CN106435267A - High temperature-resistance and wear-resistance titanium base composite material and preparation method thereof - Google Patents
High temperature-resistance and wear-resistance titanium base composite material and preparation method thereof Download PDFInfo
- Publication number
- CN106435267A CN106435267A CN201610879434.2A CN201610879434A CN106435267A CN 106435267 A CN106435267 A CN 106435267A CN 201610879434 A CN201610879434 A CN 201610879434A CN 106435267 A CN106435267 A CN 106435267A
- Authority
- CN
- China
- Prior art keywords
- titanium
- mass fraction
- temperature
- granularity
- alloy
- Prior art date
- Legal status (The legal status 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 status listed.)
- Granted
Links
- 239000010936 titanium Substances 0.000 title claims abstract description 56
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 title claims abstract description 45
- 229910052719 titanium Inorganic materials 0.000 title claims abstract description 45
- 239000002131 composite material Substances 0.000 title claims abstract description 44
- 238000002360 preparation method Methods 0.000 title claims abstract description 8
- 239000000956 alloy Substances 0.000 claims abstract description 23
- 239000002994 raw material Substances 0.000 claims abstract description 10
- 239000011159 matrix material Substances 0.000 claims description 41
- 229910045601 alloy Inorganic materials 0.000 claims description 19
- 229910052782 aluminium Inorganic materials 0.000 claims description 19
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 16
- 239000000463 material Substances 0.000 claims description 16
- 239000010955 niobium Substances 0.000 claims description 15
- 238000002844 melting Methods 0.000 claims description 14
- 230000008018 melting Effects 0.000 claims description 14
- 238000004458 analytical method Methods 0.000 claims description 13
- 229910052758 niobium Inorganic materials 0.000 claims description 13
- 229910052726 zirconium Inorganic materials 0.000 claims description 13
- 238000005266 casting Methods 0.000 claims description 12
- 229910052710 silicon Inorganic materials 0.000 claims description 12
- 229910052718 tin Inorganic materials 0.000 claims description 12
- 239000000203 mixture Substances 0.000 claims description 11
- 229910052750 molybdenum Inorganic materials 0.000 claims description 11
- 229910052721 tungsten Inorganic materials 0.000 claims description 11
- 230000002708 enhancing effect Effects 0.000 claims description 10
- 238000005242 forging Methods 0.000 claims description 9
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 claims description 6
- 239000004411 aluminium Substances 0.000 claims description 6
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 5
- 239000012535 impurity Substances 0.000 claims description 5
- 210000003625 skull Anatomy 0.000 claims description 5
- 239000000126 substance Substances 0.000 claims description 5
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052802 copper Inorganic materials 0.000 claims description 4
- 239000010949 copper Substances 0.000 claims description 4
- 230000009466 transformation Effects 0.000 claims description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 4
- 229910001182 Mo alloy Inorganic materials 0.000 claims description 3
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 3
- 229910001257 Nb alloy Inorganic materials 0.000 claims description 3
- 235000010627 Phaseolus vulgaris Nutrition 0.000 claims description 3
- 244000046052 Phaseolus vulgaris Species 0.000 claims description 3
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 3
- QNTVPKHKFIYODU-UHFFFAOYSA-N aluminum niobium Chemical compound [Al].[Nb] QNTVPKHKFIYODU-UHFFFAOYSA-N 0.000 claims description 3
- 239000000470 constituent Substances 0.000 claims description 3
- 238000009415 formwork Methods 0.000 claims description 3
- 239000000155 melt Substances 0.000 claims description 3
- 239000011733 molybdenum Substances 0.000 claims description 3
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims description 3
- 238000005070 sampling Methods 0.000 claims description 3
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 3
- 239000011863 silicon-based powder Substances 0.000 claims description 2
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 claims 1
- 229910052737 gold Inorganic materials 0.000 claims 1
- 239000010931 gold Substances 0.000 claims 1
- 229910052725 zinc Inorganic materials 0.000 claims 1
- 229910001069 Ti alloy Inorganic materials 0.000 abstract description 34
- 230000002787 reinforcement Effects 0.000 abstract description 5
- 238000005728 strengthening Methods 0.000 description 11
- 238000005260 corrosion Methods 0.000 description 10
- 230000007797 corrosion Effects 0.000 description 10
- 238000005299 abrasion Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 239000000243 solution Substances 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 4
- 230000007423 decrease Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 230000003647 oxidation Effects 0.000 description 4
- 238000007254 oxidation reaction Methods 0.000 description 4
- 150000001875 compounds Chemical class 0.000 description 3
- 230000001965 increasing effect Effects 0.000 description 3
- 229910021332 silicide Inorganic materials 0.000 description 3
- FVBUAEGBCNSCDD-UHFFFAOYSA-N silicide(4-) Chemical compound [Si-4] FVBUAEGBCNSCDD-UHFFFAOYSA-N 0.000 description 3
- 239000010703 silicon Substances 0.000 description 3
- 230000008602 contraction Effects 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 239000010408 film Substances 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 238000001556 precipitation Methods 0.000 description 2
- 239000006104 solid solution Substances 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- 150000003608 titanium Chemical class 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- CWYNVVGOOAEACU-UHFFFAOYSA-N Fe2+ Chemical compound [Fe+2] CWYNVVGOOAEACU-UHFFFAOYSA-N 0.000 description 1
- 229910021330 Ti3Al Inorganic materials 0.000 description 1
- 229910009843 Ti3Sn Inorganic materials 0.000 description 1
- 238000002441 X-ray diffraction Methods 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- ZXTFQUMXDQLMBY-UHFFFAOYSA-N alumane;molybdenum Chemical compound [AlH3].[Mo] ZXTFQUMXDQLMBY-UHFFFAOYSA-N 0.000 description 1
- 230000003026 anti-oxygenic effect Effects 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 229910001325 element alloy Inorganic materials 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000005121 nitriding Methods 0.000 description 1
- 230000006911 nucleation Effects 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 229920001296 polysiloxane Polymers 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 238000010025 steaming Methods 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
- 238000005496 tempering Methods 0.000 description 1
- 239000010409 thin film Substances 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- 229910052720 vanadium Inorganic materials 0.000 description 1
- GPPXJZIENCGNKB-UHFFFAOYSA-N vanadium Chemical compound [V]#[V] GPPXJZIENCGNKB-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C14/00—Alloys based on titanium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/10—Alloys containing non-metals
- C22C1/1036—Alloys containing non-metals starting from a melt
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/10—Alloys containing non-metals
- C22C1/1036—Alloys containing non-metals starting from a melt
- C22C1/1047—Alloys containing non-metals starting from a melt by mixing and casting liquid metal matrix composites
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
- C22C32/0047—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with carbides, nitrides, borides or silicides as the main non-metallic constituents
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
- C22C32/0047—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with carbides, nitrides, borides or silicides as the main non-metallic constituents
- C22C32/0073—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with carbides, nitrides, borides or silicides as the main non-metallic constituents only borides
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
- C22F1/18—High-melting or refractory metals or alloys based thereon
- C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Composite Materials (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
Abstract
The invention belongs to the field of composite materials, and in particular, relates to a high temperature-resistance and wear-resistance titanium base composite material and a preparation method thereof. The composite material comprises the following raw material components in percentage by weight: 6-7% of Al, 3-4.5% of Sn, 8-10% of Zr, 0.8-1% of Mo, 0.2-0.3% of Si, 0.8-1% of Nb, 0.8-1% of W, 4.5-6.5% of reinforcement phase by mass, and the balance of Ti. The wear-resistance titanium base composite material can be used at high temperature; and a titanium alloy material is reinforced through mixed reinforcement phase to achieve the titanium base composite material with high wear resisting degree at high temperature, so that the application range of a titanium alloy is widened.
Description
Technical field
The invention belongs to field of compound material, more particularly, to a kind of heat resistant and wear resistant damage titanium matrix composite and its preparation side
Method.
Background technology
Titanium alloy is the alloy adding other elements composition with titanium for base, has very high specific strength, in aerospace
Be used widely in field, frequently as the important feature material of aircraft and spacecraft.In recent years, due to titanium alloy have good
Corrosion resistance, high temperature performance, its application in the field such as oil and chemical industry gradually expands, and is used as heat exchanger, reaction tower, steaming
Structural material under the conditions of the corrosion such as the blade of vapour turbine, valve, pump line road or distinct temperature.
Existing titanium alloy material, compared with ferrous materials, also has that wearability is low, be difficult to machining and elastic modelling quantity
Low shortcoming, hinders the expansion of titanium alloy range of application, the weakness that particularly hardness is low, anti-wear performance is poor.The hardness of pure titanium
It is about HV150-200, titanium alloy is typically not greater than HV350.Under many circumstances, such hardness number can not meet actual production
The requirement of application.The low wearability of titanium alloy is attributable to two principal elements：One is inductile shearing drag and low processing is hard
Rate；Two be oxide on surface protective effect very low.The oxide-film that the oxygen of titanium alloy and in the air is formed, this oxide-film is rubbing
Wipe in contact and easily peel off；Simultaneously in the case of more rugged environment and generation crevice corrosion, the corrosion resistant of titanium alloy
Corrosion also will substantially reduce.At present, in order to improve the corrosion resistance of titanium alloy, generally titanium alloy is surface-treated, for example
The techniques such as nitriding, anodic oxidation, differential arc oxidation.If but simply applying thin film in titanium alloy surface with these techniques at present, only
It is only the corrosion resistance strengthening titanium alloy surface layer, be not an up the corrosion resistance of titanium alloy substrate；And these techniques by
Very thin in depth of penetration, under friction environment, long period work, may result in coating and is worn, destroy the corrosion resistant on surface
Erosion layer.
Titanium alloy is poor due to its wearability, when prepared part occurs fine motion abrasion, can cause fatigue strength
Rapid decline, is therefore difficult to accomplish to use titanium alloy in a large number on the modified fluoromaterial such as engineering goods, automobile component, otherwise exists
Potential safety hazard.In order to meet the market demand of titanium alloy, need badly and develop the titanium matrix composite that a kind of heat resistant and wear resistant damages.
Content of the invention
The present invention is directed to the problems referred to above, provides a kind of abrasion-resistant titanium basic composite that can use at high temperature, by mixing
Strengthen and mutually strengthen titanium alloy material, reached the titanium matrix composite of high abrasion degree during high temperature, thus widening answering of titanium alloy
Use scope.
To achieve these goals, the invention provides a kind of heat resistant and wear resistant damages titanium matrix composite, raw material composition is pressed
Percentage by weight proportioning is as follows：Al be 6-7%, Sn be 3-4.5%, Zr be 8-10%, Mo be 0.8-1%, Si be 0.2-0.3%, Nb
It is 0.8-1% for 0.8-1%, W, add the enhancing phase of the mass fraction of 4.5%-6.5%, balance of Ti.
Described enhancing is mutually combining of TiB or TiB and TiC.
To achieve these goals, present invention also offers this heat resistant and wear resistant damages the preparation method of titanium matrix composite,
Comprise the following steps that.
Step 1, get the raw materials ready：Weigh titanium sponge, sponge zirconium, the aluminum stannum containing mass fraction 50% stannum and 50% aluminum by weight percentage
Alloy, granularity is 0.25-3mm；Aluminium molybdenum alloys containing mass fraction 50% molybdenum and 50% aluminum, granularity is 0.4-4mm；Containing quality
Fraction is the aluminum niobium alloy of 50% niobium and 50% aluminum, and granularity is 0.25-2mm；Fine aluminium bean, granularity is 6-9mm, pure tungsten powder,
Granularity is 0.4-1 μm, pure silicon powder, and granularity is 125-325 mesh, and enhancing phase granularity is 0.01-2mm.
Step 2, melting：Melting is carried out using vacuum consumable water jacketed copper crucible sensing skull crucible, monitor system is 320-
345kW, carries out melting, suction to 0.15Pa, is incubated 5-8min after melting, holding temperature is not less than fusing point under vacuum condition
1995 DEG C of temperature, obtains alloy solution；Sense under the vacuum condition of skull crucible in vacuum consumable water jacketed copper crucible, by alloy solution
It is cast in formwork for cylindrical columns, in atmosphere, naturally cool to room temperature, obtain alloy cast ingot.
Step 3, ingot casting analysis：With 20 lathes from alloy cast ingot top, middle part, bottom sampling, analyzed with spectroanalysis instrument
Chemical analysis and impurity composition, whether the chemical analysis to analyze ingot casting with this are uniform, the then transformation temperature of analysis of material.
Step 4, forging：By step（3）Detect that qualified alloy of ingot ingot casting preheating is 1050-1100 DEG C to temperature, and
Keep 45min at such a temperature, forged with 5000t hydraulic press, the total deformation of three draw outs is not less than 85%, forging
Make and complete.
Beneficial effects of the present invention.
In the composite of the present invention, Mo can improve the heat resistance of titanium alloy, makes titanium alloy material in high temperature environments
Use time extends, Mo solution strengthening β phase, and significantly reducing the transformation temperature of titanium alloy, increasing quenching degree, thus strengthening heat treatment
Strengthening effect, the effect that Mo improves creep resistance is better than vanadium, can also improve the corrosion resistance of alloy；Si can carry heavy alloyed anti-compacted
Become performance, but excessive element silicon can not be added, because silicide, in the long-term exposure of high temperature, may proceed on crystal boundary and phase boundary
Separate out and constantly accumulate, heat stability can be affected, silicone content of the present invention controls 0.2-0.3%, and silicon can be completely dissolved in can in matrix
To obtain optimal croop property.
Control the content range of Al, Sn, Zr in the present invention（Al is 6-7%, Sn is 8-10% for 3-4.5%, Zr）, more than one
After determining scope, constituent content is higher, and after beat exposure, the contraction percentage of area reduces more.Because Al, Sn and Ti form Ti3Al、
Ti3Sn, the content of Al, Sn, Zr controls, and on the one hand can promote Ti3The ordering of Al, on the other hand can also generate Zr3Al、
Zr3The compounds such as Sn；Zr is often used as improving a kind of effective element of heat resistance, and it forms continuous α and β solid solution with titanium,
Diffusion velocity in titanium is slower, and restricted silicide is grown up the effect being allowed in disperse state, makes tiny Precipitation of Silicide
Mutually it is uniformly distributed, adding Zr can make the creep limit of titanium alloy significantly improve；For high aluminum and titanium alloy, add a small amount of Zr permissible
Increase α2（α2It is one of titanium alloy microstructure）With the mispairing coefficient of matrix, promote dislocation bypass mechanism to be formed, increase material
The plasticity of material.
The increase of aluminium content is favourable to the creep-resistant property of titanium alloy and the raising of antioxygenic property, but, also lead simultaneously
The plasticity of titanium alloy and deformability is caused to decline.The amount of Nb, W element adding in the present invention is less than 1%, molten less than in α titanium
Xie Du（Nb can reach 20%, W and can also reach 2%）, α can be made2The C curve of phase moves right, α2The precipitation of phase is slack-off, and nucleation is equal
Even, increase plasticity and the toughness of material；And decrease the tendency of ordering, slow down the effect becoming fragile, so both can improve
Creep-resistant property, can improve heat stability again；If but both constituent contents are too high（More than 1%）, especially more than dissolve
Degree, will make remaining β phase increase, at high temperature long-term expose after, so that remaining β phase is decomposed in a large number and to reduce alloy thermally-stabilised
Property, and then reduce the anti-wear performance under the conditions of titanium alloy high-temperature.
Titanium matrix composite of the present invention, with the addition of enhancing phase, and the selection strengthening phase is to improve material against oxidative ability, intensity
It is foundation with hardness, this requires to strengthen mutually has the features such as high rigidity, high-melting-point.Select TiC and TiB as reinforcement, be
Due to the similar density of the density of the two and titanium, fusing point is respectively 3067 DEG C and 2200 DEG C, and thermal coefficient of expansion is 8 × 10-6/ DEG C left side
The right side, with titanium alloy thermal coefficient of expansion（The coefficient of expansion 8.2）Close.Due to strengthen mutually these physical properties so that itself and titanium alloy
The compatibility between matrix is good.The interpolation strengthening phase makes the intensity of titanium matrix composite be significantly increased, but moulds simultaneously
Property also decline therewith, and in titanium matrix composite Nb, W element interpolation, so that its plasticity is increased again, and improve high temperature resist
Oxidation susceptibility.Multiple element of the present invention is with the interaction strengthening phase so that titanium matrix composite hardness improves, wearability increases
By force, there is good combination property simultaneously.
The present invention, with titanium alloy as matrix, adds and strengthens phase, strengthens the mutually interface binding power and matrix between stronger.Compound
Material, under the working environment of fretting wear, can cause to the interface between reinforcement and matrix to damage, occur in ambient temperature
During change or when fretting wear produces temperature change, can cause enhancing mutually and matrix expands contraction, if thermal expansion system simultaneously
Number difference is larger, can cause the debonding at interface.But, the heat strengthening between phase and matrix of titanium matrix composite of the present invention
Relatively, interface binding power is strong for the coefficient of expansion.The titanium matrix composite of this method preparation, due to adding the microcosmic strengthening in phase
In reaction, C, B element and titanium alloy substrate react generation, and the bond strength between obtained reinforcement and matrix is high,
The material property being finally obtained is preferably also.Therefore, strengthening mutually and having with the titanium matrix composite made by this titanium matrix
There is good wearability.
In sum, titanium matrix composite of the present invention, is mutually to strengthen interface binding power so that material by adding to strengthen
Intensity enhancing, simultaneously add Nb, elements such as w with enhancing phase interaction, that is, on the premise of proof strength, improve material
The plasticity of material, also improves high-temperature oxidation resistance so that the hardness of titanium matrix composite improves, wearability strengthens simultaneously.?
At 650 DEG C, still can have good tensile strength and percentage elongation, and this titanium matrix composite breakthrough titanium alloy is not wear-resisting
Technological difficulties.
Brief description
Fig. 1 is the microscopic structure that embodiment 1 adds the titanium matrix composite strengthening phase TiB.
Fig. 2 is the microscopic structure that embodiment 2 adds the titanium matrix composite strengthening phase TiB+TiC.
Fig. 3 is the friction coefficient curve of embodiment 1 titanium matrix composite.
Fig. 4 is the XRD curve of embodiment 1 titanium matrix composite.
Specific embodiment
With reference to specific embodiment, the present invention is described in detail.
Embodiment 1.
A kind of abrasion-resistant titanium basic composite using at a temperature of 650 DEG C includes Al 6%, Sn 4%, Zr by weight percentage
10%th, Mo 1%, Si 0.25%, Nb 1%, W 1%, adds the TiB, balance of Ti of 5% mass fraction.
The present embodiment is with the ingot casting of 15kg as standard.
Step one, get the raw materials ready：Prepare titanium sponge 11.32kg, sponge zirconium 1.55kg, the aluminum stannum containing 50% stannum by weight percentage
Alloy 1.2kg, the aluminium molybdenum alloys 0.3kg containing 50% molybdenum, the aluminum niobium alloy 0.3kg containing 50% niobium, fine aluminium bean 0.04kg, tungsten
0.152kg, silicon 0.0378kg, TiB 0.75kg.
Step 2, melting：Melting is carried out using vacuum cold-crucible sensing skull crucible.True for 335kW in monitor system
Carry out melting, suction to 0.15Pa, after melting, insulation 8min obtains alloy solution, 2000 DEG C of holding temperature under empty condition.
Under vacuum, further alloy solution is cast in formwork for cylindrical columns, in atmosphere, naturally cools to room temperature, obtain
Alloy cast ingot.
Step 3, ingot casting analysis：With 20 lathes from ingot casting sampling, analytical chemistry composition and impurity composition, to be analyzed with this
Whether the chemical analysis of ingot casting are uniform, the then transformation temperature of analysis of material.
Step 4, forging：By step（3）Detect that qualified ingot casting preheating is 1100 DEG C to temperature, and protect at such a temperature
Hold 45min, forged with 5000t hydraulic press, the first fire pulling deflection is 40%, melts down and is heated to 1100 DEG C, insulation
30min；Second fire pulling deflection is 30%, melts down and is heated to 1075 DEG C, is incubated 30min；3rd fire pulling deflection is 25%,
The total deformation of three forgings is more than 85%, and forging completes.
Embodiment 2.
A kind of abrasion-resistant titanium basic composite mass percent is by Al 6.3%, Sn 4.5%, Zr 8.8%, Mo 0.82%, Si
0.3%th, Nb 0.87%, W 0.87%, adds 2.5% TiB of mass fraction and 3.5% TiC of mass fraction and the Ti of surplus
Make.
Embodiment 3.
A kind of abrasion-resistant titanium basic composite mass percent is by Al 7%, Sn 3%, Zr 8%, Mo 0.8%, Si 0.2%, Nb
0.8%th, W 0.8%, adds 2.5% TiB of mass fraction and 2.5% TiC of mass fraction and the Ti of surplus and makes.
First, following performance detection analysis is carried out to the titanium matrix composite of above-described embodiment.
Microstructure observation is carried out to embodiment 1, sees Fig. 1.It is observed that TiB is many being distributed along crystal boundary, size is less, main
Needle-like to be, illustrates the high-temperature stability of TiB very well, strengthens wearability during titanium matrix composite high temperature.If strengthen being mutually
TiC and TiB, i.e. embodiment 2, then TiC mostly larger-size graininess or strip, TiB is graininess or filamentary structure,
See Fig. 2.
Measuring friction coefficient is carried out to embodiment 1, sees Fig. 3.As can be seen from the figure under room temperature and the condition of high temperature, friction
Coefficient is very stable, not prolongation over time and fluctuate, this illustrates that its anti-wear performance is stable, is not subject to the shadow of temperature and time
Ring.
XRD analysis are carried out to embodiment 1, sees Fig. 4.It can be seen that in addition to Ti matrix, the enhancing existing is mutually
TiB, has no the generation of other impurities phase, and the presence that this explanation TiB can be stable is in the composite.Analysis result from XRD
From the point of view of, have no the phase that other elements reaction generates in prepared titanium matrix composite, other alloying element solid solutions such as Al, Si are described
To among matrix, chemical reaction between each element added in matrix alloy, is not occurred to generate impurity yet.
Tension test is carried out to embodiment 1, records at ambient temperature, its tensile strength is >=1200MPa, percentage elongation is
10% about；At 650 DEG C of high temperature, its tensile strength is >=600MPa, and percentage elongation is 25% about.The high temperature titanium commonly used at present closes
Golden TC11, during its room temperature, its tensile strength is >=890MPa, and percentage elongation is 10%；At 450 DEG C of high temperature, its tensile strength be >=
620MPa, percentage elongation is 10%.
Claims (9)
1. a kind of heat resistant and wear resistant damages titanium matrix composite it is characterised in that raw material composition components by weight percentage includes：Al
For 6-7%, Sn be 3-4.5%, Zn be 8-10%, Mo be 0.8-1%, Si be 0.2-0.3%, Nb be 0.8-1%, W be 0.8-1%, add
The enhancing phase of the mass fraction of 45%-65%, balance of Ti.
2. composite as claimed in claim 1 is it is characterised in that described hardening constituent is TiB and TiB and the combining of TiC.
3. composite as claimed in claim 1 is it is characterised in that raw material composition components by weight percentage is as follows：Al
6%th, Sn 4%, Zr 10%, Mo 1%, Si 0.25%, Nb 1%, W 1%, add the TiO, balance of Ti of 5% mass fraction.
4. composite as claimed in claim 1 is it is characterised in that raw material composition components by weight percentage is as follows：Al
6.3%th, Sn 4.5%, Zr 8.8%, Mo 0.82%, Si 0.3%, Nb 0.87%, W 0.87%, the mass fraction of interpolation 3.5%
TiC and balance of Ti.
5. composite as claimed in claim 1 is it is characterised in that raw material composition components by weight percentage is as follows：Al
7%, Sn 3%, Zr 8%, Mo 0.8%, Si 0.2%, Nb 0.8%, W0.8%, add 2.5% TiB of mass fraction and 2.5%
The TiC of mass fraction and balance of Ti.
6. the heat resistant and wear resistant as described in claim 1-5 damages the preparation method of titanium matrix composite, comprises the following steps that：Step
1st, get the raw materials ready；Step 2, melting are processed；Step 3, ingot casting analysis；Step 4, forging.
7. the heat resistant and wear resistant as described in claim 1-5 damages the preparation method of titanium matrix composite, comprises the following steps that：
Step 1, get the raw materials ready：Weigh titanium sponge, sponge zirconium by weight percentage, the aluminum stannum containing mass fraction 50% stannum and 50% aluminum closes
Gold, granularity is 0.25-3；Aluminium molybdenum alloys containing mass fraction 50% molybdenum and 50% aluminum, granularity is 0.4-4；Containing mass fraction it is
The aluminum niobium alloy of 50% niobium and 50% aluminum, granularity is 0.25-2；Fine aluminium bean, granularity is 6-9, pure tungsten powder, and granularity is 0.4-
1, pure silicon powder, granularity is 125-325, and enhancing phase granularity is 0.01-2；
Step 2, melting：Melting is carried out using vacuum consumable water jacketed copper crucible sensing skull crucible, monitor system is 320-345kW,
Carry out melting, suction to 0.15Pa under vacuum condition, after melting, be incubated 5-8min, holding temperature is not less than melting temperature
1995 DEG C, obtain alloy solution；Sense under the vacuum condition of skull crucible in vacuum consumable water jacketed copper crucible, alloy solution is cast
To in formwork for cylindrical columns, in atmosphere, naturally cool to room temperature, obtain alloy cast ingot；
Step 3, ingot casting analysis：With 20 lathes from alloy cast ingot top, middle part, bottom sampling, use spectroanalysis instrument analytical chemistry
Composition and impurity composition, whether the chemical analysis to analyze ingot casting with this are uniform, the then transformation temperature of analysis of material；
Step 4, forging：By step（1）Detect that qualified alloy of ingot ingot casting preheating is 1050-1100 DEG C to temperature, and at this
At a temperature of keep 45min, forged with 5000t hydraulic press, total deformation ＞ 85% of three draw outs, forging completes.
8. heat resistant and wear resistant as claimed in claim 7 damages titanium matrix composite it is characterised in that described three draw outs
Being specially the first fire pulling deflection is 40%, melts down and is heated to 1100 DEG C, is incubated 30min；Second fire pulling deflection is 30%,
Melt down and be heated to 1075 DEG C, be incubated 30min；3rd fire pulling deflection is 25%, and the total deformation of three draw outs is 85%,
Forging completes.
9. described titanium matrix composite as arbitrary in claim 1-8 is it is characterised in that can apply to temperature is 650 DEG C
In environment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610879434.2A CN106435267B (en) | 2016-10-09 | 2016-10-09 | A kind of heat resistant and wear resistant damage titanium composite material and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610879434.2A CN106435267B (en) | 2016-10-09 | 2016-10-09 | A kind of heat resistant and wear resistant damage titanium composite material and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106435267A true CN106435267A (en) | 2017-02-22 |
| CN106435267B CN106435267B (en) | 2019-03-22 |
Family
ID=58171956
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610879434.2A Expired - Fee Related CN106435267B (en) | 2016-10-09 | 2016-10-09 | A kind of heat resistant and wear resistant damage titanium composite material and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106435267B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108356259A (en) * | 2018-01-31 | 2018-08-03 | 上海交通大学 | A kind of nanometer of aluminum matrix composite powder and preparation method thereof |
| CN109468484A (en) * | 2018-12-25 | 2019-03-15 | 哈尔滨工业大学 | A method of addition zirconium nitride realizes high-temperature titanium alloy complex intensifying |
| CN113388756A (en) * | 2021-06-25 | 2021-09-14 | 哈尔滨工业大学 | Preparation method of multi-element reinforced high-temperature titanium-based composite material |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0931572A (en) * | 1995-07-21 | 1997-02-04 | Sumitomo Metal Ind Ltd | Heat resistant titanium alloy excellent in high temperature fatigue strength |
| CN1752264A (en) * | 2005-09-28 | 2006-03-29 | 哈尔滨工业大学 | In-situ autogenous TiB+TiC/Ti composite material based on Ti-B4C-C series and preparing method thereof |
| CN101392338A (en) * | 2008-11-06 | 2009-03-25 | 上海交通大学 | Composite reinforced high strength and high elastic modulus titanium alloy and preparation method thereof |
| CN104745872A (en) * | 2015-04-22 | 2015-07-01 | 哈尔滨工业大学 | High-temperature titanium alloy applicable to use at temperature of 650 DEG C and preparation method thereof |
-
2016
- 2016-10-09 CN CN201610879434.2A patent/CN106435267B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0931572A (en) * | 1995-07-21 | 1997-02-04 | Sumitomo Metal Ind Ltd | Heat resistant titanium alloy excellent in high temperature fatigue strength |
| CN1752264A (en) * | 2005-09-28 | 2006-03-29 | 哈尔滨工业大学 | In-situ autogenous TiB+TiC/Ti composite material based on Ti-B4C-C series and preparing method thereof |
| CN101392338A (en) * | 2008-11-06 | 2009-03-25 | 上海交通大学 | Composite reinforced high strength and high elastic modulus titanium alloy and preparation method thereof |
| CN104745872A (en) * | 2015-04-22 | 2015-07-01 | 哈尔滨工业大学 | High-temperature titanium alloy applicable to use at temperature of 650 DEG C and preparation method thereof |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108356259A (en) * | 2018-01-31 | 2018-08-03 | 上海交通大学 | A kind of nanometer of aluminum matrix composite powder and preparation method thereof |
| CN109468484A (en) * | 2018-12-25 | 2019-03-15 | 哈尔滨工业大学 | A method of addition zirconium nitride realizes high-temperature titanium alloy complex intensifying |
| CN113388756A (en) * | 2021-06-25 | 2021-09-14 | 哈尔滨工业大学 | Preparation method of multi-element reinforced high-temperature titanium-based composite material |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106435267B (en) | 2019-03-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Verma et al. | High temperature wear in CoCrFeNiCux high entropy alloys: The role of Cu | |
| Ibrahim et al. | On the impact toughness of Al-15 vol.% B4C metal matrix composites | |
| Thomas et al. | Processing and characterization of TiAl-based alloys: Towards an industrial scale | |
| Mathabathe et al. | The vacuum melted ɣ-TiAl (Nb, Cr, Si)-doped alloys and their cyclic oxidation properties | |
| Kumar et al. | Fabrication and characterizations of mechanical properties of Al-4.5% Cu/10TiC composite by in-situ method | |
| US20130199680A1 (en) | Aluminum Die Casting Alloy | |
| Zhao et al. | Microstructure and mechanical properties of titanium alloy/zirconia functionally graded materials prepared by laser additive manufacturing | |
| Dong et al. | Microstructure and dry sliding wear resistance of laser clad TiC reinforced Ti–Ni–Si intermetallic composite coating | |
| Xing et al. | Microstructure and mechanical properties of Sn-9Zn-xAl2O3 nanoparticles (x= 0–1) lead-free solder alloy: first-principles calculation and experimental research | |
| Liu et al. | Microstructure and high-temperature wear and oxidation resistance of laser clad γ/W2C/TiC composite coatings on γ-TiAl intermetallic alloy | |
| CN106435267A (en) | High temperature-resistance and wear-resistance titanium base composite material and preparation method thereof | |
| Nguyen et al. | Influence of nano-alumina and sub-micron copper on mechanical properties of magnesium alloy AZ31 | |
| Lu et al. | Analysis on brazed diamond joints with modified Cu-based filler alloy | |
| JP3229339B2 (en) | Oxidation and corrosion resistant alloy for components used in intermediate temperature range based on added iron aluminide Fe3Al | |
| CN106756237A (en) | A kind of abrasion-resistant titanium basic composite | |
| Ibrahim et al. | Metallurgical parameters controlling matrix/B4C particulate interaction in aluminium–boron carbide metal matrix composites | |
| Chao et al. | Effect of TiO2-doping on the microstructure and the wear properties of laser-clad nickel-based coatings | |
| Gecü et al. | Volume fraction effect of stainless steel on microstructure, interface, corrosion and wear behavior of stainless steel/aluminum bimetal composites | |
| Bharath et al. | Fractographic characterization of Al2O3p particulates reinforced Al2014 alloy composites subjected to tensile loading | |
| Zhang et al. | Growth kinetics and isothermal oxidation behavior of aluminide coatings on Nb–Si based alloy | |
| Long et al. | Research on the corrosion resistance and mechanism of Fe-Cr-Si alloy in molten aluminum | |
| Yong et al. | Mechanism of Zr in in situ-synthesized particle reinforced composite coatings by laser cladding | |
| Abreu-Castillo et al. | In situ processing aluminide coatings with and without tungsten carbide | |
| Liu et al. | Microstructure and dry sliding wear behavior of Fe2TiSi/γ-Fe/Ti5Si3 composite coating fabricated by plasma transferred arc cladding process | |
| Azarmi | Creep properties of nickel aluminide composite materials reinforced with SiC particulates |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190322 |