CN104561869B - A kind of titanium alloy profile stretch wrap forming situ heat treatment method - Google Patents
A kind of titanium alloy profile stretch wrap forming situ heat treatment method Download PDFInfo
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- CN104561869B CN104561869B CN201410827568.0A CN201410827568A CN104561869B CN 104561869 B CN104561869 B CN 104561869B CN 201410827568 A CN201410827568 A CN 201410827568A CN 104561869 B CN104561869 B CN 104561869B
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Abstract
The present invention relates to a kind of titanium alloy profile stretch wrap forming situ heat treatment method, including: at the anti-oxidation ceramic coating of sectional material blank surface smear；Samming stove is made to be warming up to the first temperature；By fixed component, section bar two ends are fixed；Heating section bar, temperature rises to the first temperature, according to fixed component movement locus on stretch bending mold, is shaped to stretch bending paste mould, and keeps the benefit amount of drawing during stretch wrap forming constant；Heating further to section bar, is warming up to the second temperature, and makes the temperature of section bar stablize at the second temperature allowed range in solution time section；By pattern and described stretch bending mold matched moulds, in making section bar cavity after pattern with stretch bending mold matched moulds, it is in mould constraint state；Carry out section bar forcing Cooling Quenching to room temperature；The temperature of regulation samming stove is the 3rd temperature；When keeping the benefit amount of drawing constant, by the section bar homoiothermic in cavity to the 3rd temperature, after reaching aging time section, the section bar in cavity naturally cools to room temperature.
Description
Technical field
The present invention relates to metal forming processing technique field, particularly to a kind of titanium alloy profile stretch wrap forming situ heat treatment method.
Background technology
Section bar part is the important feature part constituting aircraft primary load bearing framework, its forming quality is directly connected to the assembly precision of aircraft, complete machine aerodynamic configuration, service life, become and affect aircraft development and ensure the key problem in technology of aircraft entirety military service performance, be also one of principal element affecting aircraft manufacturing cycle, cost and benefit.
Existing conventional section bar part forming technology be described below:
1, section bar electric heating stretch wrap forming technology
Titanium alloy plasticity at ambient temperature is poor, makes its plasticity increase by promoting temperature, uses from hindering heating means, make section bar conducting self-heating by low-voltage, high-current, be one of the important of titanium alloy profile stretch wrap forming and effective measures.Titanium alloy profile electric heating stretch wrap forming technique is to utilize the characteristic that titanium alloy heat conductivility is low, resistance coefficient is big, bigger electric current is continued through in sectional material blank bending forming process, the Joule heat utilizing this section of sectional material blank self-resistance to produce heats, and is heated to forming temperature the technique of charged stretch wrap forming.Can preferably solve the technological difficulties that titanium alloy profile temperature-room type plasticity difference difficulty shapes, can be widely applied to the bending forming of the constitutional details such as military battlebus, ships used for military purposes, carry-on frame, edge strip.Domestic begin one's study from resistance heating stretch wrap forming technology in the nineties, use process route predominantly: blank electrified regulation, to temperature power-off, stretching+stretch bending+stretching, hot school shape, unloading.CyrilBath company of the U.S. is the demand meeting Boeing's composite fuselage titanium alloy grid beam part, develops titanium alloy electric heating stretch bending equipment cooperatively with RTI Internat Metals Inc. of titanium alloy manufacturer, obtains practical engineering application on Boeing 787 aircraft.
2, titanium alloy profile is from resistance heating stretch wrap forming and thermal creep technology
The patent application document of Application No. 201210303645.3 discloses a kind of section bar hot-drawn curved creep combined shaping system and using method thereof.Use and from resistance heating system, section bar is heated, until section bar temperature reaches default stretch wrap forming temperature value, through prestretching, it is coated with, mends and be pulled through journey and complete stretch wrap forming, then use the hot tank that adds being installed on stretch benders platform to make section bar keep creep temperature, complete creep process.
Technique scheme is in practice, and technique experiences repeatedly thermal cycle, easily causes section bar intensity less than mother metal, it is difficult to meet performance requirement.According to the technique that after titanium alloy profile electric heating stretch wrap forming, heat treatment improves intensity in heating furnace again, for preventing heat treatment deformation, part after section bar electric heating stretch wrap forming needs to be clamped by complicated special fixture, frock must also be able to provide huge mold clamping force, heat treatment is carried out in fixture is placed on together with part heating furnace, complex technical process, and special tooling is complicated and is only provided that clamping pressure, Deformation control DeGrain.
Summary of the invention
For solving problem of the prior art, the present invention proposes a kind of titanium alloy profile stretch wrap forming situ heat treatment method, the problem that solution actual production medium section patch mould difficulty and intensity reduce.By the way of from resistance heating, carrying out titanium alloy profile stretch wrap forming in stretch bending mold, during solution hardening, section bar is still in stretch bending mold.Under samming stove assists, regulate and control titanium alloy profile intensity by ageing strengthening after Cooling Quenching, make the part of acquisition reach performance requirement.
For achieving the above object, the invention provides a kind of titanium alloy profile stretch wrap forming situ heat treatment method, the method includes:
At the anti-oxidation ceramic coating of sectional material blank surface smear；
Open samming stove, make described samming stove be warming up to the first temperature；
By fixed component, section bar two ends are fixed；
Heating section bar, temperature rises to the first temperature, under the effect of described samming stove, makes the temperature stabilization of section bar at the first temperature allowed range；
In the first temperature allowed range, according to fixed component movement locus on stretch bending mold, stretch bending is shaped to paste mould, and it is constant to keep mending the amount of drawing during stretch wrap forming；
Protective gas is inputted so that the bringing-up section of section bar is under gas shield state at described stretch bending mold end；
Heating further to section bar, is warming up to the second temperature, and makes the temperature of section bar stablize at the second temperature allowed range in solution time section；
In the second temperature allowed range, by pattern and described stretch bending mold matched moulds；
After solid solution completes, carry out section bar forcing Cooling Quenching to room temperature, in quenching process, in making section bar cavity after pattern with stretch bending mold matched moulds, be in mould constraint state；Meanwhile, protective gas is closed；
The temperature of regulation samming stove is the 3rd temperature；
When keeping mending the amount of drawing, by the section bar homoiothermic in cavity to the 3rd temperature, under the effect of described samming stove, the temperature making section bar is stable at the 3rd temperature allowed range in aging time section；
After reaching aging time section, the section bar in cavity naturally cools to room temperature, it is thus achieved that titanium alloy profile part.
Preferably, the method also included before the step that temperature is the 3rd temperature of described regulation samming stove:
Heating the section bar in cavity, temperature rises to the first temperature, in the first temperature allowed range, type part is carried out benefit and draws；Meanwhile, keep mending deflection when drawing constant.
Preferably, described first temperature in the range of: 500 DEG C～700 DEG C.
Preferably, described second temperature is in the range of 920 DEG C～950 DEG C.
Preferably, described 3rd temperature is in the range of 480 DEG C～600 DEG C.
Preferably, the method for described intensification is that electric current is from hindering heating.
Preferably, described fixed component is clamp.
Technique scheme has the advantages that the technical program, compared with former technique, in terms of frock angle, prevents the special tooling mould that heat treatment deformation uses, improves the efficiency of heating surface of section bar itself, improve capacity usage ratio in decreasing heating furnace；Section bar part aspect, not only ensure that forming accuracy but also regulated and controled performance.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, the accompanying drawing used required in embodiment or description of the prior art will be briefly described below, apparently, accompanying drawing in describing below is only some embodiments of the present invention, for those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is one of a kind of titanium alloy profile stretch wrap forming of proposing of the present invention situ heat treatment method flow diagram；
Fig. 2 is a kind of titanium alloy profile stretch wrap forming the two of situ heat treatment method flow diagram that the present invention proposes；
Fig. 3 is the titanium alloy profile solid solution schematic diagram of the present embodiment；
Fig. 4 cools down schematic diagram for the present embodiment titanium alloy profile.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is only a part of embodiment of the present invention rather than whole embodiments.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art are obtained under not making creative work premise, broadly fall into the scope of protection of the invention.
The operation principle of the technical program is: the technical program is divided into and at least includes three phases: section bar electric heating stretch wrap forming, electric heating solution treatment, electric heating Ageing Treatment.For effectively controlling the geomery change of part, it is also possible to carried out benefit before electric heating Ageing Treatment and draw.During section bar electric heating stretch wrap forming, the technical program carries out situ heat treatment based on shaping dies, eliminate the shifting furnaceman's sequence in traditional handicraft, it is not necessary to configure special heat treatment aging furnace, solve samming problem by auxiliary samming stove (playing insulation effect).In section bar electric heating stretch wrap forming stage, electric heating solution treatment stage, electric current is used to be heated to be heating mode from resistance, insulation samming effect is played with samming stove, compared with radiant heating pattern in traditional burner, both it had been obviously improved the efficiency of heating surface and had reduced energy consumption, having can guarantee that again that the uniformity of temperature was in the range of permissible value.
Based on above-mentioned operation principle, the present invention proposes a kind of titanium alloy profile stretch wrap forming situ heat treatment method.As shown in Figure 1.The method includes:
Step 101): at the anti-oxidation ceramic coating of sectional material blank surface smear；
Step 102): open samming stove, make described samming stove be warming up to the first temperature T1；
Step 103): by fixed component, section bar two ends are fixed；
Step 104): heating section bar, temperature rises to the first temperature T1, under the effect of described samming stove, makes the temperature stabilization of section bar in the first temperature T1 allowed band；
Step 105): in the first temperature T1 allowed band, according to fixed component movement locus on stretch bending mold, stretch bending is shaped to paste mould, and it is constant to keep mending the amount of drawing during stretch wrap forming；
Step 106): input protective gas at described stretch bending mold end so that the bringing-up section of section bar is under gas shield state；
Step 107): heating further to section bar, it is warming up to the second temperature T2, and makes the temperature of section bar stablize in the second temperature T2 allowed band in solution time section；
Step 108): in the second temperature T2 allowed band, by pattern and described stretch bending mold matched moulds；
Step 109): after solid solution completes, carry out section bar forcing Cooling Quenching to room temperature, in quenching process, in making section bar cavity after pattern with stretch bending mold matched moulds, be in mould constraint state；Meanwhile, protective gas is closed；
Step 110): the temperature of regulation samming stove is the 3rd temperature T3；
Step 111): when keeping mending the amount of drawing, by the section bar homoiothermic in cavity to the 3rd temperature T3, under the effect of described samming stove, the temperature making section bar is stable in the 3rd temperature T3 allowed band in aging time section；
Step 112): after reaching aging time section, the section bar in cavity naturally cools to room temperature, it is thus achieved that titanium alloy profile part.
Based on above-mentioned operation principle, the technical program also provides for another kind of titanium alloy profile stretch wrap forming situ heat treatment method.As in figure 2 it is shown, the method also included before step 110:
Step 110 '): heating the section bar in cavity, temperature rises to the first temperature T1, in the first temperature T1 allowed band, type part is carried out benefit and draws；Meanwhile, mend, during keeping stretch wrap forming, the amount of drawing constant.
Based on technique scheme, the present embodiment application stretch-wrap bending test system is for titanium alloy profile part.The present embodiment selects reason is that of stretch-wrap bending testing machine to provide pulling force online by stretch benders pivoted arm, it is possible to effective control section bar forming accuracy.When mould closes, during by the process means such as solution treatment, Ageing Treatment, regulate and control titanium alloy profile performance so that it is ageing strengthening.
As a example by titanium alloy TC 4 section bar, concrete operation step is as follows:
At sectional material blank surface spraying 0.5～2mm high-temp antioxidizing ceramic coating, such as aluminium oxide or zirconium oxide etc..
Open samming stove, make samming stove be warming up to forming temperature 500 DEG C～700 DEG C (T1).
For the thin-wall titanium alloy section bar of section bar thickness≤3mm, use clamp to be fixed at section bar two ends, apply pre-stretching strain 0.5%～2%；Regulating power source voltage 15～25V (noticing that running voltage is not above safe voltage 36V), makes section bar cross section electric current density reach 10A～100A/mm2, make section bar temperature rise to stretch wrap forming temperature 500 DEG C～700 DEG C (T1)；With displacement-control mode, it is shaped to paste mould by stretch bending according to clamp movement locus on stretch bending mold；Stretch wrap forming process includes: prestretching, is coated with and mends and draw, and mending the dependent variable drawn is 0～1.5%.
Open stretch bending mold end gas shield gas, make section bar bringing-up section be under gas shield state.
Stretch wrap forming terminates, and keeps mending the deflection drawing the stage to reach constant, and regulation voltage is 3～8V, makes section bar cross section electric current density reach 200～300A/mm2, section bar is brought rapidly up to 920 DEG C～950 DEG C (T2)；Further, section bar temperature is made to be kept stable in solid solubility temperature T2 allowed band, temperature retention time 1～10min.
By pattern and stretch bending mold matched moulds, section bar is made to be under the restrained condition of the cavity after matched moulds；As it is shown on figure 3, be the titanium alloy profile solid solution schematic diagram of the present embodiment.
After solution time terminates, close power supply；Opening big flow cooling pump, in making mold cavity, cooling medium is in quick flow regime, it is ensured that section bar rate of cooling is 20 DEG C～410 DEG C/s scopes, the section bar temperature in cavity to room temperature, closes protection gas.As shown in Figure 4, schematic diagram is cooled down for the present embodiment titanium alloy profile.A part of cooling medium is in pattern part, and another part cooling medium is in stretch bending mold.
The temperature of regulation samming stove is to 480 DEG C～600 DEG C (T3).
Power-on, continues in section bar to be passed through electric current, in the case of keeping the benefit amount of drawing, makes section bar be warming up to aging temp 480～600 DEG C (T3), makes section bar temperature stabilization in aging temp allowed band, and temperature retention time is 4～24h；This time period is aging time.
After reaching the aging time set, power-off makes the section bar in cavity naturally cool to room temperature, pickup.
In actual application technology scheme, technique experiences repeatedly thermal cycle, easily causes section bar intensity less than mother metal, it is difficult to meet performance requirement.And this case carries out solid solution-cooling-aging technique after shaping in situ, controllable titanium alloy profile intensity makes it higher than strength of parent.
Actual application scheme is according to the technique that after titanium alloy profile electric heating stretch wrap forming, heat treatment improves intensity in heating furnace again, for preventing heat treatment deformation, part after section bar electric heating stretch wrap forming needs to be clamped by complicated special fixture, frock must also be able to provide huge mold clamping force, heat treatment, complex technical process is carried out in fixture is placed on together with part heating furnace.And this case uses to shape and uses frock to be shaping dies with heat treatment, eliminate the special fixture of complexity, reduce shifting stove process and this process potential impact to material property.
In actual application scheme, special tooling is complicated and is only provided that clamping pressure, and section bar bears Moment, Deformation control DeGrain.And this case uses the benefit of clamp to draw to control section bar and be in patch mould state all the time, section bar entirety bears action of pulling stress, is effectively reduced resilience to ensure patch mould precision.
Above-described detailed description of the invention; the purpose of the present invention, technical scheme and beneficial effect are further described; it is it should be understood that; the foregoing is only the detailed description of the invention of the present invention; the protection domain being not intended to limit the present invention; all within the spirit and principles in the present invention, any modification, equivalent substitution and improvement etc. done, should be included within the scope of the present invention.
Claims (6)
1. a titanium alloy profile stretch wrap forming situ heat treatment method, it is characterised in that the method includes:
At the anti-oxidation ceramic coating of sectional material blank surface smear；
Open samming stove, make described samming stove be warming up to the first temperature；
By fixed component, section bar two ends are fixed；
Heating section bar, temperature rises to the first temperature, under the effect of described samming stove, makes the temperature stabilization of section bar in the first temperature allowed range；
In the first temperature allowed range, according to fixed component movement locus on stretch bending mold, stretch bending is shaped to paste mould, and it is constant to keep mending the amount of drawing during stretch wrap forming；
Protective gas is inputted so that the bringing-up section of section bar is under gas shield state at described stretch bending mold end；
Heating further to section bar, is warming up to the second temperature, and makes the temperature of section bar stablize in the second temperature allowed range in solution time section；
In the second temperature allowed range, by pattern and described stretch bending mold matched moulds；
After solid solution completes, carry out section bar forcing Cooling Quenching to room temperature, in quenching process, in making section bar cavity after pattern with stretch bending mold matched moulds, be in mould constraint state；Meanwhile, protective gas is closed；
The temperature of regulation samming stove is the 3rd temperature；
When keeping mending the amount of drawing, by the section bar homoiothermic in cavity to the 3rd temperature, under the effect of described samming stove, the temperature making section bar is stable in the 3rd temperature allowed range in aging time section；
After reaching aging time section, the section bar in cavity naturally cools to room temperature, it is thus achieved that titanium alloy profile part；
Wherein, the method also included before the step that temperature is the 3rd temperature of described regulation samming stove:
Heating the section bar in cavity, temperature rises to the first temperature, in the first temperature allowed range, type part is carried out benefit and draws；Meanwhile, mend, during keeping stretch wrap forming, the amount of drawing constant.
2. the method for claim 1, it is characterised in that described first temperature in the range of: 500 DEG C～700 DEG C.
3. the method for claim 1, it is characterised in that described second temperature is in the range of 920 DEG C～950 DEG C.
4. the method for claim 1, it is characterised in that described 3rd temperature is in the range of 480 DEG C～600 DEG C.
5. the method for claim 1, it is characterised in that the method for described intensification is that electric current is from hindering heating.
6. the method for claim 1, it is characterised in that described fixed component is clamp.
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| CN113612091B (en) * | 2021-08-02 | 2022-04-01 | 北京航空航天大学 | Large-current sliding conductive device suitable for self-resistance heating hot stretch bending equipment |
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| CN102367563A (en) * | 2011-10-13 | 2012-03-07 | 北京航空航天大学 | Titanium alloy thin-wall part hot-stretch creep deformation composite molding method |
| CN102500675A (en) * | 2011-10-13 | 2012-06-20 | 北京航空航天大学 | Hot forming tool of titanium alloy thin-wall part and machining method of hot forming tool |
| CN102814368A (en) * | 2012-08-23 | 2012-12-12 | 北京航空航天大学 | Compound molding tool system for hot stretch bending and creep deformation of section bar and application method of compound molding tool system |
| CN102834196A (en) * | 2009-11-30 | 2012-12-19 | 西瑞尔贝兹公司 | Stretch forming apparatus with supplemental heating and method |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102834196A (en) * | 2009-11-30 | 2012-12-19 | 西瑞尔贝兹公司 | Stretch forming apparatus with supplemental heating and method |
| CN102367563A (en) * | 2011-10-13 | 2012-03-07 | 北京航空航天大学 | Titanium alloy thin-wall part hot-stretch creep deformation composite molding method |
| CN102500675A (en) * | 2011-10-13 | 2012-06-20 | 北京航空航天大学 | Hot forming tool of titanium alloy thin-wall part and machining method of hot forming tool |
| CN102814368A (en) * | 2012-08-23 | 2012-12-12 | 北京航空航天大学 | Compound molding tool system for hot stretch bending and creep deformation of section bar and application method of compound molding tool system |
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