CN100460541C - Composite heat-resisting enhance titanium alloy - Google Patents
Composite heat-resisting enhance titanium alloy Download PDFInfo
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- CN100460541C CN100460541C CNB2007100423044A CN200710042304A CN100460541C CN 100460541 C CN100460541 C CN 100460541C CN B2007100423044 A CNB2007100423044 A CN B2007100423044A CN 200710042304 A CN200710042304 A CN 200710042304A CN 100460541 C CN100460541 C CN 100460541C
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Abstract
A composite enhanced heat-resisting titanium-alloy consists of Al 3-8%, Sn 1-6%, Zr 1-6%, Mo 0.5-2%, Nb 0.5-1.5%, Si 0.1-0.8%, La 0.3-1%, B 0.1-0.5% and Ti residue. It has excellent heat, creep resistances and thermal stability at 650-700 degree. It can be used for aviation and aerospace.
Description
Technical field
What the present invention relates to is a kind of titanium alloy of metallic substance technical field, specifically is a kind of composite heat-resisting enhance titanium alloy.
Background technology
High-temperature titanium alloy is mainly used in space flight, aviation etc. and requires resistant to elevated temperatures field.As the requirement harshness of aircraft engine to high-temperature titanium alloy, 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 high-temperature titanium alloy performance demands.IMI834 (Britain), Ti-1100 (U.S.), BT36 alloys such as (Russia) have been applied to aerospace field as 600 ℃ of titanium alloys, and China is also fruitful in this regard, and development has obtained Ti60, Ti600 and the fire-retardant titanium alloy T i40 of 600 ℃ of uses.
Find by literature search, people such as Mao Xiaonan are in " Rare Metals Materials and engineering ", in June, 2004, the 33rd the 6th phase of volume, 620-623 writes articles " performance of TP_650 granule intensified titanium-base compound material and tissue signature ", the TP650 alloy is expected to become 650 ℃ of titanium alloys, have easy processing, low cost, stable interface, heat-proof corrosion-resistant, characteristics such as wear-resisting, but its intensity of 700 ℃ only is equivalent to IMI834 and Ti1100 650 ℃ intensity, its heat resisting temperature can't further improve.Present 700 ℃ of typical case's 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 employing might cause fragility phase Ti by the method that the raising alloy content improves the alloy use temperature usually
3X separates out, thereby reduces the thermostability of alloy.Should control the kind and the content of alloying element, avoid occurring the deterioration of thermostability.
Summary of the invention
The objective of the invention is to overcome the deficiencies in the prior art, a kind of composite heat-resisting enhance titanium alloy is provided.Adopt the vacuum consumable smelting technology, the synthetic titanium alloy that contains the TiB wild phase, and add earth La, and absorb the oxygen element in the alloy, generate oxide strengthened alloy simultaneously.Composite heat-resisting enhance titanium alloy maximum operation (service) temperature of the present invention can reach 700 ℃.
The present invention is achieved by the following technical solutions, and each component weight percent content of the present invention is: Al3%-8%; Sn 1%-6%; Zr 1%-6%; Mo 0.5%-2%; Nb 0.5%-1.5%; Si 0.1%-0.8%; La 0.3%-1%; B 0.1%-0.5%; Ti is a surplus.
Described Al, its preferable range is: 4%-7%; Described Sn, its preferable range is: 3%-5%; Described Zr, its preferable range is: 3%-5%; Described Mo, its preferable range is: 0.6%-1.5%; Described Nb, its preferable range is: 0.5%-1%; Described Si, its preferable range is: 0.3%-0.6%; Described La, its preferable range is: 0.4%-0.9%; Described B, its preferable range is: 0.15%-0.4%.
Each element of the present invention all adds in the feedstock production process, except that Al, Zr, Si, all the other each alloying elements all add in the raw material with the form of master alloy or compound, and specific as follows: Nb adds in the mode of AlNb master alloy, and it contains Nb amount (weight percent) and is 40%-65%; Mo adds in the mode of AlMo master alloy, and it contains Mo amount (weight percent) and is 40%-65%; Sn adds in the mode of TiSn master alloy, and it contains Sn amount (weight percent) and is 50%-80%; La and B add with compound form between the two, and it contains La amount (weight percent) and is 67%-76%.Titanium alloy provided by the invention is to be prepared by the vacuum consumable electrode arc furnace melting, in order to guarantee the homogeneity of Chemical Composition, has adopted twice melting in the preparation process at least, generally adopts three meltings.Concrete preparation method is as follows for material: take by weighing titanium sponge (one-level), lanthanum boron compound, alloying element and each master alloy at first in proportion, it is mixed; Then utilize press that the raw material that mixes is pressed into electrode bar; Then electrode is put into vacuum consumable electrode arc furnace and carry out melting once, obtain one time ingot; Again with two ingots with welding in argon welder welding or the stove after, put into consumable electroarc furnace and carry out secondary smelting, obtain the secondary ingot; Carry out three meltings with twice melting operation.The chemical reaction that takes place in the fusion process is: 12Ti+2LaB
6+ 3[O]=12TiB+La
2O
3Secondary ingot behind the car light of surface or three ingots carry out secondary hot-work at 960-1010 ℃ again through 1100-1150 ℃ of open die forging cogging, and the deflection of cogging and secondary processing preferably all is controlled at more than 75%, obtains the material that can heat-treat.Preferred thermal treatment process is the ageing treatment of 1100 ℃, 1 hour, the solution treatment of air cooling and 650 ℃, 2 hours, air cooling.Recommend the alloy after the heat treating regime to be organized as the master, in matrix, generated acicular ceramic phase, be TiB, also generated tiny La with lamellated
2O
3Particle.In addition, find that also acicular TiB has formed certain arranging along machine direction.
Titanium alloy provided by the invention still keeps good high-temperature intensity, creep resistance, over-all properties such as thermally-stabilised under 650-700 ℃, can be applicable to the high temperature resistant field of space flight, aviation.
The present invention still maintains good high-temperature stretching, creep resistance, over-all properties such as thermally-stabilised under 650-700 ℃, and this alloy temperature-room type plasticity is good, and is less 1100-1150 ℃ of resistance to deformation, is easy to processing.Titanium alloy provided by the invention is for aircraft engine of new generation provides ideal compressor disc and blade material.
Description of drawings
Fig. 1 concerns synoptic diagram over time for composite heat-resisting enhance titanium alloy and Ti1100, IMI834, the TP650 alloy high-temp tensile strength of example 1 preparation.
Fig. 2 is the composite heat-resisting enhance titanium alloy of example 1 preparation and the steady state creep speed and the initial stress relation contrast synoptic diagram of IMI834 alloy.
Fig. 3 is the composite heat-resisting enhance titanium alloy of example 1 preparation and the creep rupture life and the initial stress relation contrast synoptic diagram of IMI834 alloy.
Embodiment
Below embodiments of the invention are elaborated: present embodiment has provided detailed embodiment and process being to implement under the prerequisite with the technical solution of the present invention, but protection scope of the present invention is not limited to following embodiment.
Take by weighing one-level titanium sponge (79.8%), LaB by mass percentage
x(the wherein mass percent 70% of La) compound (0.7%), AlNb (mass percent 53% of Nb) master alloy powder (1.6%), aluminium powder (4.2%), AlMo (mass percent 50% of Al and Mo) master alloy powder (2.0%), TiSn (mass percent 65% of Sn) master alloy powder (6.9%), zirconium sponge (4.5%), silicon metal (0.3%), preparation quality per-cent are the composite heat-resisting enhance titanium alloy of Al 6%-Sn 4.5%-Zr 4.5%-Mo 1%-Nb 0.9%-Si 0.3%-La 0.5%-B 0.2%.The raw material that mixes is pressed into electrode bar; Then electrode is put into vacuum consumable electrode arc furnace and carry out melting once, obtain one time ingot; Again with two ingots with welding in argon welder or the stove after, put into consumable electroarc furnace and carry out secondary smelting, obtain the secondary ingot; The melting treatment process is identical with secondary smelting for the third time.Three ingots behind the car light of surface obtain pole through 1100 ~ 1150 ℃ of open die forging coggings, carry out secondary hot-work at 960～1010 ℃ again, and the deflection of cogging and secondary processing obtains the material that can heat-treat all more than 75%.The thermal treatment process of adopt recommending: 1100 ℃, 1 hour, solution treatment+650 of air cooling ℃, 2 hours, the ageing treatment of air cooling can make TiB and La
2O
3The heat-resistant titanium alloy of strengthening.This alloy wild phase is tiny and be evenly distributed, room temperature tensile performance, high temperature tensile properties, creep property and thermal stability obviously are better than IMI834, Ti1100 and TP650 alloy, list four kinds of various performance datas of alloy below respectively, shown in table 1-table 4, σ wherein
bBe tensile strength, σ
0.2Be regulation disproportional yield strength, δ is a unit elongation.All the other performances are referring to Fig. 1-shown in Figure 3.
Table 1 room temperature tensile performance
| Alloy | σ b(MPa) | σ 0.2(MPa) | δ(％) |
| IM?I834 | 1070 | 960 | 11 |
| Ti?1100 | 960 | 860 | 11 |
| Ti60 | 1100 | 1030 | 11 |
| Ti600 | 1068 | 1050 | 11 |
| TP?650 | 1330 | 1280 | 5~8 |
| This alloy | 1100 | 1060 | 11 |
Table 2 high temperature tensile properties
Table 3 creep, enduring quality
Table 4 thermal stability
Embodiment 2
Take by weighing one-level titanium sponge (85.05%), LaB by mass percentage
4(mass percent 76% of La) compound (0.65%), AlNb (mass percent 40% of Nb) master alloy powder (1.25%), aluminium powder (2.35%), AlMo (mass percent 40% of Mo) master alloy powder (1.5%), TiSn (mass percent 50% of Sn) master alloy powder (6%), zirconium sponge (3%), silicon metal (0.2%), preparation quality per-cent are the composite heat-resisting enhance titanium alloy of Al 4%-Sn 3%-Zr 3%-Mo 0.6%-Nb 0.5%-Si 0.2%-La 0.4%-B 0.15%.According to embodiment 1 identical three melting technologies and heat processing technique, obtain the bar that to heat-treat.The thermal treatment process of adopt recommending: 1100 ℃, 1 hour, solution treatment+650 of air cooling ℃, 2 hours, the ageing treatment of air cooling, the over-all properties of the heat-resistant titanium alloy that makes is close with embodiment 1, temperature-room type plasticity and thermostability are good slightly, and intensity and durable creeping performance are poor slightly.
Embodiment 3
Take by weighing one-level titanium sponge (77.35%), LaB by mass percentage
6(mass percent 67% of La) compound (1.3%), AlNb (mass percent 65% of Nb) master alloy powder (1.5%), aluminium powder (5.7%), AlMo (mass percent 65% of Mo) master alloy powder (2.3%), TiSn (mass percent 80% of Sn) master alloy powder (6.25%), zirconium sponge (5%), silicon metal (0.6%), preparation quality per-cent are the composite heat-resisting enhance titanium alloy of Al 7%-Sn 5%-Zr 5%-Mo 1.5%-Nb 1%-Si 0.6%-La 0.9%-B 0.4%.According to embodiment 1 identical three melting technologies and heat processing technique, obtain the bar that to heat-treat.The thermal treatment process of adopt recommending: 1100 ℃, 1 hour, solution treatment+650 of air cooling ℃, 2 hours, the ageing treatment of air cooling, the over-all properties of the heat-resistant titanium alloy that makes is close with embodiment 1, intensity and durable creeping performance are good slightly, and temperature-room type plasticity and thermostability are poor slightly.
Embodiment 4
Take by weighing one-level titanium sponge (92.5%), LaB by mass percentage
4(mass percent 76% of La) compound (0.4%), AlNb (mass percent 40% of Nb) master alloy powder (1.25%), aluminium powder (1.5%), AlMo (mass percent 40% of Mo) master alloy powder (1.25%), TiSn (mass percent 50% of Sn) master alloy powder (2%), zirconium sponge (1%), silicon metal (0.1%), preparation quality per-cent are the composite heat-resisting enhance titanium alloy of Al 3%-Sn 1%-Zr 1%-Mo 0.5%-Nb 0.5%-Si 0.1%-La 0.3%-B 0.1%.According to embodiment 1 identical three melting technologies and heat processing technique, obtain the bar that to heat-treat.This material wild phase content and alloying element content are relatively low, transformation temperature is also lower, adopt following thermal treatment process: 1050 ℃, 1 hour, solution treatment+650 of air cooling ℃, 2 hours, the ageing treatment of air cooling, the heat-resistant titanium alloy wild phase that makes is very tiny and be evenly distributed, have more excellent temperature-room type plasticity and thermostability, but the time of proper extension ageing treatment is to improve its intensity and creep-resistant property.
Embodiment 5
Take by weighing one-level titanium sponge (72.7%), LaB by mass percentage
6(mass percent 67% of La) compound (1.5%), AlNb (mass percent 65% of Nb) master alloy powder (2.3%), aluminium powder (6.1%), AlMo (mass percent 65% of Mo) master alloy powder (3.1%), TiSn (mass percent 80% of Sn) master alloy powder (7.5%), zirconium sponge (6%), silicon metal (0.8%), preparation quality per-cent are the composite heat-resisting enhance titanium alloy of Al 8%-Sn 6%-Zr 6%-Mo 2%-Nb 1.5%-Si 0.8%-La 1%-B 0.5%.According to embodiment 1 identical three melting technologies and heat processing technique, obtain the bar that to heat-treat.This material wild phase content is relative with alloying element content higher, transformation temperature is also higher, adopt following thermal treatment process: 1125 ℃, 1 hour, solution treatment+600 of air cooling ℃, 1 hour, the ageing treatment of air cooling, the heat-resistant titanium alloy wild phase that makes is evenly distributed, room temperature strength is significantly improved, and creep-resistant property is preferably arranged.Answer the time of strict control ageing treatment, avoid the deterioration of temperature-room type plasticity and thermostability.
Claims (9)
1. a composite heat-resisting enhance titanium alloy is characterized in that, each component weight percent content is: Al3%-8%; Sn 1%-6%; Zr 1%-6%; Mo 0.5%-2%; Nb 0.5%-1.5%; Si 0.1%-0.8%; La 0.3%-1%; B 0.1%-0.5%; Ti is a surplus;
The heat resisting temperature scope of this composite heat-resisting enhance titanium alloy is 650-700 ℃.
2. composite heat-resisting enhance titanium alloy as claimed in claim 1 is characterized in that, described Al, and its weight percent content is: 4%-7%.
3. composite heat-resisting enhance titanium alloy as claimed in claim 1 is characterized in that, described Sn, and its weight percent content is: 3%-5%.
4. composite heat-resisting enhance titanium alloy as claimed in claim 1 is characterized in that, described Zr, and its weight percent content is: 3%-5%.
5. composite heat-resisting enhance titanium alloy as claimed in claim 1 is characterized in that, described Mo, and its weight percent content is: 0.6%-1.5%.
6. composite heat-resisting enhance titanium alloy as claimed in claim 1 is characterized in that, described Nb, and its weight percent content is: 0.5%-1%.
7. composite heat-resisting enhance titanium alloy as claimed in claim 1 is characterized in that, described Si, and its weight percent content is: 0.3%-0.6%.
8. composite heat-resisting enhance titanium alloy as claimed in claim 1 is characterized in that, described La, and its weight percent content is: 0.4%-0.9%.
9. composite heat-resisting enhance titanium alloy as claimed in claim 1 is characterized in that, described B, and its weight percent content is: 0.15%-0.4%.
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| CN101598139B (en) * | 2008-06-04 | 2013-03-27 | 北京有色金属研究总院 | Titanium alloy integral blade disc with composite performance and fabricating method thereof |
| CN102251145B (en) * | 2011-07-04 | 2013-02-06 | 西安西工大超晶科技发展有限责任公司 | 1100 MPa level thermal strength titanium alloy and preparation method thereof |
| CN102952968A (en) * | 2011-08-23 | 2013-03-06 | 上海航天精密机械研究所 | Particle reinforced heatproof titanium alloy |
| US9957836B2 (en) * | 2012-07-19 | 2018-05-01 | Rti International Metals, Inc. | Titanium alloy having good oxidation resistance and high strength at elevated temperatures |
| CN103555999A (en) * | 2013-11-06 | 2014-02-05 | 北京科技大学 | High-strength cast Ti-Si-Al-B-Zr base alloy |
| CN104561657B (en) * | 2014-12-26 | 2017-01-18 | 上海腾辉有色铸造有限公司 | Titanium-aluminium alloy material and preparation technology thereof |
| CN104726730B (en) * | 2015-02-09 | 2017-03-15 | 上海交通大学 | One kind prepares layer structure Ti (TiB+La2O3The method of)/Ti composites |
| CN105838922B (en) * | 2016-05-25 | 2017-12-29 | 西部超导材料科技股份有限公司 | A kind of aviation thermal strength titanium alloy ingot casting and preparation method thereof |
| CN105950911A (en) * | 2016-06-27 | 2016-09-21 | 西北有色金属研究院 | Multi-element solid solution strengthening heat-resistant titanium alloy |
| CN106756237B (en) * | 2017-01-10 | 2019-02-05 | 沈阳泰恒通用技术有限公司 | A kind of abrasion-resistant titanium basic composite material |
| CN108774702A (en) * | 2018-06-22 | 2018-11-09 | 广西趣创想创客空间管理有限责任公司 | A kind of high temperature oxidation resisting titanium alloy and preparation method thereof |
| CN110643852A (en) * | 2019-10-22 | 2020-01-03 | 白福林 | High-strength and high-toughness titanium alloy and preparation method thereof |
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2007
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