CN100567534C - The hot-work of the high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability and heat treating method - Google Patents

The hot-work of the high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability and heat treating method Download PDF

Info

Publication number
CN100567534C
CN100567534C CNB2007100117710A CN200710011771A CN100567534C CN 100567534 C CN100567534 C CN 100567534C CN B2007100117710 A CNB2007100117710 A CN B2007100117710A CN 200710011771 A CN200710011771 A CN 200710011771A CN 100567534 C CN100567534 C CN 100567534C
Authority
CN
China
Prior art keywords
alloy
heat
hot
beta
work
Prior art date
Application number
CNB2007100117710A
Other languages
Chinese (zh)
Other versions
CN101104898A (en
Inventor
王清江
刘建荣
杨锐
魏寿庸
刘羽寅
陈战乾
王鼎春
高颀
Original Assignee
中国科学院金属研究所
宝钛集团有限公司
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 中国科学院金属研究所, 宝钛集团有限公司 filed Critical 中国科学院金属研究所
Priority to CNB2007100117710A priority Critical patent/CN100567534C/en
Publication of CN101104898A publication Critical patent/CN101104898A/en
Application granted granted Critical
Publication of CN100567534C publication Critical patent/CN100567534C/en

Links

Abstract

The present invention is the hot-work and the thermal treatment process of the high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability, this alloy adds Nb, Ta, three kinds of cocrystallizing type alloying elements of Mo simultaneously, suitable collocation by between these three kinds of elements has obtained than higher heat resistance, thermostability and oxidation-resistance.The composition range of alloy (by weight percentage) is: Al:5.0%~6.3%; Sn:3.0%~5.0%; Zr:2.5%~7.0%; Mo:0.2%~1.5%; Si:0.20%~0.55%; Nb:0.2%~1.0%; Ta:0.2%~3.0%; C:0.01%~0.09%, all the other are titanium and unavoidable impurities element.This alloy is the desirable alternative materials of aircraft engine high-temperature component such as wheel disc, drum barrel and drum barrel axle, blade etc.

Description

The hot-work of the high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability and heat treating method

Technical field

The invention belongs to the hot-work and the heat treated technical field of titanium base alloy, be specifically related to a kind of main for 600 ℃ or 600 ℃ of following temperature life-time service on the aircraft engine and can be for the hot-work and the heat treating method of the titanium base alloy of use in short-term under the temperature condition more than 600 ℃ or 600 ℃ of other spacecrafts.

Background technology

Aircraft engine is the design requirements of satisfying loss of weight and improving thrust-weight ratio, needs the higher titanium alloy material of specific tenacity that utilizes as much as possible.The usage quantity of titanium alloy is the trend that significantly increases on the domestic and international in recent years especially advanced military aircraft of aircraft.We can say that titanium alloy usage quantity and usage level have become an important indicator weighing domestic and international aeronautical technology and the advanced degree of aeroplane performance.

But titanium alloy runs into very big obstruction in the development course that improves use temperature, and major cause is that the contradiction between alloy heat resistance and the thermostability is more and more outstanding along with the raising of design use temperature.Here said heat resistance refers to the comprehensive of alloy high-temp intensity, lasting and creep property, and thermostability is meant that alloy is incubated the hold facility of alloy temperature-room type plasticity behind the specified time under specified temp.At present, the titanium alloy that developed country's use temperature is the highest, its trade mark has the IMI834 of Britain, the Ti-1100 of the U.S. and Muscovite BT36, the long-time use temperature of these three kinds of alloy designs all is or near 600 ℃, wherein with the over-all properties optimum of IMI834 alloy.It is reported that the IMI834 alloy has been used for tumblers such as aircraft engine blisk, Ti-1100 also enters the application stage, and BT36 does not then see as yet relevant report.What table 1 provided is the nominal composition of external these three kinds of 600 ℃ of high-temperature titanium alloys.

The 600 ℃ of high-temperature titanium alloy nominal compositions in table 1 countries in the world

By table 1 as seen, all contain Al, Sn, Zr, Mo, five kinds of elements of Si in 600 ℃ of high-temperature titanium alloys of countries in the world at present, and weight percent is also more approaching, they are principal elements of strengthening 600 ℃ of high-temperature titanium alloys; Difference is other the having or not and what of add-on of Elements C, Nb, Ta, W.Along with the China's national defense development of modernization, advanced aircraft engine to the requirement of 600 ℃ of high-temperature titanium alloys is: be not less than in other performances under the prerequisite of IMI834 alloy, make these two conflicting performance index of heat resistance and thermostability have matched well, and do not have the index request of thermostability in the technical indicator of IMI834 alloy and Ti-1100 alloy originally; Domestic IMI834 alloy according to the refining of the composition in the IMI834 alloy technology standard, survey its thermostability and heat resistance and do not reach the technical requirement of domestic air mail engine design unit 600 ℃ of high-temperature titanium alloys, therefore, in order to develop the aerospace cause of China, we must develop voluntarily can be 600.The more good titanium base alloy of life-time service and integrated performance index under the C.

Summary of the invention

Purpose of the present invention be exactly to seek a kind of main for aircraft engine 600 ℃ of following life-time service, have the hot-work and a heat treating method of the titanium base alloy of high heat-intensity, high thermal stability preferably.

The high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability, this alloy comprise the titanium and the unavoidable impurities element of Al, Sn, Zr, Mo, five kinds of elements of Si and surplus, in alloy:

(1) Mo, Nb, three kinds of beta stable elements of Ta have been added simultaneously;

(2) content of strong α stable element Al of control and strong beta stable element Mo;

(3) with Fe, Cr, Mn, Cu, V, Co, seven kinds of beta stable element overall controls of Ni below 0.20wt-%;

(4) content of control gap element O, N, H.

Above-mentioned high-temperature titanium alloy, its composition range (calculating with wt-%) is: Al:5.0%~6.3%; Sn:3.0%~5.0%; Zr:2.5%~7.0%; Mo:0.2%~1.5%; Si:0.20%~0.55%; Nb:0.2%~1.0%; Ta:0.2%~3.0%; C:0.01%~0.09%, Fe, Cr, Mn, Cu, V, Co, Ni total amount≤0.20%; O≤0.14%; N≤0.02%; H≤0.01%; Surplus is Ti and other unavoidable impurities element.

As if we notice: investigator has in the past also recognized the effect that Mo, Nb, three kinds of elements of Ta can play in titanium alloy; Yet in they disclosed embodiment, but seldom see these three kinds of elements are joined in the titanium alloy simultaneously (often just add wherein one or both), and also there is multiple conflicting saying in the control of its total amount, this illustrates that they do not do more deep research to this problem.In titanium alloy, add Mo, Nb, three kinds of isomorphism β of Ta phase stable element simultaneously.β phase stable element adds total amount increases, and has overcome the technical barrier that 600 ℃ of high-temperature titanium alloy heat resistances and thermostability are difficult to coordinate, and has also taken into account the oxidation-resistance of alloy simultaneously.Its heat resistance is embodied by creep residual set amount under duration and the 600 ℃/160MPa/100h creep condition under 600 ℃ of tensile strengths, the 600 ℃/310MPa condition; And thermostability is embodied by the reduction degree that sample (band oxide skin) or blank heat expose before (not with oxide skin) back alloy room temperature tensile plasticity exposes with respect to heat, and hot exposure condition is 600 ℃/atmospheric condition/100h.Test result shows that above-mentioned two performance index of alloy have all reached designing unit to the technical requirements of aircraft engine with 600 ℃ of high-temperature titanium alloys.

The present invention proposes the optimal components and the weight percent of above-mentioned high-temperature titanium alloy, they are: Al5.37%~6.02%; Sn 3.77%~4.03%; Zr 3.32%~3.42%; Mo 0.38~0.70%; Si0.34%~0.42%; Nb 0.37%~0.41%; Ta 0.36%~0.99%; C 0.038%~0.056%; Fe≤0.07%; O≤0.14%; Surplus is Ti and other unavoidable impurities element.

Titan alloy casting ingot can be produced in the following way in the composition range of the present invention: starting material adopt 0 grade of titanium sponge, and alloying element adds with the form of pure metal or master alloy.Pure metal and/or master alloy and titanium sponge are pressed into small electrode with press behind batching, batch mixing.With some small electrode assembly weldings together, put into the consumable electrode vacuum furnace melting 3 times, make alloy cast ingot.Ingot casting is after excising the cap mouth, removing surface scale, and 1200 ℃ of left and right sides coggings, blanking along its length after the cogging enters next step hot procedure.

After having determined the composition of alloy, hot-work worker technology and heat treating regime are also very important, and it has determined the microstructure of alloy and has had influence on performance index.The present invention proposes and be used to make corresponding hot-work of above-mentioned titanium alloy member and heat treating method:

1. carry out hot-work and thermal treatment by following technology, this technology is particularly suitable for the processing of diskware (cake ring base):

(1) water pressure engine processing is adopted in following 10 ℃~40 ℃ electric furnaces heating of alpha+beta/beta transformation point, and ratio of forging reduction is controlled between 1.5~3.0, forges the back shrend;

(2) water pressure engine processing is adopted in 10 ℃~50 ℃ electric furnace heating on alpha+beta/beta transformation point, and ratio of forging reduction is controlled at more than 1.5, forges the back air cooling;

(3) many fire time jumping-ups, pulling technology are adopted in following 10 ℃~50 ℃ electric furnaces heating of alpha+beta/beta transformation point, control Dan Huoci ratio of forging reduction 〉=3.0, and the back air cooling is forged in total ratio of forging reduction 〉=6.0;

(4) following 20 ℃~50 ℃ electric furnaces heating of alpha+beta/beta transformation point, punching, reaming, ratio of forging reduction 〉=2.0, finished product shrend;

(5) heat treating regime is: alpha+beta/beta transformation point-(10 ℃~40 ℃)/(1~4h) solid solution, air cooling+(630 ℃~750 ℃)/(and 1~10h), air cooling.

2. carry out hot-work and thermal treatment by following technology, this technology is particularly suitable for the processing of bar or square billet:

(1) 20 ℃~120 ℃ electric furnace heating on alpha+beta/beta transformation point, the water pressure engine pulling, ratio of forging reduction>3.0 can adopt many fire to forge, until forging excellent size between Φ 80~Φ 140mm;

(2) alpha+beta/beta transformation point-(20 ℃~60 ℃) electric furnace heating adopts precise forging machine to divide 2~3 fire time finish forges to final size, last fiery ratio of forging reduction 〉=3.0, fiery ratio of forging reduction second from the bottom 〉=1.5; Or alpha+beta/beta transformation point-(20 ℃~50 ℃) electric furnace heating, adopt precise forging machine to divide 1~3 fire time finish forge to a certain intermediate sizes (1) step gained finish forge rod, the back rolls into rod with the finish forge rod of intermediate sizes with milling train under alpha+beta/beta transformation point-(30 ℃~60 ℃) heating condition, last heating once and rolling time deflection 〉=65%;

(3) heat treating regime is: alpha+beta/beta transformation point-(20 ℃~60 ℃)/(1~4h) solid solution, air cooling+(630 ℃~750 ℃)/(and 1~10h), air cooling.

The present invention comes down to a kind of optionally invention, the contriver through of the influence of further investigation alloying element to the heat resistance of titanium base alloy and thermostability after, drawn for the new selection of alloy adding.Consequently, found at 600 ℃ of following life-time service and had excellent heat stability and the titanium alloy of heat resistance integrated performance index, obtained bigger technical progress.

Be how to select the composition of alloy and definite hot-work, heat-treatment protocol to be further described to the present invention more below, all elemental compositions are all counted by weight percentage.

After the present invention carries out analysis-by-synthesis to Al, Mo, the Nb mechanism of action in titanium alloy, having made following consideration: Al is the indispensable alloy element of high-temperature titanium alloy, be strong α phase stable element, hot strength, creep and the enduring quality of alloy had obvious effect.For satisfying the high heat-intensity requirement, the following of Al is limited to 5.0% among the present invention.But the aluminium add-on can be impelled fragility Ti too much 3The disperse of Al phase is separated out, cause alloy plasticity especially thermostability obviously descend.For taking into account thermostability, the upper limit of Al should be decided to be 6.3%.

Secondly, consider that Mo is strong β phase stable element, add the tensile strength that a certain amount of Mo can obviously improve titanium alloy in the high-temperature titanium alloy, can guarantee a certain amount of β phase simultaneously, this is beneficial to the obdurability that improves alloy.But the Mo too high levels can reduce alloy at room temperature plasticity and creep strength significantly.Fig. 1 (a) is that the Mo content that draws in experiment of contriver is to titanium alloy room temperature tensile strength R m, unit elongation A and relative reduction in area Z influence curve, Fig. 1 (b) then be Mo content to 100h under 600 ℃/160MPa of the titanium alloy condition after the influence curve of creep residual elongation amount.As seen, Mo content is increased to 1.5% when above in the titanium alloy, and alloy at room temperature plasticity and creep resistance are significantly reduced, so Mo content just is controlled between 0.2%~1.5% among the present invention.

Nb then is a kind of weak β phase stable element, and Nb is obvious to the oxidation-resistance effect that improves alloy.But this element add-on then can reduce the creep strength of alloy too much.Fig. 2 be our Nb content of in experiment, drawing to 100h under 600 ℃/160MPa of the titanium alloy condition after the influence curve of creep residual elongation amount.This shows that when Nb content is increased to 0.4% when above, the alloy creep drag begins to reduce, the present invention determines its composition range between 0.2%~1.0%.

Ta equally also is a kind of weak β phase stable element, and Ta than more bigger in the solid solubility of α in mutually, can strengthen α and β mutually in the solid solubility of β in mutually simultaneously, and is favourable to the intensity that improves alloy.Ta one limited to the alloy draw in than the scope of broad, see Fig. 3.But after Ta content increased, alloy unit surface gain in weight under oxidizing atmosphere reduced, and this illustrates that it is to improving the obvious (see figure 4) of alloy antioxidant property effect.Therefore its composition range determines to be good between 0.2%~3.0%, promptly requires can improve the alloy oxidation-resistance when not reducing the alloy creep drag.

Experimental result shows: add Mo, Nb simultaneously, three kinds of alloying elements of Ta also can be under the prerequisite of not damaging the titanium alloy heat resistance, increased β phase stable element content, help the improvement of alloy prior plasticity, the tearing tendency of alloy in hot procedure be can reduce, the suitability for industrialized production and the application of alloy helped.

C is a α phase stable element, and the adding of C can obviously improve the alpha+beta/β phase transition temperature of titanium alloy, widens the alpha+beta two-phase region, slows down the pace of change of primary phase amount with solid solubility temperature, to control primary phase amount, to enlarge the heat processing technique window favourable.But C content increases the alloy thermostability is had adverse influence, so C content should be controlled between 0.01%~0.09%.

Interstitial element O is a α stable element mutually with N, can increase alloy strength though surpass certain limit, can reduce its thermostability and toughness, therefore should in addition strict control.O among the present invention≤0.14%, N≤0.02%.Interstitial element H is a β eutectoid element, can reduce creep resistance and plasticity, improves intensity, H among the present invention≤0.01%.

Fe, Cr, Mn, Cu, Co, V, seven kinds of beta stable elements of Ni can obviously reduce creep strength, therefore also should strictly control, require Fe≤0.08% among the present invention, V≤0.06%, other constituent content all requires less than 0.03%, comprises that these impurity element total amounts of Fe are no more than 0.20%.

From the angle of control titanium alloy weave construction, obtaining tiny, uniform high-low time tissue is one of precondition that guarantees alloy high thermal stability in the composition range of the present invention.The above heating of alpha+beta/beta transformation point can make the thick grain boundary that produces in the cogging postcooling process disappear mutually, and β crystal grain thick in the deformation process obtains fragmentation, helps improving the alloy structure homogeneity.Larger-size forging such as cake ring base forging temperature are chosen on alpha+beta/beta transformation point 10 ℃~50 ℃ among the present invention.Bar is owing to rapid heat dissipation, reason such as easy to crack, and Heating temperature is chosen on the transformation temperature 20 ℃~80 ℃.Consider from the blank homogeneity of structure that equally every fire time ratio of forging reduction should not be too low, is controlled between 1.5~4.0 for cake ring material ratio of forging reduction, bar then is controlled at more than 2.0.

The inferior distortion of several fire all is chosen in the two-phase region heating after the hot-work of β phase region, with further raising material structure homogeneity, crystal grain thinning, and the primary phase of acquisition sufficient amount.Alpha+beta phase region texturing temperature is chosen in following 10 ℃~50 ℃ of alpha+beta/beta transformation point among the present invention, and requires Dan Huoci deflection 〉=30% or ratio of forging reduction 〉=1.5, and last fire time deflection>65% of bar is to obtain high thermal stability.

Alloy heat treating regime in the composition range of the present invention has adopted solution treatment+ageing treatment.The main purpose of solution treatment is that the quantity and the β of control primary phase changes tissue topography to take into account alloy thermostability and heat resistance.Solid solution temperature is chosen between following 10 ℃~50 ℃ of the transformation temperature, and corresponding primary phase volume fraction is controlled between 10%~40%.Timeliness can promote α after the solid solution 2Separating out of phase and silicide helps improving the alloy heat resistance.Aging temp is chosen between 630 ℃~750 ℃.

Description of drawings

Fig. 1 (a) and (b) be respectively of the influence of Mo content to titanium alloy room temperature tensile performance of the present invention and creep elongation amount;

Fig. 2 is the influence of Nb content to titanium alloy creep elongation amount of the present invention;

Fig. 3 is the influence of Ta content to titanium alloy creep elongation amount of the present invention;

Fig. 4 (a) and (b) be respectively 700 ℃ with 800 ℃ of oxidation weight gain curves of different Ta content titanium alloys of the present invention down.

Embodiment

Below in conjunction with accompanying drawing titanium alloy of the present invention is further described and replenishes.

During titanium alloy melting of the present invention, the titanium starting material adopt 0 grade of titanium sponge, and alloy element is except that Al and Zr add with the form of pure metal, and other forms with master alloy add.Behind the designed component prescription batching of the present invention, batch mixing,, be pressed into the electrode of different size according to the ingot shape difference.These electrodes are welded together, adopt consumable electrode vacuum furnace melting 3 times, make 6 different alloy cast ingots, carry out hot-work and thermal treatment according to different requirements again.Finally make bar or dish material, carry out every performance test.List some main embodiment example certificates below.Because the program of configuration, electrode die mould and the vacuum melting of raw material is mostly identical, repeated description no longer one by one just in each embodiment.

At first investigate and in titanium alloy, add the influence of Mo, Nb, three kinds of beta stable elements of Ta simultaneously alloy heat resistance, thermostability and antioxidant property, the fixing wherein content of two kinds of elements, regulate the add-on of the third element, the beta alloy performance index are corresponding simultaneously changes to determine its rule.These will be introduced in embodiment 1~3.That's about the size of it for the investigation of other element in the alloy, compiles the width of cloth for saving, and just narrated no longer one by one.At last, determine the optimum formula of alloy on this basis, to 600 ℃ of high-temperature titanium alloy performance demands, systematically detect its every important performance index during by the aircraft engine design.

Embodiment 1

Press following prescription: Al 5.3wt-%; Sn 5.0wt-%; Zr 7.0wt-%; Si 0.55wt-%; Nb 0.4wt-%; Ta 3.0wt-%; The Ti of C 0.09wt-% and surplus is pressed into electrode after with titanium sponge, fine aluminium, zirconium sponge and master alloy batch mixing, and wherein the add-on of Mo is respectively (wt-%): 0.4; 1.0; 2.0; 3.0, the electrode of above-mentioned four heterogeneities is respectively charged into carries out vacuum melting in the vaccum consumable electrode electric arc furnace.Obtain the ingot casting of four heterogeneities, carry out hot-work and thermal treatment by following processing condition again: make the finish forge rod of Φ 45 under 40 ℃ of heating conditions under 1150 ℃ of coggings, the alpha+beta/beta transformation point with precise forging machine, reheat to 1000 ℃ rolls into the rod that rolls of Φ 21.5 with milling train.Heat treating regime is the following 30 ℃/2h of alpha+beta/beta transformation point solid solution, air cooling, 700 ℃/2h timeliness.Four groups of samples of thermal treatment post-treatment are tested the creep elongation amount behind the 100h under its room temperature tensile performance, the 600 ℃/160MPa condition respectively, draw the curve shown in Fig. 1 (a) and (b).As can be seen from Fig. 1, Mo content is increased to 1.5wt-% when above in the titanium alloy, and alloy at room temperature plasticity and creep resistance can significantly decrease.

Embodiment 2

Press following prescription: Al 6.1wt-%; Sn 3.0wt-%; Zr 2.5wt-%; Mo 0.2wt-%; Si 0.25wt-%; Ta 0.3wt-%; The Ti of C 0.01wt-% and surplus, with the form of titanium sponge and master alloy mix the die mould side of making, back bar, assembly welding becomes electrode, wherein the add-on of Nb is respectively (wt-%): 0.2; 0.4; 0.7; 1.0.The electrode of above-mentioned four heterogeneities is respectively charged in the vaccum consumable electrode electric arc furnace melting 3 times, is smelted into the ingot casting of four different N b compositions.Carry out hot-work and thermal treatment by the processing condition of embodiment 1 again.Make four groups of samples at last and test its creep elongation amount after under the 600 ℃/160MPa 100 hours respectively, draw the curve that shows as Fig. 2.As seen from Figure 2, in the titanium alloy Nb content be increased to 0.4wt-% when above the creep resistance of alloy begin to reduce.

Embodiment 3

Press following prescription: Al 5.8wt-%; Sn 4.0wt-%; Zr 3.5wt-%; Mo 0.4wt-%; Si 0.35wt-%; Nb 0.4wt-%; C 0.05wt-%, wherein the add-on of Ta is respectively (wt-%): 0; 0.4; 1.0; 1.5; 2.0; 2.5 surplus is titanium and unavoidable impurities.With technology melting, processing and the thermal treatment of embodiment 1, to make six groups of samples at last and carry out creep test as embodiment 2, it the results are shown among Fig. 3; Measure the time dependent curve of increasing weight of oxidation in 200 hours with the above-mentioned sample of respectively organizing down at 700 ℃ and 800 ℃ again, its result then is shown in respectively in Fig. 4 (a) and (b).As can be seen from Fig. 3 Ta one limited to alloy creep resistance influence in than the scope of broad, but in Fig. 4, reflect it clearly to the effect that improves the alloy antioxidant property.

Embodiment 4~9

The one-tenth of embodiment 4~9 is respectively in the table 2.Press I in the table 2~VI and become composition alloyage electrode in the subfield, carry out vacuum consumable smelting.After alloy melting is made ingot casting, ingot casting is excised the cap mouth, removes surface scale, 1200 ℃ of left and right sides coggings, after this in the water pressure engine hot-work of β phase region, Heating temperature and ratio of forging reduction FR see Table 3 the 3rd row.β phase region distortion is finished Heating temperature that the back provides by table 3 the 4th row and ratio of forging reduction in the hot-work of alpha+beta two-phase region, and diameter can adopt precise forging machine directly to finish at the bar of Φ more than 30, and the bar of Φ below 30 then needs to adopt finish forge+roll excellent mode to finish.Table 3 composition is that the bar final specification of I~III is Φ 21.5, has adopted finish forge+roll excellent technology, rolls excellent Heating temperature and deflection and sees Table 3 the 5th row; Composition is that the bar final specification of IV~VI is Φ 32.5, has adopted forging.Roll rod and the finish forge rod of Φ 32.5 of above-mentioned Φ 22.5 are listed as under the solid solution aging condition that provides after the thermal treatment at table 3 the 6th and 7, are processed into laboratory sample and carry out performance test, obtain every performance data of the titanium alloy rod bar of embodiment 4~9 in the table 4.The preceding plasticity of hot exposure means that heat exposes preceding material temperature-room type plasticity in the table 4, and hot exposure back plasticity means the temperature-room type plasticity of material behind 600 ℃ of following sample heat exposure 100h.

Table 2

Table 3

The composition numbering Transformation temperature ℃ The hot-work of β phase region Alpha+beta phase region finish forge The alpha+beta phase region rolls rod The solid solution system Institution of prescription ??I ??1055 ??1150℃,FR=4.0 ??1000℃.FR=5.6 ??1000 ??℃,S=75% ??1025℃/2h/AC ??700℃/2h/AC ??II ??1035 ??1150℃,FR=4.0 ??1000℃.FR=5.6 ??1000 ??℃,S=75% ??1005℃/2h/AC ??700℃/2h/AC ??III ??1040 ??1100℃,FR=2.6 ??1005℃.FR=2.7 ??1005 ??℃,S=75% ??1005℃/2h/AC ??700℃/2h/AC

??IV ??1055 ??1120℃,FR=4.0 ??1020℃.FR=7.4 ??\ ??1025℃/2h/AC ??700℃/2h/AC ??V ??1050 ??1120℃,FR=4.0 ??1020℃.FR=7.4 ??\ ??1020℃/2h/AC ??700℃/2h/AC ??VI ??1045 ??1120℃,FR≥4.0 ??1000℃,FR=7.4 ??\ ??1020℃/2h/AC ??700℃/2h/AC

* FR-ratio of forging reduction, S-deflection, %

Table 4

Embodiment 10~12

Three kinds of compositions that are numbered HI, VI, V in the table 2 are smelted into the ingot casting of Φ 518 by embodiment 4~9 described methods.After excising the cap mouth, removing surface scale, ingot casting is adopting dydraulic forging to become the bar of Φ about 260 1200 ℃ of left and right sides coggings about 1150 ℃.After this, cut the blank that a block specifications is Φ 260 * 460, processing parameter by table 5 the 3rd, 4,5 row carries out low-Gao-low technology with water pressure engine successively, after this hot-work is all finished at the alpha+beta two-phase region, processing parameter sees Table 5 the 5th, 6 row, and making specification at last is the cake ring base of Φ 525 * Φ 175 * 120.Cake ring base is dissected the back along the sampling of C-R direction, and after thermal treatment under the given solid solution aging condition of table 5 the 7th, 8 row, is processed into sample and carries out performance test, obtains every performance data of embodiment 10~12, sees Table 6.Plasticity meant the temperature-room type plasticity of alloy after 600 ℃ of following blank heat expose 100h after heat exposed in the table 6.

Table 5

* FR-ratio of forging reduction

Table 6

A large amount of experiments show: from the alloy over-all properties of embodiment 4~12 as can be seen, high-temperature titanium alloy of the present invention has good heat resistance and thermostability coupling under 600 ℃, it not only is suitable for aircraft engine and makes high temperature rotatable parts and/or stationary parts life-time service; Also being suitable on the spacecraft 600 ℃ or 600 ℃ uses with the upper-part short-term.

Claims (4)

1. the hot-work and the heat treating method of the high-temperature titanium alloy of a high heat-intensity, high thermal stability, said alloying constituent and weight percent are Al:5.0%~6.3%; Sn:3.0%~5.0%; Zr:2.5%~7.0%; Mo:0.2%~1.5%; Si:0.20%~0.55%; Nb:0.2%~1.0%; Ta:0.2%~3.0%; C:0.01%~0.09%, surplus are Ti and unavoidable impurities element, it is characterized in that hot-work and thermal treatment carries out as follows:
A) alpha+beta two-phase region heats forged, the back shrend is forged in ratio of forging reduction 〉=1.5;
B) β phase region heats forged, the back air cooling is forged in ratio of forging reduction 〉=1.5;
C) alpha+beta two-phase region heats forged, the back air cooling is forged in ratio of forging reduction 〉=6.0;
D) heat treating regime: beta transformation point-(10 ℃~40 ℃)/2h/ air cooling or oil quenching+(630 ℃~750 ℃)/2h/ air cooling.
2. press the hot-work and the heat treating method of the high-temperature titanium alloy of the described high heat-intensity of claim 1, high thermal stability, it is characterized in that: the composition of said alloy and weight percent are Al:5.37%~6.02%; Sn:3.77%~4.03%; Zr:3.32%~3.42%; Mo:0.38%~0.70%; Si:0.34%~0.42%; Nb:0.37%~0.41%; Ta:0.36%~0.99%; C:0.038%~0.056%, Fe:<0.07%, O<0.14%, surplus is Ti and inevitable other impurity element.
3. the hot-work and the heat treating method of the high-temperature titanium alloy of a high heat-intensity, high thermal stability, said alloying constituent and weight percent are Al:5.0%~6.3%; Sn:3.0%~5.0%; Zr:2.5%~7.0%; Mo:0.2%~1.5%; Si:0.20%~0.55%; Nb:0.2%~1.0%; Ta:0.2%~3.0%; C:0.01%~0.09%, surplus are Ti and unavoidable impurities element, it is characterized in that carrying out as follows hot-work and thermal treatment:
A) β phase region heats forged, the back air cooling is forged in ratio of forging reduction 〉=1.5;
B) the alpha+beta two-phase region is forged with precise forging machine, and 2~3 fire are finished, total ratio of forging reduction 〉=5.0, and last fire time ratio of forging reduction 〉=3.0, or:
C) the alpha+beta two-phase region rolls rod, requires the last fire of blank time texturing temperature at two-phase region, and deflection 〉=30% or ratio of forging reduction 〉=1.4; Last heating once and rolling Heating temperature in beta transformation point-(20 ℃~60 ℃) scope, deflection 〉=60%;
D) heat treating regime: beta transformation point-(20 ℃~60 ℃)/2h/ air cooling or oil quenching+(630 ℃~750 ℃)/2h/ air cooling.
4. press the hot-work and the heat treating method of the high-temperature titanium alloy of the described high heat-intensity of claim 3, high thermal stability, it is characterized in that: the composition of said alloy and weight percent are Al:5.37%~6.02%; Sn:3.77%~4.03%; Zr:3.32%~3.42%; Mo:0.38%~0.70%; Si:0.34%~0.42%; Nb:0.37%~0.41%; Ta:0.36%~0.99%; C:0.038%~0.056%, Fe:<0.07%, O<0.14%, surplus is Ti and inevitable other impurity element.
CNB2007100117710A 2007-06-19 2007-06-19 The hot-work of the high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability and heat treating method CN100567534C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CNB2007100117710A CN100567534C (en) 2007-06-19 2007-06-19 The hot-work of the high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability and heat treating method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CNB2007100117710A CN100567534C (en) 2007-06-19 2007-06-19 The hot-work of the high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability and heat treating method

Publications (2)

Publication Number Publication Date
CN101104898A CN101104898A (en) 2008-01-16
CN100567534C true CN100567534C (en) 2009-12-09

Family

ID=38998976

Family Applications (1)

Application Number Title Priority Date Filing Date
CNB2007100117710A CN100567534C (en) 2007-06-19 2007-06-19 The hot-work of the high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability and heat treating method

Country Status (1)

Country Link
CN (1) CN100567534C (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2507289C1 (en) * 2013-03-28 2014-02-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Titanium-based alloy and item made from it

Families Citing this family (48)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040221929A1 (en) 2003-05-09 2004-11-11 Hebda John J. Processing of titanium-aluminum-vanadium alloys and products made thereby
US7837812B2 (en) 2004-05-21 2010-11-23 Ati Properties, Inc. Metastable beta-titanium alloys and methods of processing the same by direct aging
FR2936172B1 (en) * 2008-09-22 2012-07-06 Snecma Process for forging a thermomechanical piece of 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
US10053758B2 (en) * 2010-01-22 2018-08-21 Ati Properties Llc Production of high strength titanium
US9255316B2 (en) 2010-07-19 2016-02-09 Ati Properties, Inc. Processing of α+β titanium alloys
US8499605B2 (en) 2010-07-28 2013-08-06 Ati Properties, Inc. Hot stretch straightening of high strength α/β processed titanium
US9206497B2 (en) 2010-09-15 2015-12-08 Ati Properties, Inc. Methods for processing titanium alloys
US8613818B2 (en) 2010-09-15 2013-12-24 Ati Properties, Inc. Processing routes for titanium and titanium alloys
CN101934341A (en) * 2010-09-20 2011-01-05 宝鸡市利泰有色金属有限公司 Forging technology of TC4 titanium alloy cylindrical part
US10513755B2 (en) 2010-09-23 2019-12-24 Ati Properties Llc High strength alpha/beta titanium alloy fasteners and fastener stock
US8652400B2 (en) 2011-06-01 2014-02-18 Ati Properties, Inc. Thermo-mechanical processing of nickel-base alloys
CN102952968A (en) * 2011-08-23 2013-03-06 上海航天精密机械研究所 Particle reinforced heatproof titanium alloy
CN102581188B (en) * 2012-02-29 2014-07-30 湖南金天钛业科技有限公司 Method for machining TC4-DT titanium alloy large-specification slab forged piece
US9957836B2 (en) * 2012-07-19 2018-05-01 Rti International Metals, Inc. Titanium alloy having good oxidation resistance and high strength at elevated temperatures
US9869003B2 (en) 2013-02-26 2018-01-16 Ati Properties Llc Methods for processing alloys
US9192981B2 (en) 2013-03-11 2015-11-24 Ati Properties, Inc. Thermomechanical processing of high strength non-magnetic corrosion resistant material
US9050647B2 (en) 2013-03-15 2015-06-09 Ati Properties, Inc. Split-pass open-die forging for hard-to-forge, strain-path sensitive titanium-base and nickel-base alloys
US9777361B2 (en) 2013-03-15 2017-10-03 Ati Properties Llc Thermomechanical processing of alpha-beta titanium alloys
CN104745871B (en) * 2013-11-04 2017-03-01 铜山县丰华工贸有限公司 A kind of method preparing Al-Ti alloy impeller
CN103735316B (en) * 2013-12-18 2016-01-27 宁波德美家医疗科技有限公司 A kind of orthopedic navigation device and preparation method thereof
CA2947981A1 (en) * 2014-05-15 2016-02-18 General Electric Company Titanium alloys and their methods of production
CN104018028B (en) * 2014-06-23 2016-06-29 北京科技大学 A kind of high alumina height silicon cast titanium alloy
CN105316524B (en) * 2014-08-04 2017-11-28 中国科学院金属研究所 Strong high-ductility titanium alloy and preparation method thereof in a kind of Ti Al Zr Mo V systems
CN104388755A (en) * 2014-12-20 2015-03-04 常熟市强盛电力设备有限责任公司 Wind generator stator frame
CN104454390A (en) * 2014-12-20 2015-03-25 常熟市强盛电力设备有限责任公司 Wind turbine generator unit cabin base
CN104454389A (en) * 2014-12-20 2015-03-25 常熟市强盛电力设备有限责任公司 Direct-driven rotor for wind driven generator
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
US10094003B2 (en) 2015-01-12 2018-10-09 Ati Properties Llc Titanium alloy
CN104745867A (en) * 2015-03-27 2015-07-01 常熟市双羽铜业有限公司 High-temperature-resistant titanium alloy plate
CN105018789A (en) * 2015-07-16 2015-11-04 北京百慕航材高科技股份有限公司 Casting titanium alloy and preparation method thereof
CN105018793B (en) * 2015-08-28 2017-03-22 西北有色金属研究院 Heat-resistant Ti alloy
CN105154701B (en) * 2015-10-14 2017-08-18 华中科技大学 A kind of method that use selective laser melting RP technique prepares high-temperature titanium alloy
US10502252B2 (en) 2015-11-23 2019-12-10 Ati Properties Llc Processing of alpha-beta titanium alloys
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
CN106244853B (en) * 2016-08-30 2018-04-06 南京赛达机械制造有限公司 A kind of anti-water erosion titanium alloy turbine blade
CN106566949A (en) * 2016-11-08 2017-04-19 中航装甲科技有限公司 Preparation method and mixing device of graphene/titanium alloy composite armor material
CN106435270B (en) * 2016-11-15 2017-12-01 东北大学 Laser 3D printing TC21 titanium alloy powders and preparation and application
CN106967897B (en) * 2016-11-18 2019-02-19 中国科学院金属研究所 A kind of inexpensive, Ti alloy with high performance
CN107515989A (en) * 2017-08-31 2017-12-26 哈尔滨理工大学 A kind of double-response face method for calculating aero-engine leaf dish high-temerature creep reliability
CN107625405A (en) * 2017-09-10 2018-01-26 李瑞卿 One kind is without oil smoke titanium pot
CN107475566A (en) * 2017-10-11 2017-12-15 宝鸡市永盛泰钛业有限公司 A kind of high-temperature titanium alloy and preparation method thereof
CN107604210A (en) * 2017-11-23 2018-01-19 宁国市华成金研科技有限公司 A kind of high temperature resistant titanium alloy plate
CN108179314A (en) * 2017-11-28 2018-06-19 杭州杭联汽车连杆有限公司 A kind of titanium alloy and its manufacturing method
CN108588606B (en) * 2018-05-24 2019-11-05 太原理工大学 A kind of process of the high tough beta-titanium alloy crystal grain of rapid refinement
CN109295342A (en) * 2018-08-22 2019-02-01 北京理工大学 A kind of Ti-Al-Mo-Sn-Zr-Si-V alloy and preparation method thereof
CN109234554A (en) * 2018-09-30 2019-01-18 中国科学院金属研究所 A kind of preparation method of high-temperature titanium alloy bar

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2507289C1 (en) * 2013-03-28 2014-02-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Titanium-based alloy and item made from it

Also Published As

Publication number Publication date
CN101104898A (en) 2008-01-16

Similar Documents

Publication Publication Date Title
CN104694808B (en) High-entropy alloy with dispersion nano-sized precipitate strengthening effect and preparing method thereof
EP2860272B1 (en) Ni-BASED ALLOY
US9458527B2 (en) Secondary titanium alloy and the art of its manufacture
JP5299610B2 (en) Method for producing Ni-Cr-Fe ternary alloy material
CN102230097B (en) Preparation method of titanium alloy bars
RU2066253C1 (en) Method of making turbine blades
CN101225494B (en) Magnesium alloy material and production thereof
CN102839297B (en) High-temperature titanium alloy and preparation method thereof
EP0464366B1 (en) Process for producing a work piece from an alloy based on titanium aluminide containing a doping material
CN104018027B (en) A kind of heat-resistant titanium alloy and machining manufacture thereof and application
CN100485079C (en) Technique for processing titanium alloy sheet material
JP4179024B2 (en) High speed tool steel and manufacturing method thereof
CN105177344B (en) Cu-Fe alloy wire and preparing method thereof
JP6165171B2 (en) Titanium alloys with improved properties
CN103938102B (en) A kind of preparation method of ferrum-chromium-aluminum system multi-element high-resistance electrothermal alloy
Tang et al. Hot forging design and microstructure evolution of a high Nb containing TiAl alloy
CN105132772B (en) Low-cost non-rare-earth type high-strength magnesium alloy and preparing method thereof
EP2980258B1 (en) Ni-BASED SUPERALLOY AND METHOD FOR PRODUCING SAME
EP3040430B1 (en) Copper alloy sheet material and method for producing same, and current-carrying component
CN104532057B (en) A kind of Ti6242 titanium alloy and the preparation method of small-sized bar thereof
FR2838135A1 (en) CORROSIVE ALLOY PRODUCTS A1-Zn-Mg-Cu WITH VERY HIGH MECHANICAL CHARACTERISTICS, AND AIRCRAFT STRUCTURE ELEMENTS
EP1924718B1 (en) Production of fine grain micro-alloyed niobium sheet via ingot metallurgy
CN1962179A (en) Direct rolling of cast gamma titanium aluminide alloys
CN102418042B (en) Novel manufacturing process of phi 300 mm-phi 700 mm high-carbon high-chromium cold-working die steel forged round steel
CN102303083B (en) Quick isothermal forging method and device for preparing less-deformable alloy cake blank

Legal Events

Date Code Title Description
PB01 Publication
C06 Publication
SE01 Entry into force of request for substantive examination
C10 Entry into substantive examination
GR01 Patent grant
C14 Grant of patent or utility model