CN110000246A - A kind of large-scale complex thin-wall titanium alloy covering part stress relaxation straightening method in short-term - Google Patents
A kind of large-scale complex thin-wall titanium alloy covering part stress relaxation straightening method in short-term Download PDFInfo
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- CN110000246A CN110000246A CN201910171094.1A CN201910171094A CN110000246A CN 110000246 A CN110000246 A CN 110000246A CN 201910171094 A CN201910171094 A CN 201910171094A CN 110000246 A CN110000246 A CN 110000246A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D1/00—Straightening, restoring form or removing local distortions of sheet metal or specific articles made therefrom; Stretching sheet metal combined with rolling
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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Abstract
The invention discloses a kind of large-scale complex thin-wall titanium alloy covering part stress relaxation straightening methods in short-term, belong to sheet metal hot sizing technology field, while this method is by establishing stress relaxation equation, go out Creep Equation function by stress relaxation equation inference, analogue simulation is carried out to blank hot forming again, forming temperature is primarily determined according to the deflection after titanium alloy plate hot forming, primary stress condition and stress relaxation time, according to the relaxed stress value in stress relaxation gentle stage, a small amount of elastic stage compensation rate is added in mold design, titanium-alloy sheet metal heat forming technology is carried out afterwards, finally shape part with high accuracy；The rebound in forming process effectively can be reduced using method of the invention with maximum degree, reduce the internal stress of part after forming, obtain more accurate titanium-alloy sheet metal in the shortest possible time, improve the production efficiency of product, reduce production cost.
Description
Technical field
The invention belongs to metal plate or pipes, stick or profile substantially without machining or process field, be related to a kind of metal
Plate hot sizing technique more particularly to a kind of large-scale complex thin-wall titanium alloy covering part stress relaxation straightening method in short-term.
Background technique
The performance indicators such as the development Flight Vehicle Structure rigidity with aircraft industry are continuously improved, and want to the military service of aeronautical material
Ask increasingly harsh.In order to improve the flying quality of aircraft as far as possible, it is necessary to be continuously improved aircraft parts material specific strength and
Specific stiffness.Titanium alloy possesses the characteristic of high-strength light, is one of ideal advanced aircraft material.Especially for advanced superb
For the aircraft of velocity of sound, material is other than specific strength to be guaranteed and specific stiffness, it is necessary to consider material high temperature resistant, it is corrosion-resistant
Etc. characteristics.It is continually striving to have developed some high-temperature titanium alloy materials for this purpose, researchers both domestic and external pass through, and has succeeded
It is applied on aerospace industry.Due to being difficult under the room temperature of titanium alloy, titanium alloy metal plate zero in aircraft industry
Part mostly uses hot formed method to be manufactured.
Straightening method based on stress relaxation is at normal temperature to be fixed part by fixture clamping, and reach part deformation
To design requirement, part and fixture are then heated to stress relaxation temperature together, are answered using material is internal under Elevated Temperature Conditions
Power increases at any time and reduces, and the characteristic that elastic deformation is plastic deformation is obtained the high part of dimensional accuracy.In stress
Loose initial stage, sheet metal deformation are just completed, and there are residual stress for inside, and with loose generation, under stress level is continuous
Drop tends towards stability until reaching Relaxation Limit.Currently, there are many domestic and foreign scholars to high-temperature titanium alloy stress relaxation behavior into
It has gone research, but has been applied to still remain the problem of forming efficiency is lower, and dimensional accuracy is difficult to ensure when hot forming.
In the prior art, a kind of titanium-alloy sheet metal forming and machining method is proposed in CN103990664A, using titanium
Alloy material stress relaxation and enter creep state at a temperature of when, processing is formed by heat-insulation pressure keeping certain time,
The forming that high quality and high stability are carried out to titanium-alloy sheet metal is realized in success, but there is no research initial strains
And initial load is on the hot formed influence of titanium alloy.
A kind of hot combined shaping method for numerical simulation of titanium alloy is provided in CN103886125A, it is single by being carried out to material
To stretching and stress relaxation experiment, establishes constitutive equation and simulated for hot-stretch deformation simulation, pass through the numerical value meter to rebound
It calculates and analysis optimization slack time, rebound greatly reduces, reach Accurate Shaping, but due to the precision problem of finite element modelling,
Difference is shaped with practical.
Summary of the invention
The present invention discloses a kind of large-scale complex thin-wall titanium alloy covering part in short-term aiming at the problems existing in the prior art
Stress relaxation straightening method while this method is by establishing stress relaxation equation, goes out creep by stress relaxation equation inference
Constitutive equation function reduces the rebound in forming process with maximum degree, the internal stress of part after forming is reduced, in practical life
The production efficiency that product is improved during producing, reduces production cost, solves problems of the prior art.
The present invention is implemented as follows:
A kind of large-scale complex thin-wall titanium alloy covering part stress relaxation straightening method in short-term, which is characterized in that steps are as follows:
Step 1: carrying out short time high temperature stress relaxation test to titanium alloy plate, obtain certain titanium alloy in different temperatures and
Stress relaxation curve under different primary condition；
Step 2: by origin Software on Drawing titanium alloy this structure curve, fitting obtains the stress relaxation under different parameters
Equation；
Step 3: Creep Equation function is gone out by stress relaxation equation inference；Gone out by stress relaxation equation inference
Creep Equation function, so as in the simulation softwares such as subsequent importing ABAQUS；
Step 4: blank and mold former are imported in simulation software, and added material density, elasticity modulus, Poisson's ratio,
Plastic stage stress-strain diagram and Creep Equation carry out analogue simulation to blank hot forming；Blank hot forming is imitated
True simulation makees reference frame for the selection of actual production technological parameter；
Step 5: according to the deflection after titanium alloy plate hot forming primarily determine forming temperature, primary stress condition and
Stress relaxation time；
Step 6: according to the relaxed stress value in stress relaxation gentle stage, elastic stage compensation is added in mold design
Amount increases the strain value that mold occurs under the stress and hot environment are as follows:
Wherein: ε is the logarithmic strain of elastic stage, and σ is the true stress of elastic stage, and E is elasticity modulus.
Step 7: in a mold to titanium alloy plate blank spraying high temperature antioxidant and by its clamping, heat is placed into
Carry out in forming machine tool with stove heating, when temperature reaches the forming temperature of design, start to carry out heat preservation forming, when blank pressure maintaining extremely
The stress relaxation time of design stops pressurization；
Step 8: stopping heating, after mold and part are cooling, opens hot forming lathe, takes out titanium alloy component, measurement
Springback angle size, fine tuning forming temperature, primary stress condition and stress relaxation time；
Step 9: repeat the above steps four and step 5, according to specific demand, show that meeting product quality requires most
Good hot forming parameter, finally shapes part with high accuracy.
Further, different ginsengs are obtained using secondary decaying exponential function fitting shown in formula (1) in the step two
Stress relaxation equation under several:
Wherein σ is instantaneous residual stress；σrFor stress relaxation limit；B, c and τ1, τ2For Material Relaxation constant；T is relaxation
Time.
Further, the step three is specially to be carried out using hyperbolic sine function shown in formula (2) to stress data
Fitting obtains creep constitutive model:
Wherein T is creep process temperature, and unit K, Q is creep activity energy, and unit K J/mol*K, R are gas constant, A, B
It is material creep constant with n.
Further, the simulation software is ABAQUS simulation software, but is not limited to ABAQUS simulation software.
Further, the high-temp antioxidizing agent is boron nitride.
Further, the dimensioned area of the titanium alloy is greater than 1m2, wall thickness is less than 3mm, especially for 1mm~1.5mm's
Large-scale complex thin-wall sheet metal part.
Further, the titanium alloy be TA32 titanium alloy plate, the TA32 titanium alloy plate it is best at parameter
Number: forming temperature is 775~800 DEG C, and primary stress condition is 175~200MPa, and stress relaxation time is 1100~1300s.
The beneficial effect of the present invention and the prior art is:
The present invention obtains the stress relaxation side under different parameters by origin Software on Drawing titanium alloy this structure curve, fitting
Journey, then Creep Equation function is gone out by stress relaxation equation inference, by establishing the more efficient reliable pine of stress in short-term
While relaxation equation, the exact correlation of creep and stress relaxation is characterized, the rebound in forming process, drop are reduced with maximum degree
The internal stress of part after low forming, obtains that performance is good in the shortest possible time, and the high large-scale complex thin-wall titanium alloy of dimensional accuracy covers
Leather goods；
Large-scale titanium alloy sheet metal part heat forming technology is carried out using the present invention, can effectively be subtracted with maximum degree
Rebound in small forming process reduces the internal stress of part after forming, obtains more accurate titanium alloy metal plate in the shortest possible time
Metal parts improve the production efficiency of product, reduce production cost.
Detailed description of the invention
Fig. 1 is large-scale complex thin-wall titanium alloy covering part stress relaxation straightening method flow chart in short-term；
Fig. 2 is titanium-alloy sheet metal hot forming schematic diagram；
Fig. 3 is large-scale complex thin-wall titanium alloy covering exemplar figure；
Fig. 4 is the stress relaxation curve under TA32 titanium alloy different condition, wherein (a) is initial load 100MPa stress pine
Relaxation curve (b) is initial load 150MPa stress relaxation curve, (c) is initial load 200MPa stress relaxation curve.
Specific embodiment
It is clear to keep the purpose of the present invention, technical solution and effect clearer, example is exemplified below to the present invention into one
Step is described in detail.It should be understood that specific implementation described herein is not intended to limit the present invention only to explain the present invention.
As shown in FIG. 1, FIG. 1 is large-scale complex thin-wall titanium alloy covering part stress relaxation straightening method flow chart in short-term, this
Invention is using TA32 titanium alloy plate as example, the specific steps are as follows:
(1) TA32 titanium alloy plate is selected, it, will according to national standard GB/T10120-2013 metal stresses relaxation test method
Test sample is made in TA32 titanium alloy plate, carries out short time high temperature stress pine according to specified experimental program on universal testing machine
Relax the stress relaxation curve for testing and obtaining TA32 titanium alloy under different temperatures and different primary condition；
(2) stress relaxation curve for passing through origin Software on Drawing TA32 titanium alloy, as shown in figure 4, using following formula
(1) secondary decaying exponential function fitting, obtains the stress relaxation equation under different parameters, the stress of different primary stress shown in
Shown in relaxation equation coefficient such as table (1)；
Wherein σ is instantaneous residual stress；σrFor stress relaxation limit；B, c and τ1, τ2For Material Relaxation constant；T is relaxation
Time.
The stress relaxation equation coefficient of the different primary stress of table 1
(3) stress data is fitted to obtain using (or power exponential function) shown in hyperbolic sine function such as formula (2)
Creep constitutive model.
Wherein T is creep process temperature (unit K), and Q is creep activity energy (unit K J/ (mol*K)), and R is gas constant,
A, B and n is material creep constant.Shown in the parameter for the Creep Equation that each experiment condition obtains after fitting such as table (2).
The different stress level Creep Equation coefficients of table 2
(4) blank and mold former are imported in ABAQUS simulation software, and adds relevant material parameters and creep side
Journey, carries out analogue simulation to blank hot forming, makees reference frame for the selection of actual production technological parameter；
(5) suitable forming temperature 750~825 is primarily determined according to the deflection after TA32 titanium alloy plate hot forming
DEG C, primary stress 100~200MPa of condition, 1000~1400s of stress relaxation time；
(6) according to the relaxed stress value in stress relaxation gentle stage, a small amount of elastic stage is added in mold design and mends
The amount of repaying, flexible deformation can be indicated with formula (3) and (increase the strain value that mold occurs under the stress and hot environment)；
Wherein, ε is the logarithmic strain of elastic stage, and σ is the true stress of elastic stage, and E is elasticity modulus.
(7) as shown in Fig. 2, spraying boron nitride to titanium alloy plate blank, and by its clamping in designed mold,
It places into hot forming lathe and carries out with stove heating, when temperature reaches the forming temperature of design, start to carry out heat preservation forming, work as hair
Base pressure maintaining stops pressurization to the stress relaxation time (carrying out pressure maintaining school shape to part) of design；
(8) stop heating, after mold and part are cooling, open hot forming lathe, take out titanium alloy component, measurement rebound
Angle size, fine tuning forming temperature, primary stress condition and stress relaxation time；
(9) step 4) and step 5) are repeated, best hot forming parameter is obtained out, forming temperature is 775~800 DEG C, initially
Stress condition is 175~200MPa, and stress relaxation time is 1100~1300s, finally shapes pad pasting degree and reaches 0.2mm or less
High-precision part.
The drip molding that method of the invention is directed to is large-scale complex thin-wall titanium alloy covering part as shown in Figure 3, size
Area is greater than 1m2, wall thickness is less than 3mm, especially for the large-scale complex thin-wall sheet metal part of 1mm~1.5mm.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the principle of the present invention, several improvement can also be made, these improvement also should be regarded as of the invention
Protection scope.
Claims (7)
1. a kind of large-scale complex thin-wall titanium alloy covering part stress relaxation straightening method in short-term, which is characterized in that steps are as follows:
Step 1: short time high temperature stress relaxation test is carried out to titanium alloy plate, obtains certain titanium alloy in different temperatures and difference
Stress relaxation curve under primary condition；
Step 2: by origin Software on Drawing titanium alloy this structure curve, fitting obtains the stress relaxation equation under different parameters；
Step 3: Creep Equation function is gone out by stress relaxation equation inference；
Step 4: blank and mold former are imported in simulation software, and added material density, elasticity modulus, Poisson's ratio, plasticity
Stage stress-strain diagram and Creep Equation carry out analogue simulation to blank hot forming；
Step 5: forming temperature, primary stress condition and stress are primarily determined according to the deflection after titanium alloy plate hot forming
Slack time；
Step 6: according to the relaxed stress value in stress relaxation gentle stage, elastic stage compensation rate is added in mold design, increases
The strain value for adding mold to occur under the stress and hot environment are as follows:
Wherein, ε is the logarithmic strain of elastic stage, and σ is the true stress of elastic stage, and E is elasticity modulus；
Step 7: in a mold to titanium alloy plate blank spraying high temperature antioxidant and by its clamping, hot forming is placed into
It carries out in lathe with stove heating, when temperature reaches the forming temperature of design, starts to carry out heat preservation forming, when blank pressure maintaining is to designing
Stress relaxation time, stop pressurization；
Step 8: stopping heating, after mold and part are cooling, opens hot forming lathe, takes out titanium alloy component, measurement rebound
Angle size, fine tuning forming temperature, primary stress condition and stress relaxation time；
Step 9: repeat the above steps four and step 5, obtains best hot forming parameter, finally shapes part with high accuracy.
2. a kind of large-scale complex thin-wall titanium alloy covering part according to claim 1 stress relaxation straightening method in short-term,
It is characterized in that, using secondary decaying exponential function fitting shown in formula (1) in the step two, obtains under different parameters
Stress relaxation equation:
Wherein σ is instantaneous residual stress；σrFor stress relaxation limit；B, c and τ1, τ2For Material Relaxation constant；T is slack time.
3. a kind of large-scale complex thin-wall titanium alloy covering part according to claim 1 stress relaxation straightening method in short-term,
It is characterized in that, the step three is specially to be fitted using hyperbolic sine function shown in formula (2) to stress data
To creep constitutive model:
Wherein T is creep process temperature, and unit K, Q is creep activity energy, and unit K J/mol*K, R are gas constant, and A, B and n are
Material creep constant.
4. a kind of large-scale complex thin-wall titanium alloy covering part according to claim 1 stress relaxation straightening method in short-term,
It is characterized in that, the simulation software is ABAQUS simulation software.
5. a kind of large-scale complex thin-wall titanium alloy covering part according to claim 1 stress relaxation straightening method in short-term,
It is characterized in that, the high-temp antioxidizing agent is boron nitride.
6. a kind of large-scale complex thin-wall titanium alloy covering part according to claim 1 stress relaxation straightening method in short-term,
It is characterized in that, the dimensioned area of the titanium alloy is greater than 1m2, wall thickness is less than 3mm.
7. a kind of large-scale complex thin-wall titanium alloy covering part according to claim 6 stress relaxation straightening method in short-term,
It is characterized in that, the titanium alloy is TA32 titanium alloy plate, the best forming parameter of the TA32 titanium alloy plate: forming
Temperature is 775~800 DEG C, and primary stress condition is 175~200MPa, and stress relaxation time is 1100~1300s.
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| CN113102868A (en) * | 2021-04-20 | 2021-07-13 | 中国直升机设计研究所 | Helicopter main nozzle lobe machining method |
| CN113343381A (en) * | 2021-05-31 | 2021-09-03 | 上海交通大学 | Analysis method for influence rule of reduction rate on springback in inner and outer tooth thin-wall part profile rolling |
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| CN113343381B (en) * | 2021-05-31 | 2023-03-14 | 上海交通大学 | Analysis method for influence rule of reduction rate on springback in inner and outer tooth thin-wall part type rolling |
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Application publication date: 20190712 |