CN104561869A - Titanium alloy profile stretch bending, forming and in-situ heat treating method - Google Patents
Titanium alloy profile stretch bending, forming and in-situ heat treating method Download PDFInfo
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- CN104561869A CN104561869A CN201410827568.0A CN201410827568A CN104561869A CN 104561869 A CN104561869 A CN 104561869A CN 201410827568 A CN201410827568 A CN 201410827568A CN 104561869 A CN104561869 A CN 104561869A
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Abstract
The invention relates to a titanium alloy profile stretch bending, forming and in-situ heat treating method which comprises the following steps: painting an anti-oxidation ceramic coating on the surface of a profile blank; enabling a temperature equilibrium furnace to reach a first temperature; fixing the two ends of a profile through fixing parts; heating the profile to enable the temperature to reach the first temperature, bending and forming the profile onto an attaching die according to the running track of the fixing part on a stretch bending die, and keeping the supplemental stretching quantity to be unchanged during the stretching bending process; further heating the profile, increasing the temperature to reach a second temperature, and enabling the temperature of the profile to be stable within a range allowed by the second temperature in a solid solution time period; carrying out die assembly to a former and the stretch bending die, so as to enable the profile to be in a die restrained condition inside a cavity formed by through die assembly of the former and the stretch bending die; carrying out forced cooling and quenching to the profile to enable the profile to reach a room temperature; adjusting the temperature of the temperature equilibrium furnace to be a third temperature; under a state of keeping the stretching quantity unchanged, adjusting the temperature of the profile in the cavity to the third temperature, and after an aging time period is reached, naturally cooling the profile inside the cavity to the room temperature.
Description
Technical field
The present invention relates to metal forming processing technique field, particularly a kind of titanium alloy profile stretch wrap forming situ heat treatment method.
Background technology
Section bar part is the important feature part forming aircraft primary load bearing framework, its forming quality is directly connected to the assembly precision of aircraft, complete machine aerodynamic configuration, work-ing life, becoming the key problem in technology affecting aircraft development and ensure overall aircraft military service performance, is also one of the principal element affecting aircraft manufacturing cycle, cost and benefit.
Introduce existing conventional section bar part forming technology below:
1, section bar electric heating stretch wrap forming technology
Titanium alloy at ambient temperature plasticity is poor, by promoting temperature, its plasticity being increased, adopting from hindering heating means, making section bar conducting self-heating, be the important of titanium alloy profile stretch wrap forming and one of effective measures by low-voltage, high-current.Titanium alloy profile electric heating stretch wrap forming technique utilizes the characteristic that titanium alloy heat conductivility is low, specific resistance is large, larger electric current is continued through in sectional material blank bending forming process, the joule heating utilizing this section of sectional material blank self-resistance to produce heats, and is heated to forming temperature and the technique of charged stretch wrap forming.The difficult technological difficulties be shaped of titanium alloy profile temperature-room type plasticity difference can be solved preferably, the bending forming of the structural partss such as military battlebus, Military Ship, carry-on frame, edge strip can be widely used in.Domesticly to begin one's study from resistance heating stretch wrap forming technology in the nineties, adopt operational path to be mainly: blank electrified regulation, to warm power-off, stretching+stretch bending+stretching, hot school shape, unloading.Cyril Bath company of the U.S. is the demand meeting Boeing's matrix material fuselage titanium alloy frame beam part, develops titanium alloy electric heating stretch bending equipment cooperatively, Boeing 787 aircraft obtains practical engineering application with RTI Internat Metals Inc. of titanium alloy manufacturers.
2, titanium alloy profile is from resistance heating stretch wrap forming and thermal creep technology
Application number be 201210303645.3 patent application document disclose a kind of section bar hot-drawn curved creep combined shaping system and using method thereof.Adopt and from resistance heating system, section bar is heated, until section bar temperature reaches default stretch wrap forming temperature value, through prestretching, coated, mend and be pulled through journey and complete stretch wrap forming, then adopt the heating container be 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 cycling, easily causes section bar intensity lower than mother metal, is difficult to meet performance requriements.According to after titanium alloy profile electric heating stretch wrap forming again in process furnace thermal treatment improve the technique of intensity, for preventing heat treatment deformation, part after section bar electric heating stretch wrap forming needs to be clamped by the unit clamp of complexity, frock also must can provide huge mold clamping pressure, fixture is placed in process furnace together with part and heat-treats, complex technical process, and special tooling is complicated and only can provide mold pressure, Deformation control DeGrain.
Summary of the invention
For solving the problem of prior art, the present invention proposes a kind of titanium alloy profile stretch wrap forming and situ heat treatment method, solves actual production medium section and pastes mould difficulty and the problem of intensity reduction.By the mode from resistance heating, in stretch bending mold, carry out titanium alloy profile stretch wrap forming, during solution hardening, section bar is still in stretch bending mold.Under samming stove is auxiliary, regulate and control titanium alloy profile intensity by ageing strengthening after Cooling Quenching, make the part of acquisition reach performance requriements.
For achieving the above object, the invention provides a kind of titanium alloy profile stretch wrap forming and situ heat treatment method, the method comprises:
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 fixing part, section bar two ends are fixed;
To section bar heating, temperature rises to the first temperature, under the effect of described samming stove, makes the temperature-stable of section bar at the first temperature allowed range;
In the first temperature allowed range, according to the movement locus of fixing part on stretch bending mold, stretch bending is shaped to subsides mould, and keeps the benefit amount of drawing in stretch wrap forming process constant;
At described stretch bending mold end input protection gas, under making the heating zone of section bar be in gas shield state;
Section bar is heated further, is warming up to the second temperature, and make the temperature of section bar be stabilized 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, pressure Cooling Quenching is carried out to room temperature to section bar, in quenching process, make to be in mould constraint state in the cavity of section bar after pattern and stretch bending mold matched moulds; Meanwhile, shielding gas is closed;
The temperature regulating samming stove is the 3rd temperature;
Keeping, under the state of mending the amount of drawing, by the section bar temperature adjustment in cavity to the 3rd temperature, under the effect of described samming stove, making the temperature of section bar in aging time section, be stabilized in the 3rd temperature allowed range;
After reaching aging time section, the section bar in cavity naturally cools to room temperature, obtains titanium alloy profile part.
Preferably, the method also comprised before the temperature of described adjustment samming stove is the step of the 3rd temperature:
To the section bar heating in cavity, temperature rises to the first temperature, carries out benefit draw in the first temperature allowed range to shaped piece; Meanwhile, deflection when keeping benefit to draw is constant.
Preferably, the scope of described first temperature is: 500 DEG C ~ 700 DEG C.
Preferably, the scope of described second temperature is 920 DEG C ~ 950 DEG C.
Preferably, the scope of described 3rd temperature is 480 DEG C ~ 600 DEG C.
Preferably, the method for described intensification is that electric current is from hindering heating.
Preferably, described fixing part is clamp.
Technique scheme has following beneficial effect: the technical program, compared with former technique, in frock angle, decreases in process furnace the special tooling mould preventing heat treatment deformation from using, improves the heating efficiency of section bar itself, improve capacity usage ratio; Section bar part aspect, not only ensure that forming accuracy but also has regulated and controled performance.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present invention or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is a kind of titanium alloy profile stretch wrap forming of proposing of the present invention and one of situ heat treatment method flow diagram;
Fig. 2 is a kind of titanium alloy profile stretch wrap forming of proposing of the present invention and situ heat treatment method flow diagram two;
Fig. 3 is the titanium alloy profile solid solution schematic diagram of the present embodiment;
Fig. 4 is for being the present embodiment titanium alloy profile cooling schematic diagram.
Embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, be clearly and completely described the technical scheme in the embodiment of the present invention, obviously, described embodiment is only the present invention's part embodiment, instead of whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.
The principle of work of the technical program is: the technical program is divided into and at least comprises 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, benefit can also be carried out before electric heating ageing treatment and drawing.In section bar electric heating stretch wrap forming process, the technical program carries out situ heat treatment based on shaping dies, eliminate and move furnaceman's sequence in traditional technology, do not need configure dedicated thermal treatment aging oven, 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 adopted to be heated to be heating mode from resistance, the effect of insulation samming is played with samming stove, compared with radiant heating pattern in traditional burner, both significantly promoted heating efficiency and reduced energy consumption, and can ensure that again the homogeneity of temperature was within the scope of permissible value.
Based on above-mentioned principle of work, the present invention proposes a kind of titanium alloy profile stretch wrap forming and situ heat treatment method.As shown in Figure 1.The method comprises:
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 fixing part, section bar two ends are fixed;
Step 104): to section bar heating, temperature rises to the first temperature T1, under the effect of described samming stove, makes the temperature-stable of section bar in the first temperature T1 allowed band;
Step 105): in the first temperature T1 allowed band, according to the movement locus of fixing part on stretch bending mold, stretch bending is shaped to subsides mould, and keeps the benefit amount of drawing in stretch wrap forming process constant;
Step 106): at described stretch bending mold end input protection gas, under making the heating zone of section bar be in gas shield state;
Step 107): section bar is heated further, is warming up to the second temperature T2, and make the temperature of section bar be stabilized 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, pressure Cooling Quenching is carried out to room temperature to section bar, in quenching process, make to be in mould constraint state in the cavity of section bar after pattern and stretch bending mold matched moulds; Meanwhile, shielding gas is closed;
Step 110): the temperature regulating samming stove is the 3rd temperature T3;
Step 111): keeping, under the state of mending the amount of drawing, by the section bar temperature adjustment in cavity to the 3rd temperature T3, under the effect of described samming stove, making the temperature of section bar be stabilized 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, obtains titanium alloy profile part.
Based on above-mentioned principle of work, the technical program also provides another kind of titanium alloy profile stretch wrap forming and situ heat treatment method.As shown in Figure 2, the method also comprised before step 110:
Step 110 '): to the section bar heating in cavity, temperature rises to the first temperature T1, carries out benefit draw in the first temperature T1 allowed band to shaped piece; Meanwhile, keep the benefit amount of drawing in stretch wrap forming process constant.
Based on technique scheme, the present embodiment application stretch-wrap bending test system is for titanium alloy profile part.The present embodiment selects the reason of stretch-wrap bending trier to be: provide pulling force online by stretch benders pivoted arm, can effectively control section bar forming accuracy.Under the state that mould is closed, during by the process means such as solution treatment, ageing treatment, regulation and control titanium alloy profile performance, makes its ageing strengthening.
For 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, as aluminum oxide or zirconium white 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, adopt clamp to be fixed at section bar two ends, apply pre-stretching strain 0.5% ~ 2%; Regulating power source voltage 15 ~ 25V (note operating voltage can not higher than safety voltage 36V), makes section bar cross section current density reach 10A ~ 100A/mm
2, make section bar temperature rise to stretch wrap forming temperature 500 DEG C ~ 700 DEG C (T1); With displacement-control mode, according to the movement locus of clamp on stretch bending mold, stretch bending is shaped to subsides mould; Stretch wrap forming process comprises: prestretching, coated and mend and draw, and mending the dependent variable of drawing is 0 ~ 1.5%.
Open stretch bending mold end gas shield gas, under making section bar heating zone be in gas shield state.
Stretch wrap forming terminates, and the deflection keeping the benefit stage of drawing to reach is constant, and regulating voltage is 3 ~ 8V, makes section bar cross section current density reach 200 ~ 300A/mm
2, section bar rapid temperature increases to 920 DEG C ~ 950 DEG C (T2); Further, section bar temperature is made to keep being stabilized in solid solubility temperature T2 allowed band, soaking time 1 ~ 10min.
By pattern and stretch bending mold matched moulds, under making section bar be in the restrained condition of the cavity after matched moulds; As shown in Figure 3, be the titanium alloy profile solid solution schematic diagram of the present embodiment.
After solution time terminates, powered-down; Open large discharge cooling pump, make heat-eliminating medium in mold cavity be in quick flow state, ensure that section bar speed of cooling is 20 DEG C ~ 410 DEG C/s scope, the section bar temperature in cavity, to room temperature, closes protection gas.As shown in Figure 4, be the present embodiment titanium alloy profile cooling schematic diagram.Part heat-eliminating medium is in pattern part, and another part heat-eliminating medium is in stretch bending mold.
Regulate temperature to 480 DEG C ~ 600 DEG C (T3) of samming stove.
Power-on, continues in section bar to pass into electric current, and when keeping mending the amount of drawing, make section bar be warming up to aging temp 480 ~ 600 DEG C (T3), make section bar temperature-stable in aging temp allowed band, soaking time is 4 ~ 24h; This time period is aging time.
After reaching the aging time of setting, power-off makes the section bar in cavity naturally cool to room temperature, pickup.
In practical application technical scheme, technique experiences repeatedly thermal cycling, easily causes section bar intensity lower than mother metal, is difficult to meet performance requriements.And this case original position after being shaped carries out solid solution-cooling-aging technique, controllable titanium alloy profile intensity makes it higher than strength of parent.
Actual application scheme according to after titanium alloy profile electric heating stretch wrap forming again in process furnace thermal treatment improve the technique of intensity, for preventing heat treatment deformation, part after section bar electric heating stretch wrap forming needs to be clamped by the unit clamp of complexity, frock also must can provide huge mold clamping pressure, fixture is placed in process furnace together with part and heat-treats, complex technical process.And this case adopts to be shaped and adopts frock to be shaping dies with thermal treatment, eliminate the unit clamp of complexity, reduce and move stove process and this process to the potential impact of material property.
In actual application scheme, special tooling is complicated and only can provide mold pressure, and section bar bears Moment, Deformation control DeGrain.And this case adopts the benefit of clamp to draw to control section bar to be in mould state of pasting all the time, section bar entirety bears action of pulling stress, effectively can reduce resilience to ensure subsides mould precision.
Above-described embodiment; object of the present invention, technical scheme and beneficial effect are further described; be understood that; the foregoing is only the specific embodiment of the present invention; the protection domain be not intended to limit the present invention; within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (7)
1. titanium alloy profile stretch wrap forming a situ heat treatment method, it is characterized in that, the method comprises:
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 fixing part, section bar two ends are fixed;
To section bar heating, temperature rises to the first temperature, under the effect of described samming stove, makes the temperature-stable of section bar in the first temperature allowed range;
In the first temperature allowed range, according to the movement locus of fixing part on stretch bending mold, stretch bending is shaped to subsides mould, and keeps the benefit amount of drawing in stretch wrap forming process constant;
At described stretch bending mold end input protection gas, under making the heating zone of section bar be in gas shield state;
Section bar is heated further, is warming up to the second temperature, and the temperature of section bar is stabilized 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, pressure Cooling Quenching is carried out to room temperature to section bar, in quenching process, make to be in mould constraint state in the cavity of section bar after pattern and stretch bending mold matched moulds; Meanwhile, shielding gas is closed;
The temperature regulating samming stove is the 3rd temperature;
Keeping, under the state of mending the amount of drawing, by the section bar temperature adjustment in cavity to the 3rd temperature, under the effect of described samming stove, making the temperature of section bar be stabilized 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, obtains titanium alloy profile part.
2. the method for claim 1, is characterized in that, the method also comprised before the temperature of described adjustment samming stove is the step of the 3rd temperature:
To the section bar heating in cavity, temperature rises to the first temperature, carries out benefit draw in the first temperature allowed range to shaped piece; Meanwhile, keep the benefit amount of drawing in stretch wrap forming process constant.
3. method as claimed in claim 1 or 2, it is characterized in that, the scope of described first temperature is: 500 DEG C ~ 700 DEG C.
4. method as claimed in claim 1 or 2, it is characterized in that, the scope of described second temperature is 920 DEG C ~ 950 DEG C.
5. method as claimed in claim 1 or 2, it is characterized in that, the scope of described 3rd temperature is 480 DEG C ~ 600 DEG C.
6. method as claimed in claim 1 or 2, is characterized in that, the method for described intensification is that electric current is from hindering heating.
7. method as claimed in claim 1 or 2, it is characterized in that, described fixing part is clamp.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113560381A (en) * | 2021-07-27 | 2021-10-29 | 北京航空航天大学 | Large-section titanium alloy profile high-temperature creep forming tool and using method thereof |
| CN113612091A (en) * | 2021-08-02 | 2021-11-05 | 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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2014
- 2014-12-26 CN CN201410827568.0A patent/CN104561869B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113560381A (en) * | 2021-07-27 | 2021-10-29 | 北京航空航天大学 | Large-section titanium alloy profile high-temperature creep forming tool and using method thereof |
| CN113560381B (en) * | 2021-07-27 | 2022-03-29 | 北京航空航天大学 | Large-section titanium alloy profile high-temperature creep forming tool and using method thereof |
| CN113612091A (en) * | 2021-08-02 | 2021-11-05 | 北京航空航天大学 | Large-current sliding conductive device suitable for self-resistance heating hot stretch bending equipment |
| 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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Effective date of registration: 20190603 Address after: 100024 North East military villa, eight Li bridge, Chaoyang District, Beijing Patentee after: China Institute of Aeronautical Manufacturing Technology Address before: 100024 North East military villa, eight Li bridge, Chaoyang District, Beijing Patentee before: Beijing Aviation Manufacturing Engineering Institute of China Aviation Industry Group Company |