CN202951751U - Isothermal forming device of aircraft spherical shell - Google Patents
Isothermal forming device of aircraft spherical shell Download PDFInfo
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- CN202951751U CN202951751U CN 201220540756 CN201220540756U CN202951751U CN 202951751 U CN202951751 U CN 202951751U CN 201220540756 CN201220540756 CN 201220540756 CN 201220540756 U CN201220540756 U CN 201220540756U CN 202951751 U CN202951751 U CN 202951751U
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Abstract
An isothermal forming device of an aircraft spherical shell relates to the field of forging and is divided into an upper portion and a lower portion which are symmetrical. The upper portion and the lower portion respectively comprise a mold, an induction coil, a thermocouple and a water pipe cooling mold holder, wherein the induction coil is arranged on an outer ring of the mold, the thermocouple is arranged in the mold, and the water pipe cooling mold holder and the mold are mutually fixed. Each mold comprises an upper part and a lower part, an argon pipe is arranged in the upper part of the mold, and a hemispheric isothermal forming region is arranged in the lower part of the mold. Compared with the traditional device which adopts mechanical processing after multi-step mold forging forming, the isothermal forming device of the aircraft spherical shell has the advantages that labor grinding load is reduced to 1/2-1/3 of the existing grinding load, metal consumption is reduced to 1/3-1/5 of the existing metal consumption, and accuracy of part geometrical parameters is improved by 4-6 times.
Description
Technical field
The utility model relates to a kind of device that forges field, specifically a kind of aircraft spherical shell ausforming device.
Background technology
In space flight and aviation aircraft parts are produced, controlling under optimum lot size production time condition, guarantee that the tactics processing performance of Element Design is basic task.
In aircraft, from the metal wastage viewpoint, the body that relates to various geometries is maximum.These parts should have high unit strength (breaking load and mass ratio), because changes in environmental conditions is very big in actual use, likely meet with very big load.
In manufacturing the aircraft parts, be widely used high strength titanium alloy TC4, BT14, BT20, BT23.These alloys have that high pressure-bearing, quality are little, the characteristics of high corrosion-resistant life.But, due to material high strength and inductile, under the pressure processing condition, problem has appearred.Addressing these problems future directions, be in the inferior temperature and pressure power processing of certain speed～temperature conditions, at this moment deformable material shows visco-plasticity and VISCOUS FLOW, can be under relatively low technique power material production large deformation and not destroying more, to guarantee the precision of the high physical dimension parameter of filling shape degree and part.
For taking up the fuel spherical shell, dividing plate is typical part, its traditional processing technology is that multiple operation stretches on forcing press, inter process also will heat, or at the hammer die forging.
These techniques existing problems are, because the precision level that has the residual stress part is low, residual stress causes the External Shape distortion, for subsequent handling, needs pincers worker to a large amount of reconditionings of part, think that follow-up argon arc welding or electron beam welding prepare.In many cases, residual stress exists in original blank and distortion sheet material, and it causes the anisotropic mechanical property of part and unhomogeneity of deformation.
Through the retrieval to prior art, find; Chinese patent literature CN1814371 open day 2006～08～09; put down in writing a kind of titanium alloy spherical shell superplastic manufacturing process; this technology is put into counterdie by titanium alloy blank; heating by electric cooker is incubated while being warming up to the lower limit temperature of shaping; be incubated rear hydraulic press depress to just as the time continue to heat up, during to the maximum temperature that reaches shaping, stop being shaped, once circulation finishes; Start to heat up while being cooled to lower 50 ℃～80 ℃ of the lower limit temperature of shaping, start to be shaped to the lower limit temperature be shaped, stop moulding while reaching the moulding maximum temperature again, secondary cycle finishes, and so through repeatedly being circulated to moulding, completes; In described forming method, the temperature range of moulding is 800 ℃～900 ℃ and only moulding in temperature-rise period, and range of temperature is 100 ℃, shaping speed 0.6mm/min～1.0mm/min.Can be used for
The following different-diameter of 800mm, the moulding of different wall titanium alloy spherical shell, utilize this process to provide required withstand voltage ball for bathyscaph, and the titanium alloy spherical shell inner surface of moulding is without processing, and outer surface and top allowance are very little.This manufacturing process is called the environment superplasticity, but the prior art need to repeatedly heat up, lower the temperature in the set point of temperature scope, can bring variations in temperature stress to mould undoubtedly, reduces die life; Again because of the cooling that repeatedly heats up, thereby reduce productivity ratio, cause manufacturing cost can not to be in any more; Easily in blank surface, form not only hard but also crisp α shell in this technology implementation process simultaneously, not only reduce Product Precision, more can cause properties of product to descend.
Also there is the die forging cubic deformation in prior art; but because it does not all relate to stabilisation heat treatment; cause in workpiece and have residual stress; it will cause anisotropic mechanical property and the unhomogeneity of deformation of part; blank in heating process is not carried out to effectively anti-oxidation, anti-operation of inhaling the hydrogen protection in prior art simultaneously yet; the final performance of product will certainly be affected, and also specification requirement can't be met far away on the Product Precision that obtains of prior art.
The utility model content
The utility model, for the prior art above shortcomings, proposes a kind of aircraft spherical shell ausforming device, prepares more high accuracy and has the aircraft spherical shell that meets GJB2921～1997 code requirement performances and deformation parameter.
The utility model is achieved through the following technical solutions:
The utility model relates to a kind of aircraft spherical shell ausforming device, this apparatus structure is symmetrical upper and lower two parts and comprises respectively: mould, induction coil, thermocouple and water flowing cooling die holder, wherein: induction coil is arranged on the outer ring of mould, thermocouple is arranged on the inside of mould, and water flowing cooling die holder and mould fix.
Described mould comprises upper and lower two parts, wherein: be provided with the argon gas pipeline in upper part mould, be provided with hemispherical ausforming zone in lower part mould.
The arrival end of described argon gas pipeline is positioned at the top of mould and divides induction coil top, the outside; The port of export of argon gas pipeline is positioned at the upper part center of mould and for the lower part of mould, the plate-like cavity that this port of export comprises outlet opening and is attached thereto.
Described water flowing cooling die holder inside is provided with cooling water inlet pipe and cooling drainpipe, wherein: some cooling water inlet pipes are arranged at the upper part of water flowing cooling die holder with S shape structure, corresponding some cooling drainpipes are arranged at the lower part of water flowing cooling die holder, be connected and synchronize and input cooling water with forcing press with water pump by the arrival end by cooling water inlet pipe, realizing the cooling of mould.
Described mould adopts nickel-base alloy IN100 casting, and hemispherical ausforming zone adopts the spark-erosion machine tool electric discharge to be processed into; The thermocouple monitoring that is arranged at hemispherical ausforming region surface for the temperature of mould, realize that Average remains on 25%-35%, is preferably 30%.
The utility model relates to the aircraft spherical shell that said apparatus prepares, and this spherical shell is along being out of shape the variation thick to the ball roof of feature radius zone: to titanium alloy material, be 1.15 ~ 0.55mm.
The tensile strength that adopts the TC4 titanium alloy to prepare described aircraft spherical shell is 958-978(MPa), yield strength is 922-942(MPa), percentage elongation is 21-23%, hardness HRC is 31-33, meets code requirement GJB2921～1997.
The utility model, for titanium alloy characteristics in heating process, passes into the protectiveness inert gas, not only is conducive to, without the punch gas expansion forming, protect workpiece surface quality and mechanical property simultaneously.Violent effect at high temperature can occur with furnace gas in titanium alloy.What harm was maximum is oxygen, particularly hydrogen.About temperature more than 595 ℃, titanium alloy reacts with oxygen and nitrogen and generates scale, under scale, for the oxygen rich nitrogen rich layer, is called the α shell; Blank surface scale thickness everywhere is different, and after scale removal, titanium or titanium alloy blank surface occurs uneven, has affected the surface quality of workpiece.On the other hand, be to make the oxygenation of blank top layer.More than 630 ℃, oxygen uptake phenomenon appears in the surface of titanium or titanium alloy, and oxygen, by loose scale, from the epidermis of blank, to depths, spread, and, more than beta transus temperature, the diffusion of oxygen is accelerated greatly.Because oxygen is the element of stable alpha phase, after amount that oxygen enters titanium alloy surpasses certain numerical value, β just can not exist mutually, thereby, at blank surface formation α embrittlement layer, according to the difference of heating condition and alloy kind, the thickness of α embrittlement layer can reach 0.65mm.This α shell is not only hard but also crisp, easily makes product cause crackle.
Oxygen is only had an effect on the blank top layer, and hydrogen is deep into alloy inside, makes its plasticity degradation.Be subject to titanium and the alloy thereof of hydrogen contamination that " hydrogen embrittlement " easily occurs.Put into practice and studies have shown that, the hydrogen－sucking amount of titanium alloy has remarkable impact to mechanical property, and along with the increase of hydrogen－sucking amount, its plasticity also decreases, and wherein the reduction of impact flexibility is especially remarkable.
The utility model and traditional Simulation Based On Multi-step die-forging forming then machining relatively, it is original 1/2 ~ 1/3 that the work reconditioning quality reduces to, it is original 1/3 ~ 1/5 that metal consumption reduces to, the precision of part geometry parameter has increased by 4 ~ 6 times.
The accompanying drawing explanation
Fig. 1 is the utility model process chart.
Fig. 2 is the embodiment device structural representation;
In figure: 1 mould, 2 induction coils, 3 thermocouples, 4 die holders, 5 induction heating apparatus fixed bars, 6 cooling water pipes, 7 hemispherical ausforming zones, 8 argon gas pipelines, 9 plate-like cavitys.
Fig. 3 is mold temperature test thermocouple distribution schematic diagram.
Fig. 4 is that cooling water pipe is arranged schematic diagram.
Fig. 5 is that the utility model prepares aircraft spherical shell schematic diagram;
In figure: (a) being top view, is (b) upward view.
The specific embodiment
Below embodiment of the present utility model is elaborated; the present embodiment is implemented take technical solutions of the utility model under prerequisite; provided detailed embodiment and concrete operating process, but protection domain of the present utility model is not limited to following embodiment.
Embodiment 1
The present embodiment be take the material titanium alloy TC 4 as example, and its processing step comprises:
1), as shown in Fig. 1 i, treat that the blank of goods sequentially passes through cutting, degreasing, pickling, clear water rinsing, drying program;
2) mould is installed on TZP type 6300kN single action sheet hydraulic drawing press, after upper/lower die is closed up, opens the intermediate frequency induction heating device button, heating mould to 900 ℃;
3) as shown in Fig. 1 ii, thick 1.5mm, TC4 titanium alloy plate are heated in the vacuum drying oven argon gas, temperature range is 875 ~ 930 ℃, sheet material flow stress scope is 100 ~ 200MPa;
4) as shown in Fig. 1 iii, start press, open mould, the sheet material after preheating is inserted in impression, to close die, pass into argon gas and, at Forming under Pressure, the argon pressure scope is 1 ~ 1.5MPa, curring time is 12 ~ 18 minutes; Maximum argon pressure 1.5MPa, appear at and be shaped the 4th minute, final forming pressure 1MPa, total curring time 15 minutes;
5) treat that under gas pressure goods are cooled to 300 ℃ with mould, 200 minutes cool times;
6) after removing pressure, cooling die in mobile argon gas, be cooled to 70 ~ 100 ℃, 200 minutes cool times;
7), as shown in Fig. 1 iv and Fig. 5, trimming and chemistry mill; Blank after shaping is along the flange trimming and carry out chemistry and mill the regulation wall thickness, and the maximum attenuation of blank is in the hemisphere dome, reaches original blank 40% thickness.From wall section, to flange transitional region thickness, be original blank thickness 70%, after the excision flange section, ball forming thickness limit inhomogeneities reaches 30%.Above-mentioned inhomogeneities is milled elimination by chemistry; Metallographic observation shows, in the shaping real process, crystal grain is not grown up, and is still original blank size 5 ~ 10 μ m.Thereby can guarantee creep rupture strength, the corrosion resisting property of part and keep the regulation air-tightness under service condition.
8) weld two hemisphere: be welded to connect with bonding machine, pipeline be solded into simultaneously.On mounting clip, using continuous radiation power 2.5kvt, model with laser head is that TH～LWY180180S/300S carries out laser weld, and during welding, the two hemispheres rotary speed is 1.2 rev/mins.Laying through welding on ring.Observe material structure, grain growth do not occurred.
With air pressure ausforming and traditional Simulation Based On Multi-step die-forging forming then machining relatively, it is original 1/2 ~ 1/3 that the work reconditioning quality reduces to, it is original 1/3 ~ 1/5 that metal consumption reduces to, the precision of part geometry parameter has increased by 4 ~ 6 times.
As shown in Figure 2, the present embodiment is aircraft spherical shell ausforming device, and this structure is symmetrical upper and lower two parts and comprises respectively: mould 1, induction coil 2, thermocouple 3, water flowing cooling die holder 4, induction heater fixed bar 5 and cooling water pipe 6.Wherein: induction coil 2 is arranged on the outer ring of mould 1, and thermocouple 3 is arranged on the inside of mould 1, and water flowing cooling die holder 4 fixes with mould 1.
Described thermocouple 3 according to hot conduction principles, be vertically installed in respectively mould 1 upper and lower part end face and be distributed in: the footpath of the edge of the center of mould 1, mould 1 (four) and mould 1 make progress plate-like cavity 9 periphery (four) and with the mid point (four) at the edge of mould 1, as shown in Figure 3.
As shown in Figure 4, described water flowing cooling die holder 4 inside are provided with cooling water inlet pipe 6a and cooling drainpipe 6b, wherein: some cooling water inlet pipe 6a are arranged at the upper and lower part of water flowing cooling die holder 4 with S shape structure, the corresponding some cooling drainpipe 6b upper and lower parts that are arranged at water flowing cooling die holder 4 alternate with water inlet pipe, be connected and synchronize and input cooling water with forcing press with water pump by the arrival end by cooling water inlet pipe 6a, realizing the cooling of mould.
Described mould 1 comprises upper and lower two parts, wherein: be provided with argon gas pipeline 8 in upper part mould, be provided with hemispherical ausforming zone 7 in lower part mould.
The arrival end of described argon gas pipeline 8 is positioned at the top of mould 1 and divides induction coil 2 tops, the outside; The port of export of argon gas pipeline 8 is positioned at the upper part center of mould 1 and for the lower part of mould 1, the plate-like cavity 9 that this port of export comprises outlet opening and is attached thereto.
The diameter in described hemispherical ausforming zone 7 is identical with the diameter of plate-like cavity 9, and plate-like cavity 9 to the degree of depth of die joint is: 150mm, diameter is 300mm.
Described aircraft spherical shell ausforming device is installed on TZP type 6300kN single action sheet hydraulic drawing press, the ram speed of this forcing press keeps constant strain rate by programme-control to realize that technique is omnidistance, make the yield stress of titanium alloy remain on low-level on.
The Output pressure of described forcing press and the stroke of slide block are that digitlization shows, preferably by XY2 recorder record.
Described mould 1 adopts nickel-base alloy IN100 casting, and hemispherical ausforming zone 7 adopts the spark-erosion machine tool electric discharge to be processed into; Thermocouple 3 monitoring that are arranged at 7 surfaces, hemispherical ausforming zone for the temperature of mould 1, realize that Average remains on 25%-35%, is preferably 30%.
Ausforming depends on the speed that under the pressure processing condition, gas pressure increases in time.The increase of speed causes the rising of pressure, and distortion sheet material degree in uneven thickness also increases.Underspeeding will be overheated, and metal grain is grown up, the accumulation internal flaw.In view of this, must guarantee the Best Times length of deformation process: for the TC4 titanium alloy time be 0.2 ~ 0.3h.After shaping, pressurize a period of time stabilisation heat treatment under gas pressure.
The TC4 titanium alloy aircraft spherical shell prepared by said apparatus and technique, this spherical shell is thick to the ball roof along distortion feature radius zone is changed to 1.15 ~ 0.55mm.
The present embodiment ausforming method and conventional method compare, and design parameter is in Table 1 and table 2.
The resistance of deformation of table 1TC4 under differing formed technique, from plastic force, preferably take superplasticforming, but will do complicated superplasticity before being shaped, processes, and cost is too high, and productivity ratio is too low, therefore, selects the ausforming method that lower-cost output capacity is higher:
| Forming technology | Resistance of deformation (MPa) |
| Common shaping | 1200 |
| Approach ausforming | 700 |
| Ausforming | 150 |
| Superplasticforming | 40 |
The comparison of table 2TC4 titanium alloy conventional shaping and isothermal forging forming parameters:
| Parameter name | The conventional shaping | Ausforming |
| Mold temperature (℃) | 150 | 900 |
| The blank temperature (℃) | 900 | 900 |
| Workpiece temperature (℃) | 800 | 900 |
| Strain rate (s ～1） | 10 1～10 3 | 10 ～3～10 ～2 |
| Flow stress (MPa) | 500～1200 | 80～120 |
| Mold materials | X38CrMoV51 | IN100 |
Half bulb diameter that the present embodiment is shaped is
The thick 1.5mm of titanium alloy TC 4 sheet material, its test parameter is as follows:
The technical program is made hemisphere-shaped workpiece except being applied to titanium alloy TC 4, also can be applied to the parts of titanium alloy BT14, aluminium alloy 1971 and 5456 materials, and can obtain approximate effect.
Claims (4)
1. an aircraft spherical shell ausforming device, it is characterized in that, this apparatus structure is symmetrical upper and lower two parts and comprises respectively: mould, induction coil, thermocouple and water flowing cooling die holder, wherein: induction coil is arranged on the outer ring of mould, thermocouple is arranged on the inside of mould, and water flowing cooling die holder and mould fix; Described mould comprises upper and lower two parts, wherein: be provided with the argon gas pipeline in upper part mould, be provided with hemispherical ausforming zone in lower part mould.
2. device according to claim 1, it is characterized in that, described thermocouple according to hot conduction principles, be vertically installed in respectively mould upper and lower part end face and be distributed in: the footpath of the center of mould, the edge of mould and mould make progress the peripheral of plate-like cavity and with the mid point at the edge of mould.
3. device according to claim 1, is characterized in that, the arrival end of described argon gas pipeline is positioned at the top of mould and divides induction coil top, the outside; The port of export of argon gas pipeline is positioned at the upper part center of mould and for the lower part of mould, the plate-like cavity that this port of export comprises outlet opening and is attached thereto; The diameter in this hemispherical ausforming zone is identical with the diameter of plate-like cavity.
4. device according to claim 1, it is characterized in that, described water flowing cooling die holder inside is provided with cooling water inlet pipe and cooling drainpipe, wherein: some cooling water inlet pipes are arranged at the upper and lower part of water flowing cooling die holder with S shape structure, and corresponding some cooling drainpipes are arranged at the upper and lower part of water flowing cooling die holder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220540756 CN202951751U (en) | 2012-10-19 | 2012-10-19 | Isothermal forming device of aircraft spherical shell |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220540756 CN202951751U (en) | 2012-10-19 | 2012-10-19 | Isothermal forming device of aircraft spherical shell |
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| CN 201220540756 Expired - Fee Related CN202951751U (en) | 2012-10-19 | 2012-10-19 | Isothermal forming device of aircraft spherical shell |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102873166A (en) * | 2012-10-19 | 2013-01-16 | 上海桦厦实业有限公司 | Aircraft spherical shell isothermal forming method and device |
| CN114603252A (en) * | 2022-03-29 | 2022-06-10 | 江苏大学 | Method and device for assisting laser shock micro-forming by medium-frequency electromagnetic induction heating |
-
2012
- 2012-10-19 CN CN 201220540756 patent/CN202951751U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102873166A (en) * | 2012-10-19 | 2013-01-16 | 上海桦厦实业有限公司 | Aircraft spherical shell isothermal forming method and device |
| CN102873166B (en) * | 2012-10-19 | 2014-12-24 | 上海桦厦实业有限公司 | Aircraft spherical shell isothermal forming method and device |
| CN114603252A (en) * | 2022-03-29 | 2022-06-10 | 江苏大学 | Method and device for assisting laser shock micro-forming by medium-frequency electromagnetic induction heating |
| CN114603252B (en) * | 2022-03-29 | 2024-04-09 | 江苏大学 | Method and device for auxiliary laser shock micro-forming by medium-frequency electromagnetic induction heating |
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