CN108161346A - A kind of Ti2The preparation method of AlNb/TA15 bimetallic titanium alloy composite hollow structures - Google Patents
A kind of Ti2The preparation method of AlNb/TA15 bimetallic titanium alloy composite hollow structures Download PDFInfo
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- CN108161346A CN108161346A CN201711296229.4A CN201711296229A CN108161346A CN 108161346 A CN108161346 A CN 108161346A CN 201711296229 A CN201711296229 A CN 201711296229A CN 108161346 A CN108161346 A CN 108161346A
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- middle layer
- upper strata
- lamina rara
- rara externa
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/16—Arc welding or cutting making use of shielding gas
- B23K9/173—Arc welding or cutting making use of shielding gas and of a consumable electrode
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/23—Arc welding or cutting taking account of the properties of the materials to be welded
- B23K9/232—Arc welding or cutting taking account of the properties of the materials to be welded of different metals
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
Abstract
The present invention proposes a kind of Ti2The preparation process of AlNb/TA15 bimetallic titanium alloy composite hollow constitutional details, prepared by blank, be surface-treated, only solder flux coating, the connection of superplastic forming/diffusion, cooling come out of the stove and etc. prepare Ti2AlNb/TA15 bimetallic titanium alloy composite hollow structural fin class components.The superplastic forming of dissimilar material hollow-core construction part proposed by the present invention/diffusion connecting process method, breaches Ti2AlNb intermetallic compounds and common alloy of titanium combination prepare key technology prepared by multi-layer hollow structure, make Ti2The high-temperature stability and the good superplasticity of TA15 titanium alloys of AlNb intermetallic compounds are all not fully exerted, and realize structural weight reduction, improve guided missile thrust-weight ratio, pushed Ti2Material application range has been expanded in application of the AlNb intermetallic compounds in model, and improving stock utilization reduces cost.
Description
Technical field
The invention belongs to titanic alloy machining technical fields, and in particular to a kind of Ti2AlNb/TA15 bimetallic titanium alloys are compound
Hollow-core construction preparation method.
Background technology
Trajectory-cruise composite missile (abbreviation composite missile) is that the Long-range precision strike new concept missile of new generation in China is military
Device system, trajectory-cruise composite missile organically blend ballistic and cruise missiles technology.Using " boosting-nothing is dynamic
The novel trajectory of power gliding-dynamic cruise " realizes Long-range precision strike.Composite missile flight front half section is inertia parabola
Type trajectory has the characteristics that the coasting flight of ballistic missile exoatmosphere；Trajectory second half section, guided missile reenter motor-driven cruise in endoatmosphere
Flight, has the characteristics that cruise missile.
The complexity of composite missile rudder aerofoil service condition makes its component development be not only material development and is opened with forming technology
The problem of hair, it is necessary to be considered with complete structural system.Multiple target requirement is realized simultaneously, needed to conventional junction
Innovation on the basis of configuration formula, material selection and forming technology analysis and summary, the material that needs a person with the qualifications of a general, structure design, manufacturing process into
Row very high integrity merges.For rudder aerofoil high temperature lightweight structural material, when long temperature in use requirement 650~750 DEG C it
Between, temperature in use will reach 800 DEG C in short-term.High temperature alloy can be met the requirements in temperature in use, however high temperature alloy is than great,
It is unfavorable for loss of weight.In titanium aluminum series alloy, the Ti based on O phases2AlNb titanium alloys, due to the superstructure of long-range order
Reduce dislocation motion and High temperature diffusion, making it have excellent high-temperature behavior, (specific strength, high-temerature creep drag, resists specific stiffness
Oxidisability, heat resistance, flame retardant property), it can for a long time be used in the range of 700~800 DEG C.Moreover, its density is far below Ni-based
High temperature alloy, thus have become most potential aerospace high-temperature structural material.And Ti2AlNb alloys are due to Nb contents
Height, when hot forming easily aoxidizes, the diffusion activation energy of superplastic deformation complicated mechanism, superstructure is high, superplastic ability and
Switching performance is spread not as good as TA15 and TC4 titanium alloys, at a temperature of 980 DEG C of superplastic forming and 1 × 10-4s-1Under strain rate
Its maximum elongation percentage only has 300% or so, the only 1/3-1/4 of TA15 and TC4 alloys, and flow stress is nearly 5 times of TA15, is led
Cause the Alloy Forming temperature high, forming loading gas pressure is big, and technique is realized extremely difficult.
Ti2AlNb/TA15 bimetallics titanium alloy superplastic forming/diffusion connecting process makes full use of Ti2AlNb based alloys make
The heat safe feature in as outer layer, spreads the excellent and super modeling of switching performance in process also in relation with TA15 alloys
The advantages of property is good, can make shaping window broaden, and sandwich layer design freedom is big, sandwich layer grid can be designed it is more dense, so as to carry
The integral strength and rigidity of high part, simultaneously because TA15 alloy densities are less than Ti2AlNb based alloys can also be realized to a certain degree
Loss of weight.
Secondly, TA15 alloys only have Ti in material cost2The 1/4 of AlNb alloys, this structure type can reduce cost
40% or so.Using Ti2Also forming temperature and gas on-load pressure can be greatly lowered for AlNb/TA15 alloys, will to equipment
It asks low, is conducive to technique realization, furthermore relatively low forming temperature is conducive to the holding of material property, makes material after hot forming
Performance loss is small.
Therefore, carry out Ti2AlNb/TA15 bimetallics titanium alloy superplastic forming/diffusion connecting process research, completes combination and leads
Play the development of lightweight structure, development and Ti to new model2The engineering application of AlNb alloys is of great significance.
Invention content
The purpose of the present invention is to propose to a kind of Ti2AlNb/TA15 bimetallic titanium alloy composite hollow constitutional details preparation side
Method, to solve Ti2Superplasticity is poor in prepared by AlNb alloys multilayered structure, and design freedom is low, and forming temperature is high, forming pressure
Greatly, the problems such as narrow process window.
The technical solution of the present invention：A kind of Ti2AlNb titanium alloy multi-layer hollow structure preparation processes, pass through following step
It is rapid to realize：
The first step, blank prepare,
Upper strata lamina rara externa, upper strata middle layer plate, lower floor's middle layer plate and lower floor's lamina rara externa are obtained by design size requirement blanking；Institute
Stating the first step, lamina rara externa and lower floor's lamina rara externa use Ti at the middle and upper levels2AlNb alloys；Upper strata middle layer plate and lower floor's middle layer plate use
TA15 alloys；
Second step, upper strata lamina rara externa and lower floor's lamina rara externa surface treatment
Upper strata lamina rara externa and lower floor's lamina rara externa are Ti2AlNb intermetallic compounds, acid cleaning process are different from common titanium
Ti is configured in alloy2AlNb intermetallic compound pickles are surface-treated titanium alloy, and pickle uses 65%HNO3, the two
It is pure, the volume proportion 65%HNO of chemistry3:H2O=1：9 pickling times are 30 minutes；
Third walks, setting-out on upper strata middle layer plate or lower floor's middle layer plate, and carries out surface acid-washing processing；Titanium alloy pickling is configured
Liquid is surface-treated titanium alloy, and pickle uses 10%HF and 65%HNO3, the two is that chemistry is pure, and volume proportion is
10%HF:65%HNO3:H2O=1：9：10, pickling time is 15 minutes；
4th step applies on setting-out middle layer plate and stops solder flux；
5th step, group weldering
By upper strata lamina rara externa, upper strata middle layer plate, lower floor's middle layer plate, lower floor's lamina rara externa, totally four laminates stack a group weldering, assembling weldering
Connecing can be realized with argon arc welding, due to Ti2AlNb/TA15 is the difference of the melting welding of dissimilar material, the two material composition and hot physical property
It is different larger, the welding wire close with two kinds of material compositions can be selected when selecting welding wire, grope in the present invention through experiment, find TA1 welderings
Two kinds of welding can be achieved in silk, and weld seam good airproof performance disclosure satisfy that superplastic forming/diffusion connection sealing welding technique for extra is realized；
6th step, shove charge, heat temperature raising
It rear part is got well into soldering and sealing is fitted into mold and position and mold；It heats up after entering stove, sets 945 DEG C of maximum heating temperature,
And in the temperature, make mold fully heated, forcing press should start loading and ensure periphery in the case where rigidly loading at this time
Connection can be spread；On the mold that this pressure should load always, until off-test.
7th step, outer layer bulging,
Make upper strata lamina rara externa and lower lamina rara externa expansive forming pad pasting in outer layer applying argon gas bulging；Simultaneously make upper strata middle layer plate and
Lower floor's middle layer plate realizes diffusion connection, the full admission pressure 2.0MPa of outer layer, 120 minutes dwell times.
8th step, internal layer air inlet bulging；
Upper strata middle layer plate and lower floor's middle layer plate is made to realize superplastic forming, and outside final and upper strata in internal layer applying argon gas bulging
Laminate and lower lamina rara externa realize diffusion connection.The full admission pressure 2.5MPa of internal layer, feed rate 0.1MPa/10min, pressurize
150 minutes time.
9th step, comes out of the stove,
Cool down after internal layer air inlet, obtain Ti2AlNb/TA15 bimetallic titanium alloy multi-layer hollow structures.
The advantageous effect of the present invention compared with prior art：
The present invention provides a kind of suitable for Ti2The multi-layer hollow structure preparation process of AlNb titanium alloys.Ti2AlNb based alloys
Its superplastic forming temperature is up to 980 DEG C, and its superplasticity is low, and flow stress is high, which is carrying out superplastic forming/diffusion company
When connecing technique, process window is narrow, and forming technology is difficult to control, and relatively low material elongation percentage can also cause multi-layer hollow structural core
Layer design freedom also very little.
Ti2AlNb/TA15 bimetallics titanium alloy superplastic forming/diffusion connecting process makes full use of Ti2AlNb based alloys make
The heat safe feature in as outer layer, spreads the excellent and super modeling of switching performance in process also in relation with TA15 alloys
The advantages of property is good, can make shaping window broaden, and sandwich layer design freedom is big, sandwich layer grid can be designed it is more dense, so as to carry
The integral strength and rigidity of high part, simultaneously because TA15 alloy densities are less than Ti2AlNb based alloys can also be realized to a certain degree
Loss of weight.
Secondly, TA15 alloys only have Ti in material cost2The 1/4 of AlNb alloys, this structure type can reduce cost
40% or so.Using Ti2Also forming temperature and gas on-load pressure can be greatly lowered for AlNb/TA15 alloys, will to equipment
It asks low, is conducive to technique realization, furthermore relatively low forming temperature is conducive to the holding of material property, makes material after hot forming
Performance loss is small.
Description of the drawings
Totally 6 width attached drawing of the invention
For sandwich layer setting-out of the present invention and only, solder flux coats schematic diagram to Fig. 1；
Fig. 2 spreads connection diagram for the outer layer superplastic forming and sandwich layer and outer layer of the present invention；
Fig. 3 is the outer layer superplastic forming process schematic of the present invention；
Fig. 4 is formation of parts schematic diagram of the present invention；
Fig. 5 is flow chart of the present invention；
Fig. 6 is structure type figure of the present invention；
Specific embodiment
The present invention is described in detail with reference to the accompanying drawings and embodiments.
Embodiment 1
The material that the present embodiment uses is Ti2AlNb alloys 5 and TA15 alloys 6.
The present invention by following steps as shown in figure 5, realized：
1st, the preparation of blank
(1) prepare upper strata middle layer plate 2, lower floor's middle layer plate 3 and lamina rara externa 1 and lower floor with modes such as wire cutting or laser cuttings
4 four laminate material of lamina rara externa.
2. blank setting-out, surface treatment
(1) setting-out on up or down layer middle layer plate 2,3.
(2) four layers of blank are surface-treated, acid cleaning process can be used for surface treatment or the mode of mechanical grinding is gone
It descales.
(3) coating stops solder flux on the core plate for finish line, and reserved gas channel t2, gas channel t2 width is left for 3mm
It is right.
3. seal welding
(1) by surface treated lamina rara externa 1,4 and the performing member assembling of surface treatment core plate；
(2) argon arc welding seals after four laminate bases are fixed, and welds core plate air inlet pipe and lamina rara externa air inlet pipe (such as Fig. 2
It is shown)；
(3) it hunts leak after soldering and sealing, it is ensured that air tight, do not collaborate.
4. molding, shove charge heating
(1) welding air inlet pipe and blank and superplastic forming die are fitted into superplastic forming equipment together, heat temperature raising, and
Internal lamina rara externa vacuumizes simultaneously, is heated to 945 ± 5 DEG C and keeps the temperature 60 minutes,
(2) outer layer air inlet
After the loading of press machine, outer layer is vacuumized into state and is switched to air-suction state, outer layer air inlet to maximum gas pressure 2.0Mpa,
Outer layer expansive forming is made to paste mould (as shown in Figure 4), outer layer air inlet can be completed, and maximum gas pressure 120 is kept to divide at 5~10 minutes
Clock.
(5) internal layer air inlet
After outer layer air inlet, internal layer air inlet is switched to, internal layer feed rate must be carried out slowly, and feed rate is no more than
0.1Mpa/10 minutes, too fast feed rate can lead to core plate deformation fracture.Full admission pressure can reach 2.5Mpa, pressurize
150 minutes time, obtained end article such as Fig. 5, shown in Fig. 6.
Claims (1)
1. a kind of Ti2The preparation method of AlNb/TA15 bimetallic titanium alloy composite hollow structures, which is characterized in that pass through following step
It is rapid to realize：
The first step, blank prepare,
Upper strata lamina rara externa (1), upper strata middle layer plate (2), lower floor's middle layer plate (3) and lower floor's outer layer are obtained by design size requirement blanking
Plate (4)；Lamina rara externa (1) and lower floor's lamina rara externa (4) use Ti to the first step at the middle and upper levels2AlNb alloys；Upper strata middle layer plate (2)
With lower floor's middle layer plate (3) using TA15 alloys；
Second step, upper strata lamina rara externa (1) and lower floor's lamina rara externa (4) surface treatment
Ti is configured2AlNb intermetallic compound pickles are surface-treated titanium alloy, and pickle uses 65%HNO3, the two
It is pure, the volume proportion 65%HNO of chemistry3:H2O=1：9 pickling times are 30 minutes；
Third walks, setting-out on upper strata middle layer plate (2) or lower floor's middle layer plate (3), and carries out surface acid-washing processing；Titanium alloy acid is configured
Washing lotion is surface-treated titanium alloy, and pickle uses 10%HF and 65%HNO3, the two is chemical pure, volume proportion
For 10%HF：65%HNO3：H2O=1：9：10, pickling time is 15 minutes；
4th step applies on setting-out middle layer plate and stops solder flux；
5th step, group weldering
By upper strata lamina rara externa (1), upper strata middle layer plate (2), lower floor's middle layer plate (3), lower floor's lamina rara externa (4), totally four laminates stack group
Weldering, assembly welding argon arc welding select TA1 welding wires；
6th step, shove charge, heat temperature raising
It rear part is got well into soldering and sealing is fitted into mold and position and mold；It heats up after entering stove, 945 DEG C of maximum heating temperature of setting, and
The temperature makes mold fully heated, and forcing press should start loading and ensure that periphery can in the case where rigidly loading at this time
Diffusion connection；On the mold that this pressure should load always, until off-test；
7th step, outer layer bulging,
Make upper strata lamina rara externa (1) and lower lamina rara externa (4) expansive forming pad pasting in outer layer applying argon gas bulging；Make upper strata middle layer plate simultaneously
(2) and lower floor's middle layer plate (3) realizes diffusion connection, the full admission pressure 2.0MPa of outer layer, 120 minutes dwell times；
8th step, internal layer air inlet bulging；
Upper strata middle layer plate (2) and lower floor's middle layer plate (3) is made to realize superplastic forming, and final and upper strata in internal layer applying argon gas bulging
Lamina rara externa (1) and lower lamina rara externa (4) realize diffusion connection, full admission the pressure 2.5MPa, feed rate 0.1MPa/ of internal layer
10min, 150 minutes dwell times；
9th step, comes out of the stove,
Cool down after internal layer air inlet, obtain Ti2AlNb/TA15 bimetallic titanium alloy multi-layer hollow structures.
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Cited By (11)
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|---|---|---|---|---|
| CN109226952A (en) * | 2018-10-15 | 2019-01-18 | 中国航空制造技术研究院 | Hollow structure manufacturing process |
| CN109435413A (en) * | 2018-10-23 | 2019-03-08 | 北京航空航天大学 | A kind of integrated method of joint forming of dissimilar metal laminate |
| CN109955041A (en) * | 2019-03-28 | 2019-07-02 | 中国航空制造技术研究院 | Titanium alloy hollow structure without molding Preparation Method |
| CN110480279A (en) * | 2019-09-02 | 2019-11-22 | 北京星航机电装备有限公司 | A kind of titanium alloy change hollow active cooling cabin preparation method of wall thickness |
| CN111069860A (en) * | 2019-12-31 | 2020-04-28 | 航天海鹰(哈尔滨)钛业有限公司 | Preparation method of high-temperature alloy four-layer lattice lightweight structure |
| CN111604645A (en) * | 2020-05-23 | 2020-09-01 | 北京普惠三航科技有限公司 | Forming method of air inlet pipe of aircraft engine |
| CN111790984A (en) * | 2020-09-01 | 2020-10-20 | 哈尔滨工业大学 | Preparation method of dissimilar titanium alloy composite part based on laser welding and laser material increase |
| CN111805170A (en) * | 2020-05-27 | 2020-10-23 | 南京航空航天大学 | Method for forming hollow lattice structure with built-in foamed aluminum |
| CN112846643A (en) * | 2020-12-08 | 2021-05-28 | 北京星航机电装备有限公司 | Forming method and forming device for titanium alloy thin-wall hollow structure |
| CN112975286A (en) * | 2021-02-23 | 2021-06-18 | 哈尔滨工业大学 | Friction stir welding/superplastic forming method for magnesium alloy and aluminum alloy multilayer structure |
| CN113428342A (en) * | 2021-04-25 | 2021-09-24 | 北京星航机电装备有限公司 | Multifunctional aluminum alloy hollow structure wallboard and forming preparation method thereof |
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| CN109226952A (en) * | 2018-10-15 | 2019-01-18 | 中国航空制造技术研究院 | Hollow structure manufacturing process |
| CN109435413A (en) * | 2018-10-23 | 2019-03-08 | 北京航空航天大学 | A kind of integrated method of joint forming of dissimilar metal laminate |
| CN109955041A (en) * | 2019-03-28 | 2019-07-02 | 中国航空制造技术研究院 | Titanium alloy hollow structure without molding Preparation Method |
| CN110480279A (en) * | 2019-09-02 | 2019-11-22 | 北京星航机电装备有限公司 | A kind of titanium alloy change hollow active cooling cabin preparation method of wall thickness |
| CN110480279B (en) * | 2019-09-02 | 2020-07-28 | 北京星航机电装备有限公司 | Preparation method of titanium alloy variable-wall-thickness hollow active cooling cabin |
| CN111069860B (en) * | 2019-12-31 | 2022-10-25 | 航天海鹰(哈尔滨)钛业有限公司 | Preparation method of high-temperature alloy four-layer lattice lightweight structure |
| CN111069860A (en) * | 2019-12-31 | 2020-04-28 | 航天海鹰(哈尔滨)钛业有限公司 | Preparation method of high-temperature alloy four-layer lattice lightweight structure |
| CN111604645A (en) * | 2020-05-23 | 2020-09-01 | 北京普惠三航科技有限公司 | Forming method of air inlet pipe of aircraft engine |
| CN111805170A (en) * | 2020-05-27 | 2020-10-23 | 南京航空航天大学 | Method for forming hollow lattice structure with built-in foamed aluminum |
| CN111790984A (en) * | 2020-09-01 | 2020-10-20 | 哈尔滨工业大学 | Preparation method of dissimilar titanium alloy composite part based on laser welding and laser material increase |
| CN112846643A (en) * | 2020-12-08 | 2021-05-28 | 北京星航机电装备有限公司 | Forming method and forming device for titanium alloy thin-wall hollow structure |
| CN112975286A (en) * | 2021-02-23 | 2021-06-18 | 哈尔滨工业大学 | Friction stir welding/superplastic forming method for magnesium alloy and aluminum alloy multilayer structure |
| CN113428342A (en) * | 2021-04-25 | 2021-09-24 | 北京星航机电装备有限公司 | Multifunctional aluminum alloy hollow structure wallboard and forming preparation method thereof |
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