CN1772932A - High temperature Titanium alloy with high creepage resistance and high fatigue strength - Google Patents
High temperature Titanium alloy with high creepage resistance and high fatigue strength Download PDFInfo
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- CN1772932A CN1772932A CN 200510068116 CN200510068116A CN1772932A CN 1772932 A CN1772932 A CN 1772932A CN 200510068116 CN200510068116 CN 200510068116 CN 200510068116 A CN200510068116 A CN 200510068116A CN 1772932 A CN1772932 A CN 1772932A
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Abstract
The present invention is one kind of high temperature titanium alloy with high creepage resistance and high fatigue strength for air compressor in engine. The alloy consists of Al 3.0-7.0 wt%, Sn 1.0-6.0 wt%, Zr 1.0-6.0 wt%, Nb 0.1-2.5 wt%, Ta 0.2-4.0 wt%, Mo 0.0-3.0, Si 0.05-0.7 wt% and C 0.0-0.1 wt% except Ti. The alloy has excellent creepage resistance at 600 deg.c, high fatigue strength and fracture toughness, low fatigue crack expanding rate and excellent comprehensive performance, and is ideal material for air compressor parts in aviation engine operating at 600 deg.c.
Description
Affiliated technical field
The present invention is a kind of high creep resistance of the crucial rotatable parts that are used for aero-engine compressor and the high-temperature titanium alloy of high-fatigue strength, and this kind material can be at 600 ℃ of following life-time service, and have high creep resistance and high-fatigue strength.Belong to the metallic substance technical field.
Background technology
Titanium alloy has obtained application more and more widely with its superior high specific strength, characteristics such as corrosion-resistant on aircraft engine and aircraft.Along with the raising of aircraft engine thrust-weight ratio or power to weight ratio, engine is also being improved constantly with the titanium alloy performance demands.
Since the 1950's, the titanium alloy fast-developing road of having passed by, the use temperature of titanium alloy is that 400 ℃ of representative have brought up to Ti-6Al-4V is 600 ℃ of representative with IMI834.The high temperatures typical titanium alloy of Britain's development has: IMI679 (maximum operation (service) temperature: 450 ℃), IMI685 (520 ℃), IMI829 (540 ℃), IMI834 (600 ℃); The high-temperature titanium alloy of the U.S. has: Ti-6242S (540 ℃), Ti-1100 (600 ℃); Muscovite high-temperature titanium alloy has: BT3-1 (450 ℃), BT8 (500 ℃), BT9 (500 ℃), BT25 (550 ℃), BT25y (550 ℃), BT18y (600 ℃), BT36 (600 ℃); What the early stage high-temperature titanium alloy of China was mainly walked is the road of copying, beginning development voluntarily after the eighties in 20th century, and the typical high temperature titanium alloy has: TC4 (400 ℃), TC11 (500 ℃), TA12 (550 ℃).
At present, come into operation and the high-temperature titanium alloy developed mostly is nearly α type alloy greatly in various countries.Nearly alpha titanium alloy has good high-temperature performance, structure stability and welding property, is suitable for using under hot environment.In the world the IMI834 (Ti-5.8Al-4Sn-3.5Zr-0.7Nb-0.5Mo-0.35Si-0.06C) of Britain, the Ti-1100 (Ti-6Al-2.75Sn-4Zr-0.4Mo-0.45Si) of the U.S., Muscovite BT36 (Ti-6.2Al-2Sn-3.6Zr-0.7Mo-5.0W-0.15Si) can be arranged at the high-temperature titanium alloy of 600 ℃ of life-time service, they all are to develop on the basis of Ti-Al-Sn-Zr-Mo-Si system, but chemical ingredients differs from one another again.The IMI834 alloy has added 2 β stabilizing element Mo and Nb, and 0.06%C; The Mo content of Ti-1100 alloy is lower, and Si is higher relatively, and is very tight to impurity element Fe and 0 content requirement; The BT36 alloy contains the rare earth element y of 5% high-melting-point element W and trace.
China's development high-temperature titanium alloy is paid much attention to the effect of rare earth element, as China's patent 87105074 " a kind of heat-resistant titanium alloy ", it is characterized in that adopting rear earth element nd (Nd) to make titanium alloy strengthen and improve the oxidation-resistance of titanium alloy surface.The composition range of alloy and weight percent are: Al 2.5～7%, Sn 2～11%, Zr 0.5～5%, Mo 0.2～2%, Si 0.08～0.5%, Nd 0.2～2.5%, Ti surplus.Its optimal components scope is Al 5.5～6.5%, Sn 3～6%, Zr 1～3%, Mo 0.5～1.5%, Si 0.1～0.3%, Nd 0.5～1.5%, Ti surplus.The alloy of this patent has over-all propertieies such as good tensile strength, creep strength and thermostability at 550 ℃.
At the demand background of the advanced aircraft engine of China, the proposition needs are a kind of can be at the titanium alloy of 600 ℃ of following life-time service.The domestic high-temperature titanium alloy of having grasped can not satisfy the requirement of use properties at present.
Summary of the invention
The objective of the invention is to develop novel high-temperature titanium alloy with high creep resistance and high-fatigue strength, and can be at 600 ℃ of life-time service.
The technical problem that technical solution of the present invention at first will solve is a new alloy composition Design problem, when this new alloy of design, need take into full account it and use the requirement of parts to material mechanical performance and life-time service reliability aspect.With domestic and international close alloy phase ratio, creep resistance and fatigue strength that alloying element Ta has improved alloy have been it is characterized in that adding.Kind and the optimization of the content raising that realize over-all properties of the new alloy of design by beta stable element.The chemical ingredients of this alloy and weight percent are: Al 3.0～7.0, and Sn 1.0～6.0, and Zr 1.0～6.0, and Nb 0.1～2.5, and Ta 0.2～4.0, and Mo 0.0～3.0, and Si 0.05～0.7, and C 0.0～0.1, and surplus is Ti.Alloying constituent involved in the present invention is with the difference of domestic and international other close titanium alloys: what 1. this alloy adopted is Ti-Al-Sn-Zr-Nb-Ta-Si-C alloying system, is main β stabilizing element with Ta, Nb and Mo; 2. the combination of the content of these two neutral elements of Sn and Zr other any titanium alloys different from the past; 3. the combinative stability β of Ta and Nb element is an innovation greatly of high-temperature titanium alloy development mutually.
Description of drawings
Fig. 1 is the room temperature fatigue crack growth rate of TG6-2 alloy diskware among the embodiment two
Embodiment
Example 1:
The chemical ingredients of this alloy and weight percent are: 5.80%Al, 4.0%Sn, 3.46%Zr, 0.68%Nb, 1.86%Ta, 0.39%Si, 0.068%C, 0.03%Fe, 0.066%0,0.008%N, surplus is Ti.
Starting material adopt 0 grade of titanium sponge, pure Al bits, pure Sn, zirconium sponge, Ta powder, Al-Nb master alloy, Al-Si master alloy, C powder, by being pressed into electrode after the alloy name chemical ingredients proportioning, the electrode that every segment electrode is welded into a whole before the melting, the heavy 54kg of overall electrode.On vacuum consumable electrode arc furnace, carry out the VAR melting, made diameter and be one on the 50kg ingot casting of 220mm, temporarily called after TG6-1.
The cogging of ingot casting divides two fire to carry out on 1250 t hydraulic press.Making bar that diameter is 18.5mm on the precise forging machine and on the milling train and through 1. β district solid solution+timeliness, 2. near β district solid solution+timeliness, 3. alpha+beta district solid solution+timeliness thermal treatment.Its every performance sees Table shown in the one～table four.
The room temperature tensile performance of table 1 TG6-1 alloy bar material
| Numbering | Tensile strength MPa | Yield strength MPa | Unit elongation % | Relative reduction in area % | Heat treating regime |
| 1 | 996 | 913 | 7.0 | 15.5 | ① |
| 2 | 1006 | 911 | 13.6 | 32.3 | ② |
| 3 | 999 | 928 | 14.2 | 24.3 | ③ |
600 ℃ of tensile properties of table 2 TG6-1 alloy bar material
| Numbering | Tensile strength MPa | Yield strength MPa | Unit elongation % | Relative reduction in area % | Heat treating regime |
| 4 | 602 | 506 | 12.8 | 27.5 | ① |
| 5 | 625 | 509 | 23.2 | 46.2 | ② |
| 6 | 608 | 494 | 30.6 | 51.3 | ③ |
The room temperature tensile performance (sample thermostability) of table 3 TG6-1 alloy bar material after 600 ℃/100h sample heat exposes
| Numbering | Tensile strength MPa | Unit elongation % | Relative reduction in area % | Heat treating regime |
| 7 | 952 | 1.6 | 5.5 | ① |
| 8 | 1063 | 5.4 | 6.1 | ② |
| 9 | 1.54 | 6.1 | 6.7 | ③ |
600 ℃ of creep properties of table 4 TG6-1 alloy bar material (600 ℃/150MPa/100h)
| Numbering | Breaking elongation % | Elastic extension rate % | Remaining unit elongation % | |
| 10 | 0.227 | 0.154 | 0.073 | ① |
| 11 | 0.254 | 0.181 | 0.073 | |
| 12 | 0.215 | 0.169 | 0.046 | |
| 13 | 0.457 | 0.173 | 0.284 | ② |
| 14 | 0.474 | 0.167 | 0.307 | |
| 15 | 0.412 | 0.194 | 0.218 |
Example 2:
The chemical ingredients of this alloy and weight percent are: 5.40%Al, 4.06%Sn, 3.96%Zr, 0.68%Nb, 1.41%Ta, 0.37%Si, 0.056%C, surplus is Ti.
Starting material adopt 0 grade of titanium sponge, pure Al bits, pure Sn, zirconium sponge, Ta powder, Al-Nb master alloy, Al-Si master alloy, C powder, by being pressed into electrode after the alloy name chemical ingredients proportioning, the heavy 256kg of batching.On the 650kg vacuum consumable electrode arc furnace, carry out three VAR meltings, made diameter and be one on the 256kg ingot casting of 350mm, temporarily called after TG6-2.
The cogging of ingot casting divides two fire to carry out on 1250 t hydraulic press.On water pressure engine, adopt low height alternately forging process make the 7th grade of diskware of XX engine with cake ring base, on 10 tons of forging hammers, adopt β of the 7th grade of diskware mould of XX engine to be forged into diskware, diskware external diameter Φ 460mm, internal diameter Φ 155mm, wheel rim maximum ga(u)ge 52mm, spoke maximum ga(u)ge 34mm.Its every performance sees Table shown in the five～table ten.
The room temperature tensile performance of table 5 TG6-2 alloy diskware
| Probe temperature | σ b MPa | σ 02 MPa | δ 5 ％ | ψ ％ |
| 20℃ | 1025 | 938 | 8.4 | 17.2 |
| 992 | 900 | 7.8 | 17.2 | |
| 500℃ | 703 | 537 | 14.0 | 27.8 |
| 677 | 522 | 11.4 | 22.7 | |
| 550℃ | 640 | 491 | 10.2 | 27.8 |
| 658 | 510 | 8.8 | 25.1 |
| 600℃ | 645 | 497 | 10.2 | 18.8 |
| 642 | 496 | 10.0 | 25.8 | |
| 650℃ | 608 | 470 | 13.4 | 31.9 |
| 627 | 500 | 16.4 | 39.5 |
The thermostability of table 6 TG6-2 alloy diskware (the room temperature tensile performance after heat exposes)
| Hot exposure chamber | σ b MPa | σ 0.2 MPa | δ 5 ％ | ψ ％ |
| 600 ℃/100h sample heat exposes | 1048 | 997 | 1.8 | 4.5 |
| 1079 | 1031 | 1.8 | 3.9 | |
| 650 ℃/100h sample heat exposes | 1002 | 938 | 3.2 | 6.7 |
| 600 ℃/100h blank heat exposes | 1073 | 1000 | 7.8 | 12.2 |
| 1083 | 1009 | 6.2 | 12.0 | |
| 650 ℃/100h blank heat exposes | 1064 | 990 | 9.2 | 16.0 |
| 1035 | 957 | 7.4 | 12.2 |
The creep property of table 7 TG6-2 alloy diskware
| The creep test condition | Remaining creep compliance ε p, % |
| 600℃/150MPa/100h | 0.121 |
| 0.058 | |
| 600℃/160MPa/100h | 0.177 |
| 0.127 | |
| 650℃/100MPa/100h | 0.112 |
| 0.048 |
The enduring quality of table 8 TG6-2 alloy diskware
| The persistence testing condition | Creep rupture life t, h |
| 600℃/310MPa | 138.2 |
| 147.3 | |
| 650℃/220MPa | 100.8 |
| 111.8 | |
| Annotate: surpass 100h creep rupture life, increases stress 40MPa, increases stress 40MPa every 50h later on | |
The high cycle fatigue fatigue property of table 9 TG6-2 alloy diskware
| Testing method and condition | Intermediate value fatigue strength |
| Room temperature, rotoflector | 490MPa |
| Room temperature axially loads stress ratio: R=0.1; Stress concentration factor: K t＝1 | 655MPa |
The room temperature fracture toughness property of table 10 TG6-2 alloy diskware
High-temperature titanium alloy provided by the invention can have excellent comprehensive performance, this alloy is at the high-temperature titanium alloy with excellent comprehensive performance of 600 ℃ of life-time service, this high-temperature titanium alloy has good creep resistance at 600 ℃, also have excellent fatigue strength and fracture toughness property simultaneously, and low fatigue crack growth rate, its excellent comprehensive performances is that advanced aero-engine compressor about the 600 ℃ parts of working in position of China (as hpc blade, wheel disc and drum barrel) provide the ideal candidate material.
This alloy has tensile strength, stretching plastic, thermostability, the creep resistance of working as with alloy phases such as Britain IMI834, U.S. Ti-1100, but has higher fatigue strength, the higher fracture toughness property (K of diskware
1CApproximately higher than IMI834
) and lower fatigue crack growth rate.
Claims (2)
1. the high-temperature titanium alloy of high creep resistance and high-fatigue strength, it is characterized in that: the chemical ingredients of this alloy and weight percent are: Al 3.0～7.0, Sn 1.0～6.0, Zr 1.0～6.0, and Nb 0.1～2.5, and Ta 0.2～4.0, Mo 0.0～3.0, Si 0.05～0.7, and C 0.0～0.1, and surplus is Ti.
2. the high-temperature titanium alloy of high creep resistance according to claim 1 and high-fatigue strength, it is characterized in that: the chemical ingredients of this alloy and weight percent are: Al 5.2～6.0, Sn3.5～4.5, Zr 3.0～4.0, Nb 0.3～1.0, and Ta 0.5～2.5, and Si 0.2～0.5, C 0.03～0.08, and surplus is Ti.
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100567534C (en) * | 2007-06-19 | 2009-12-09 | 中国科学院金属研究所 | The hot-work of the high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability and heat treating method |
| CN102952968A (en) * | 2011-08-23 | 2013-03-06 | 上海航天精密机械研究所 | Particle reinforced heatproof titanium alloy |
| CN103014412A (en) * | 2011-09-27 | 2013-04-03 | 什邡市明日宇航工业股份有限公司 | Composite heat-resistant titanium alloy |
| CN103014413A (en) * | 2011-09-27 | 2013-04-03 | 什邡市明日宇航工业股份有限公司 | Composite reinforced heat-resistant titanium alloy |
| CN101967581B (en) * | 2009-07-28 | 2015-03-04 | 中国科学院金属研究所 | Titanium alloy with thin sheet layer microstructure and manufacturing method thereof |
| CN104532056A (en) * | 2014-12-08 | 2015-04-22 | 洛阳双瑞精铸钛业有限公司 | High temperature titanium alloy and preparation method thereof |
| CN104561656A (en) * | 2014-12-16 | 2015-04-29 | 中国航空工业集团公司北京航空材料研究院 | High-temperature titanium alloy |
| 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 |
| CN105445127A (en) * | 2015-11-27 | 2016-03-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Analysis method for grain size and fatigue strength relationship of titanium alloy based on additive manufacturing |
| CN105838922A (en) * | 2016-05-25 | 2016-08-10 | 西部超导材料科技股份有限公司 | Heat strong titanium alloy ingot for aviation and manufacturing method for heat strong titanium alloy |
| CN106636739A (en) * | 2016-10-31 | 2017-05-10 | 西北有色金属研究院 | Moderate-intensity and high-impact-toughness titanium alloy in ocean engineering |
| 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 |
| CN107058801A (en) * | 2017-03-09 | 2017-08-18 | 西北工业大学 | One kind is applied to 560 ~ 650 DEG C of cast titanium alloy |
| CN103572094B (en) * | 2012-07-19 | 2018-06-05 | Rti国际金属公司 | There is good oxidation resistance and the titanium alloy of high intensity at high temperature |
| CN111500959A (en) * | 2020-06-09 | 2020-08-07 | 北京工业大学 | Hot processing and heat treatment process for preparing near α type high-temperature titanium alloy layered structure |
| CN111826550A (en) * | 2020-07-27 | 2020-10-27 | 西北有色金属研究院 | Moderate-strength nitric acid corrosion resistant titanium alloy |
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2005
- 2005-04-27 CN CN 200510068116 patent/CN1772932A/en active Pending
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100567534C (en) * | 2007-06-19 | 2009-12-09 | 中国科学院金属研究所 | The hot-work of the high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability and heat treating method |
| CN101967581B (en) * | 2009-07-28 | 2015-03-04 | 中国科学院金属研究所 | Titanium alloy with thin sheet layer microstructure and manufacturing 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 |
| CN103014412A (en) * | 2011-09-27 | 2013-04-03 | 什邡市明日宇航工业股份有限公司 | Composite heat-resistant titanium alloy |
| CN103014413A (en) * | 2011-09-27 | 2013-04-03 | 什邡市明日宇航工业股份有限公司 | Composite reinforced heat-resistant titanium alloy |
| CN103572094B (en) * | 2012-07-19 | 2018-06-05 | Rti国际金属公司 | There is good oxidation resistance and the titanium alloy of high intensity at high temperature |
| CN108486409A (en) * | 2012-07-19 | 2018-09-04 | Rti国际金属公司 | Titanium alloy with good oxidation resistance and high intensity at high temperature |
| CN104532056A (en) * | 2014-12-08 | 2015-04-22 | 洛阳双瑞精铸钛业有限公司 | High temperature titanium alloy and preparation method thereof |
| CN104561656A (en) * | 2014-12-16 | 2015-04-29 | 中国航空工业集团公司北京航空材料研究院 | High-temperature titanium alloy |
| 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 |
| CN105445127A (en) * | 2015-11-27 | 2016-03-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Analysis method for grain size and fatigue strength relationship of titanium alloy based on additive manufacturing |
| CN105838922A (en) * | 2016-05-25 | 2016-08-10 | 西部超导材料科技股份有限公司 | Heat strong titanium alloy ingot for aviation and manufacturing method for heat strong titanium alloy |
| CN106636739A (en) * | 2016-10-31 | 2017-05-10 | 西北有色金属研究院 | Moderate-intensity and high-impact-toughness titanium alloy in ocean engineering |
| CN107058801A (en) * | 2017-03-09 | 2017-08-18 | 西北工业大学 | One kind is applied to 560 ~ 650 DEG C of cast titanium alloy |
| 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 |
| CN111500959A (en) * | 2020-06-09 | 2020-08-07 | 北京工业大学 | Hot processing and heat treatment process for preparing near α type high-temperature titanium alloy layered structure |
| CN111826550A (en) * | 2020-07-27 | 2020-10-27 | 西北有色金属研究院 | Moderate-strength nitric acid corrosion resistant titanium alloy |
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