～4%, silicon 0.1%～0.5%, niobium 0.2%～2.5%, all the other are titanium and inevitable impurity.
In an embodiment of titanium alloy of the present invention, the weight percentage of described aluminium is 4.5%～7.5%.
In an embodiment of titanium alloy of the present invention, the weight percentage of described tin is 1.5%～6.5%.
In an embodiment of titanium alloy of the present invention, the weight percentage of described zirconium is 2.5%～8%.
In an embodiment of titanium alloy of the present invention, the weight percentage of described tungsten is 0.4%～3.5%.
In an embodiment of titanium alloy of the present invention, the weight percentage of described silicon is 0.1%～0.45%.
In an embodiment of titanium alloy of the present invention, the weight percentage of described niobium is 0.25%～2.25%.
In some embodiments of titanium alloy of the present invention, it basically has such as the described prescription of embodiment hereinafter and forms and proportioning.
What the present invention was designed is a kind of seven constituent element titanium alloys, adopt the high temperature solid solution principle, in alloy, add weight percent and be 0.25～4% refractory metal W elements, 0.1%～0.5% element silicon and 0.2%～2.5% niobium element, can carry heavy alloyed hot strength and creep-resistant property; The tissue of alloy obtains refinement simultaneously, and fatigue property significantly improves; And the process industrial art performance of alloy is improved, make it obtain preferably over-all properties.
The preparation process of this product is: be aluminium more than 99% with purity, three kinds of metals of zirconium and niobium (particle or bits) and titanium-80 tin, aluminium-20 tungsten, three kinds of master alloys of aluminium-10 silicon are aluminium 4%～8% by weight percentage, tin 1%～7%, zirconium 2%～8%, tungsten 0.25%～4%, silicon 0.1%～0.5%, niobium 0.2%～2.5%, all the other are prepared for titanium, then be pressed into block electrode at oil press, and with several piece electrode employing Plasma Welding assembly welding growth strip shaped electric poles, then in vacuum consumable electrode arc furnace, carry out 2～3 meltings, melted ingot casting is heated to 1100 ℃ forges processing, finally make the bar of all size; Or be forged into slab, then slab rolling is become the sheet material of various thickness.
In one embodiment, the ingot casting of titanium alloy of the present invention adopts the vacuum consumable electrode arc furnace melting, and the melting number of times is three times.In one embodiment, the ingot casting of titanium alloy of the present invention adopts the vacuum consumable electrode arc furnace melting, and the melting number of times is three times, and the pressure of last melting steady stage should be not more than 5Pa.In one embodiment, described consumable electrode does not use Tig Welding.
In one embodiment of the invention, the mechanical property of titanium alloy of the present invention is tested at the sample base after β phase region solid solution+timeliness thermal treatment, and the heat treating regime that can adopt is 1000～1020 ℃, insulation 0.25～4h, stove is chilled to 920 ℃～960 ℃ insulation 0.25～4h, air cooling; 920～940 ℃, insulation 0.25～4h, stove are chilled to 750 ℃～850 ℃ insulation 0.25～4h, air cooling.
In one embodiment of the invention, the mechanical property of titanium alloy of the present invention is tested at the sample base after alpha+beta phase region solid solution+timeliness thermal treatment, the alpha+beta phase region solid solution that can adopt+timeliness heat treating regime is 920～950 ℃, insulation 0.25～4h, air cooling; 750 ℃ of insulation 0.25～4h, air cooling.
In one embodiment of the invention, the mechanical property of titanium alloy of the present invention is tested at the sample base after β phase region solid solution+timeliness thermal treatment, the β phase region solid solution that can adopt+timeliness heat treating regime is 1000～1020 ℃, insulation 1～4h, stove is chilled to 920 ℃～960 ℃ insulation 1～4h, air cooling; 920～940 ℃, insulation 1～4h, stove are chilled to 750 ℃～850 ℃ insulation 1～4h, air cooling.
In one embodiment of the invention, the mechanical property of titanium alloy of the present invention is tested at the sample base after alpha+beta phase region solid solution+timeliness thermal treatment, the alpha+beta phase region solid solution that can adopt+timeliness heat treating regime is 920～950 ℃, insulation 1～4h, air cooling; 750 ℃ of insulation 1～4h, air cooling.
In one embodiment of the invention, the heat treating regime of titanium alloy of the present invention can be 1000～1020 ℃, and insulation 0.25～4h, stove are chilled to 920 ℃～960 ℃ insulation 0.25～4h, air cooling; 920～940 ℃, insulation 0.25～4h, stove are chilled to 750 ℃～850 ℃ insulation 0.25～4h, air cooling.
In one embodiment of the invention, the heat treating regime of titanium alloy of the present invention can be 920～950 ℃, insulation 0.25～4h, air cooling; 750 ℃ of insulation 0.25～4h, air cooling.
In one embodiment of the invention, the heat treating regime of titanium alloy of the present invention can be 1000～1020 ℃, and insulation 1～4h, stove are chilled to 920 ℃～960 ℃ insulation 1～4h, air cooling; 920～940 ℃, insulation 1～4h, stove are chilled to 750 ℃～850 ℃ insulation 1～4h, air cooling.
In one embodiment of the invention, the heat treating regime of titanium alloy of the present invention can be 920～950 ℃, insulation 1～4h, air cooling; 750 ℃ of insulation 1～4h, air cooling.
The titanium alloy rod bar that the present invention is prepared and sheet material have good over-all properties, especially creep-resistant property and excellent heat stability.For example heat-resistant titanium alloy of the present invention has following premium properties in one embodiment:
Room temperature tensile performance Rm 〉=880MPa, A5 〉=12%, Z 〉=24%;
Residual set≤0.12% under 600 ℃/150MPa/100h of the high temperature creep property condition;
After 600 ℃/100h of thermostability heat exposes, Rm 〉=840MPa, A5 〉=6%, Z 〉=9%;
Room temperature fatigue property R=-1, σ 〉=430Mpa.
This alloy has good weldability simultaneously, can adopt vacuum electron beam or argon arc welding method alloy sheet material to carry out welding processing, and the welding strength coefficient is greater than 90%.
The present invention compared with prior art has the following advantages: the present invention has good over-all properties, especially creep-resistant property and excellent heat stability, creep-resistant property and thermostability form good coupling, can 600 ℃ in addition under 700 ℃ of conditions life-time service; This alloy has good weldability simultaneously, can adopt vacuum electron beam or argon arc welding method alloy sheet material to carry out welding processing, and the welding strength coefficient is greater than 90%.
Embodiment
The present invention will be further described below in conjunction with embodiment.
In the present invention, the testing method of correlation parameter can be used currently known methods, for example uses the method for following standard record: GB/T 228-2002 metal tensile test method; GB/T 232-1999 bend test of metal method; GB/T 3621-1994 titanium or titanium alloy sheet material; GB/T 4698-1996 titanium or titanium alloy chemical analysis method; The GB/T 5168-1985 diphasic titanium alloy high-low time tissue method of inspection; Plate defect detection on ultrasonic basis in Q/BS 0505 titanium or titanium alloy; GB/T 3620.2 titanium and its alloy work product chemical ingredientss and composition permissible variation.
Embodiment 1
The raw material of present embodiment alloy forms and weight percentage is:
Aluminium 8%, tin 1%, zirconium 8%,
Tungsten 0.25%, silicon 0.5%, niobium 0.2%, all the other are titanium and inevitable impurity.
Preparation technology: be that aluminium, zirconium and three kinds of metals of niobium (particle or bits) more than 99% and titanium-80 tin, aluminium-20 tungsten, three kinds of master alloys of aluminium-10 silicon are prepared by said ratio with purity; then be pressed into block electrode at oil press; and with several piece electrode employing Plasma Welding assembly welding growth strip shaped electric poles; then in vacuum consumable electrode arc furnace, carry out 2～3 meltings; melted ingot casting is heated to 1100 ℃ forges processing, finally make the bar of all size.
The prepared alloy bar material of present embodiment has good over-all properties, especially creep-resistant property and excellent heat stability:
Room temperature tensile performance Rm 〉=880MPa, A5 〉=12%, Z 〉=24%;
Residual set≤0.12% under 600 ℃/150MPa/100h of the high temperature creep property condition;
After 600 ℃/100h of thermostability heat exposes, Rm 〉=840MPa, A5 〉=6%, Z 〉=9%;
Room temperature fatigue property R=-1, σ 〉=430Mpa.
Embodiment 2
The raw material of present embodiment alloy forms and weight percentage is:
Aluminium 4%, tin 7%, zirconium 2%,
Tungsten 4%, silicon 0.1%, niobium 2.5%, all the other are titanium and inevitable impurity.
Preparation technology: be that aluminium, zirconium and three kinds of metals of niobium (particle or bits) more than 99% and titanium-80 tin, aluminium-20 tungsten, three kinds of master alloys of aluminium-10 silicon are prepared by said ratio with purity; then be pressed into block electrode at oil press; and with several piece electrode employing Plasma Welding assembly welding growth strip shaped electric poles; then in vacuum consumable electrode arc furnace, carry out 2～3 meltings; melted ingot casting is heated to 1150 ℃ forges processing; be forged into slab, then slab rolling become the sheet material of various thickness.
The prepared sheet alloy of present embodiment has good over-all properties, especially creep-resistant property and excelling in fatigue property:
Room temperature tensile performance Rm 〉=950MPa, A5 〉=13%, Z 〉=24%;
Residual set≤0.15% under 600 ℃/170MPa/100h of the high temperature creep property condition;
After 600 ℃/100h of thermostability heat exposes, Rm 〉=920MPa, A5 〉=6%, Z 〉=10%;
Room temperature fatigue property R=-1, σ 〉=450Mpa.
This alloy has good weldability simultaneously, can adopt vacuum electron beam or argon arc welding method alloy sheet material to carry out welding processing, and the welding strength coefficient is greater than 90%.
Embodiment 3
The raw material of present embodiment alloy forms and weight percentage is:
Aluminium 6.8%, tin 2.8%, zirconium 7.8%,
Tungsten 0.7%, silicon 0.375%, niobium 0.4%, all the other are titanium and inevitable impurity.
Preparation technology: be that aluminium, zirconium and three kinds of metals of niobium (particle or bits) more than 99% and titanium-80 tin, aluminium-20 tungsten, three kinds of master alloys of aluminium-10 silicon are prepared by said ratio with purity; then be pressed into block electrode at oil press; and with several piece electrode employing Plasma Welding assembly welding growth strip shaped electric poles; then in vacuum consumable electrode arc furnace, carry out 2～3 meltings; melted ingot casting is heated to 1200 ℃ forges processing; be forged into slab, then slab rolling become the sheet material of various thickness.
The prepared sheet alloy of present embodiment has good over-all properties, especially creep-resistant property and room temperature excelling in fatigue property:
Room temperature tensile performance Rm 〉=970MPa, A5 〉=10%, Z 〉=23%;
Residual set≤0.10% under 600 ℃/150MPa/100h of the high temperature creep property condition;
After 600 ℃/100h of thermostability heat exposes, Rm 〉=910MPa, A5 〉=6%, Z 〉=9%;
Room temperature fatigue property R=-1, σ 〉=470Mpa.
This alloy has good weldability simultaneously, can adopt vacuum electron beam or argon arc welding method alloy sheet material to carry out welding processing, and the welding strength coefficient is greater than 90%.
Embodiment 4
The raw material of present embodiment alloy forms and weight percentage is:
Aluminium 5.2%, tin 5.3%, zirconium 4.25%, tungsten 2.25%, silicon 0.1%, niobium 1.75%, all the other are titanium and inevitable impurity.
Preparation technology: be that aluminium, zirconium and three kinds of metals of niobium (particle or bits) more than 99% and titanium-80 tin, aluminium-20 tungsten, three kinds of master alloys of aluminium-10 silicon are prepared by said ratio with purity; then be pressed into block electrode at oil press; and with several piece electrode employing Plasma Welding assembly welding growth strip shaped electric poles; then in vacuum consumable electrode arc furnace, carry out 2～3 meltings; melted ingot casting is heated to 1200 ℃ forges processing; be forged into slab, then slab rolling become the sheet material of various thickness.
The prepared sheet alloy of present embodiment has good over-all properties, especially creep-resistant property and excellent heat stability:
Room temperature tensile performance Rm 〉=960MPa, A5 〉=9%, Z 〉=22%;
Residual set≤0.2% under 600 ℃/160MPa/100h of the high temperature creep property condition;
After 600 ℃/100h of thermostability heat exposes, Rm 〉=910MPa, A5 〉=6%, Z 〉=9%;
Room temperature fatigue property R=-1, σ 〉=420Mpa.
This alloy has good weldability simultaneously, can adopt vacuum electron beam or argon arc welding method alloy sheet material to carry out welding processing, and the welding strength coefficient is greater than 90%.
Embodiment 5
The raw material of present embodiment alloy forms and weight percentage is:
Aluminium 4.5%, tin 3%, zirconium 4.5%, tungsten 0.8%, silicon 0.4%, niobium 0.4%, all the other are titanium and inevitable impurity.
Preparation technology: be that aluminium, zirconium and three kinds of metals of niobium (particle or bits) more than 99% and titanium-80 tin, aluminium-20 tungsten, three kinds of master alloys of aluminium-10 silicon are prepared by said ratio with purity; then be pressed into block electrode at oil press; and with several piece electrode employing Plasma Welding assembly welding growth strip shaped electric poles; then consume in vain in vacuum and carry out 2～3 meltings in the electric arc furnace; processing is forged in 1150 ℃ of melted ingot casting heating, finally make the bar of all size.
The prepared alloy bar material of present embodiment has good over-all properties:
Room temperature tensile performance Rm 〉=850MPa, A5 〉=11%, Z 〉=24%;
Residual set≤0.15% under 600 ℃/160MPa/100h of the high temperature creep property condition;
After 600 ℃/100h of thermostability heat exposes, Rm 〉=800MPa, A5 〉=6%, Z 〉=9%;
Room temperature fatigue property R=-1, σ 〉=460Mpa.
Comparative example 1
This comparative example alloy formula and preparation technology are basically with reference to above-described embodiment 5, and difference is that the niobium in the alloy formula is replaced with yttrium.
Prepared alloy bar material performance is as follows:
Room temperature tensile performance Rm 〉=740MPa, A5 〉=7%, Z 〉=18%;
Residual set≤0.28% under 600 ℃/160MPa/100h of the high temperature creep property condition;
After 600 ℃/100h of thermostability heat exposes, Rm 〉=710MPa, A5 〉=3%, Z 〉=6%;
Room temperature fatigue property R=-1, σ 〉=420Mpa.
Claims (8)
1. heat-resistant titanium alloy is characterized in that this alloy is comprised of the raw material of following weight percentage:
Aluminium 4%～8%, tin 1%～7%, zirconium 2%～8%,
Tungsten 0.25%～4%, silicon 0.1%～0.5%, niobium 0.2%～2.5%, all the other are titanium and inevitable impurity.
2. according to claim 1 heat-resistant titanium alloy, the weight percentage of wherein said aluminium is 4.5%～7.5%.
3. according to claim 1 to 2 each heat-resistant titanium alloys, the weight percentage of wherein said tin is 1.5%～6.5%.
4. according to claim 1 to 3 each heat-resistant titanium alloys, the weight percentage of wherein said zirconium is 2.5%～8%.
5. according to claim 1 to 4 each heat-resistant titanium alloys, the weight percentage of wherein said tungsten is 0.4%～3.5%.
6. according to claim 1 to 5 each heat-resistant titanium alloys, the weight percentage of wherein said silicon is 0.1%～0.45%.
7. according to claim 1 to 6 each heat-resistant titanium alloys, the weight percentage of wherein said niobium is 0.25%～2.25%.
8. according to claim 1 to 7 each heat-resistant titanium alloys, it basically has such as the described prescription of embodiment and forms and proportioning.
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| CN104561657A (en) * | 2014-12-26 | 2015-04-29 | 农彩丽 | Titanium-aluminium alloy material and preparation technology thereof |
| CN104611610A (en) * | 2013-11-05 | 2015-05-13 | 北京有色金属研究总院 | High-temperature and high-strength titanium alloy and preparation method thereof |
| CN104762524A (en) * | 2015-03-18 | 2015-07-08 | 沈阳市亨运达钛业开发有限公司 | Ultrahigh temperature titanium alloy and preparation method thereof |
| CN108149068A (en) * | 2018-01-04 | 2018-06-12 | 陈国财 | A kind of preparation method of superhigh temperature titanium alloy |
| CN108913945A (en) * | 2018-08-03 | 2018-11-30 | 燕山大学 | A kind of high-strength titanium alloy and preparation method thereof |
| CN110484774A (en) * | 2019-09-24 | 2019-11-22 | 西北有色金属研究院 | A kind of resistance to 650 DEG C of high-temperature titanium alloys |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104611610A (en) * | 2013-11-05 | 2015-05-13 | 北京有色金属研究总院 | High-temperature and high-strength titanium alloy and preparation method thereof |
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| CN108149068A (en) * | 2018-01-04 | 2018-06-12 | 陈国财 | A kind of preparation method of superhigh temperature titanium alloy |
| CN108149068B (en) * | 2018-01-04 | 2020-02-21 | 陈国财 | Preparation method of ultrahigh-temperature titanium alloy |
| CN108913945A (en) * | 2018-08-03 | 2018-11-30 | 燕山大学 | A kind of high-strength titanium alloy and preparation method thereof |
| CN108913945B (en) * | 2018-08-03 | 2019-07-26 | 燕山大学 | A kind of high-strength titanium alloy and preparation method thereof |
| CN110484774A (en) * | 2019-09-24 | 2019-11-22 | 西北有色金属研究院 | A kind of resistance to 650 DEG C of high-temperature titanium alloys |
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Application publication date: 20130403 |