CN205165702U - Ultra -fine grain titanium alloy sheath and compound extrusion forming die thereof - Google Patents
Ultra -fine grain titanium alloy sheath and compound extrusion forming die thereof Download PDFInfo
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- CN205165702U CN205165702U CN201520945294.5U CN201520945294U CN205165702U CN 205165702 U CN205165702 U CN 205165702U CN 201520945294 U CN201520945294 U CN 201520945294U CN 205165702 U CN205165702 U CN 205165702U
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Abstract
The utility model provides the utility model discloses an ultra -fine grain titanium alloy sheath and compound extrusion forming die thereof of carbon fiber blade, adopt the titanium alloy blank heat in mould cavity after just, the backward extrusion obtains the semi -manufactured goods of arcuate zone lateral wall, push by the bending die that has V -arrangement structure terrace die again and make. The utility model discloses superfineization processing is done to titanium alloy TC4 grain structure earlier in innovation ground, makes its superplastic forming temperature drop to 650 DEG C by 900 DEG C, then takes shape through general hot mould steel to reduce cost by a wide margin. With accurate die forging method shaping thin wall in protective atmosphere, make its few machining, the complete smoothness of protection streamline to increase substantially its stress corrosion resistance ability, its intensity also increases by 20~30%.
Description
Technical field
The utility model relates to a kind of technology of metal process field, specifically a kind of ultra-fine grain titanium alloy sheath for carbon fiber blade and Compound Extrusion shaping dies thereof.
Background technology
Modern aeroengine fan and compressor blade uses carbon fiber manufacture.Owing to alleviating quality significantly under guarantee structural strength and reliability conditions, comparing with titanium alloy blade has more bright prospect.
But carbon fiber blade greatest weakness, namely blade in use, and leading edge portion is the most often subject to surface abrasion and outside enters object strike effect, sandstone and flying bird etc.Therefore in order to ensure flight safety, the leading edge of blade imposes high strength titanium alloy protection by means of retaining element or glue.But the manufacture of titanium alloy protective jacket is enough complicated problem, because protective jacket has different cross section, the section thickness difference of part is very large, comprises the thick and heavy leading edge cross section of thin wall and enhancing; In addition, sheath has complicated spatial form, is included on horizontal plane direction and has curve form and upright plane of bending.
Coloured combustion gas turbine company of the U.S. (ChromalloyGasTurbineCorporationUSA) designs and uses the three-dimensional blank of titanium alloy TC 4 (Ti-6Al-4V) to manufacture sheath.Blank makes inner V-arrangement die cavity by milling.Then extrusion molding sidewall in a mold, extrusion temperature 850 ~ 900 DEG C, then carry out last machining.The wall thickness of part only has 0.5 ~ 0.2mm.Protective gas is not had to cause surface gas saturated.Extrude titanium alloy at such high temperatures, expensive nickel base superalloy must be needed to make mould; There is no operation under protective atmosphere, the extruding thin-walled gas (as oxygen, hydrogen etc.) that is subject to is injured.In order to remove the surface that workpiece is soaked, must a large amount of machining be done, like this, not only having excised by gas pickling surface, and having excised the fibre flow formed in extruding, streamline having been exposed, increases stress corrosion chance.
Through finding the retrieval of prior art, Chinese patent literature CN103009018A, open (bulletin) day 2013.04.03, disclose the manufacture method of a kind of Ultra-fine Grained, high-strength alloy blade forging, manufacture process comprises, extruding, finish-forging, trimming, heat treatment, adopt barium chloride salt-bath furnace at all heating before described extrusion process; Described extrusion die adopts the square frustum structure of " rhombus blade and tenon " opposite opened, and carries out intensive treatment to extrusion die throat; But this technology secondary extrusion (deflection 20 ~ 60%) can only reach fine grain, and this technique cannot be applicable to titanium alloy TC 4.
Chinese patent literature CN1439467, open (bulletin) day 2003.09.03, disclose a kind of extruding of thermal strength titanium alloy blades, precise roll-forging method, adopt the little surplus half finish forge blade of extruding as the blank of roll-forging process, take effectively to protect lubricant coating, and adopt chemical milling process remove various add hanker formed pollution layer; Preferably, warm roll-forging process achieves the precise roll-forging shaping of the micro-surplus of medium and small compressor titanium alloy blade (≤0.10mm); And the technique adopting the heat treatment phase of vacuum dehydrogenation and adjustment leaf tissue performance to combine, technical process is: blanking, is coated with glass lubricant; Hot extrusion; Polishing, cleaning glass lubricant; Milling depollution layer; Vacuum recrystallization annealing; Roughing blade tenon and switching fillet; Warm roll forging; Second time is except glass lubricant and milling depollution; Vacuum dehydrogenation and recrystallization annealing; Correct; Second time annealing; Precision optical machinery is processed, but this technical finesse object shapes is comparatively simple, and changes of section is little.The shaping of sheath cannot be applicable to.
Chinese patent literature CN103781588A, open (bulletin) day 2014.05.07, disclose the method for a kind of making for the reinforcement 30 of the leading edge 16 of reinforced blade 12, wherein, described reinforcement 30 is made by pressurized thermal spraying plated metal coating in described leading edge 16.A kind of blade of blade 12, particularly turbine engine, the blade of helicopter, or the blade of screw, leading edge 16 is subject to the protection of such reinforcement wherein.But thermal spraying to be only stressed 40Pa to the metal in leading edge in this technology, superplastic die forging can not be stood extrude such pressure 80 ~ 120MPa and be fully out of shape, therefore some coarse grains as cast sturcture, such sheath anti-impact force and anti-corrosion capability are nothing like the extrusion strength degree σ of titanium alloy
b=1200 ~ 1500MPa; In addition, this technology is all very complicated, loaded down with trivial details to sprayed surface process, equipment, filler etc., and implementation condition requires harsh.
Utility model content
The utility model, for prior art above shortcomings, proposes a kind of ultra-fine grain titanium alloy sheath and Compound Extrusion shaping dies thereof, first does ultra fine to titanium alloy TC 4 grain structure, makes its superplastic forming temperature drop to 650 DEG C by 900 DEG C; Then be shaped by general hot die steel, mould need not be made, significantly to reduce costs with the high temperature alloy being difficult to machining of costliness.To be shaped in protective atmosphere thin-walled by precision die forging method, to make its few machining, the complete smoothness of protection streamline, to increase substantially its stress corrosion resistant ability, its intensity also increases by 20 ~ 30%.
The utility model is achieved through the following technical solutions:
The utility model relates to a kind of ultra-fine grain titanium alloy sheath and Compound Extrusion shaping dies thereof, comprise: upper die mechanism and the lower die mechanism with core rod, wherein: in lower die mechanism, be provided with inverted trapezoidal cavity, core rod is movably set in cavity also just to upper die mechanism; This core rod by two pieces of identical structures and half die be oppositely arranged form, the punch in two and half dies and upper die mechanism forms mold cavity.
Described upper die mechanism comprises: the cope match-plate pattern be from top to bottom fixedly connected sequentially, upper bolster and centring ring, and is movably set in the punch in centring ring, wherein: centring ring is fixedly connected with upper die mechanism.
The top of described punch is U-shaped structure or v-shaped structure, may be used for backward and forward extrusion and curvature correction process respectively.
Half described die is preferably according to the different half die size with correspondence different from work step workpiece shapes of the structure on punch top.
The outside of described locator slide is preferably provided with induction heater, is provided with the thermocouple be attached thereto in half die described in correspondence, thus realizes the control to blank and mold temperature.
Described being slidably connected is realized by guide post mechanism.
Described lower die mechanism comprises: be fixedly installed on the core rod fixed block on die shoe and locator slide; and two guide pin bushings be movably set between core rod fixed block and locator slide; wherein: core rod fixed block and locator slide form described inverted trapezoidal cavity, two pieces of identical structures and the guide pin bushing be oppositely arranged are just to the bottom of described half die.
Described guide pin bushing is driven by lower push rod and carries out moving upward to realize the material returned.
Preferably cooling water pipe is provided with in described upper bolster and die shoe.
The utility model relates to the ultra-fine grain titanium alloy sheath that above-mentioned mould prepares, and is strip v-shaped structure, and curve shape and the blade outer rim of this sheath lumen match.
The utility model relates to the application of above-mentioned ultra-fine grain titanium alloy sheath, is fixed on blade by high-strength adhesive.
Technique effect
Compared with prior art, the shaping of the jacket wall that the utility model technique obtains is even, and reach e ≈ 3 at wall portion logarithm deformation extent, mechanical property on average improves 20 ~ 30%.Under temperature is no more than 700 DEG C of conditions, the utility model reduces the cost of finished parts significantly.
Accompanying drawing explanation
Fig. 1 is sheath superplasticity composite extrusion die schematic diagram;
In figure: a is assembling schematic diagram; B ~ d is core rod operating diagram; Semi-finished product after semi-finished product, the anti-crowded sidewall of 23 sheaths after the just crowded leading edge of 1 screw, 2 cope match-plate patterns, 3 centring rings, 4 induction heaters, 5 screws, 6 locator slides, 7 pins, 8 screws, 9 blanks, 10 lower push rods, 11 punch, 12 pilot pins, 13 half dies, 14 water flowing upper bolsters, 15 die fixed blocks, 16 guide pin bushings, 17 guide pillars, 18 thermocouples, 19 cooling water pipes, 20 water flowing die shoes, 21 backing plates, 22 sheaths.
Fig. 2 is that bar is through conversion axial load upsetting pull schematic diagram;
Fig. 3 is the bending work step schematic diagram of the punch of v-shaped structure:
In figure: 24 sheath forging;
Fig. 4 is the utility model finished sheath forging schematic perspective view.
Detailed description of the invention
The present embodiment is implement material with titanium alloy TC 4, and the preparation of blank superfine grained structure comprises uses diameter
bar, conversion axial load, progressively reducing along the repeated multiple times jumping-up in X, Y, Z axis direction, pulling under temperature conditions, as shown in Figure 2, its concrete operation step is as follows:
Employing component is: 5.8 ~ 6.5%Al, 3.9 ~ 4.2%V, 0.12%Fe, < 0.15%Si, 0.08%C, < 0.02%N, < 0.01%H, < 0.15%O and surplus are Ti's
bar, the transition temperature of its alpha+beta/β is 990 DEG C.
The first step: cylindrical bar is heated up in micro-oxidizing atmosphere and is heated to 800 DEG C ± 10 DEG C;
Second step: treat forging stock and carry out repeatedly jumping-up pulling distortion on 2 tons of electric hydraulic free hammers, make its logarithm deformation extent reach e ≈ 3, its forging ratio is about 20.Then be placed in stove 600 DEG C of full annealings, cool to room temperature with the furnace, make strip plate.
4th step: strip plate is rolled into thick 5mm band under 600 DEG C of environment, its logarithm deformation extent e ≈ 3.Deformation result mean grain size is at 0.5 μm.
The equipment that the present embodiment adopts is numerical control isothermal forging hydropress, and its important technological parameters is: nominal pressure 25MN, moved cross beam operating rate 0.05 ~ 0.30mm/s, liquid working pressure 25MPa, workpiece and mold heated temperature≤1200 DEG C, workbench effective dimensions are 2500 × 1800mm.
The present embodiment realizes compound hot extrusion process especially by following operation:
1) adopt titanium alloy TC 4 as the material of original blank, cut out neat billet size 5 × 10 × 270mm from having the band of superfine grained structure of obtaining, Shot Blasting is done to blank;
2) as shown in Figure 1a, FR-6 glass lubricant is coated to original blank 1, then by core rod load map 1a mould in Fig. 1 b ~ d, wherein two halves die is made up of tool steel 5Cr3W3MoVSi, this core rod by two pieces of identical structures and half die 13 be oppositely arranged form.
The shape of described blank has in the horizontal plane on curve shape and vertical plane and has torsional angle, corrects before extrusion to respective planes.
Described FR6 glass lubricant, its component and mass percent are 54%SiO
2, 5%Al
2o
3, 8.5%B
2o
3, 27.5%Na2O, 5%CaO.
In order to lubricant can stick to blank surface, be sprayed onto in blank surface with sprayer, after spraying dry 20 ~ 30 minutes or dry in 60 DEG C ~ 80 DEG C baking ovens in atmosphere.After completing, the surface of original blank 1 has the coating that thickness is 0.1mm ~ 0.2mm.This coating makes the coefficient of friction between mould and blank be reduced to 0.08 ~ 0.10 in deformation process; Thus make extend 20 ~ 30% die life.
Half described die 13 is fixed on die fixed block 15 respectively from inside to outside, and the profile that inner wall shape after matched moulds and sheath are respectively out of shape work step forging 22 ~ 23 matches; Mold cavity is formed after half die 13 matched moulds and with the punch 4 of U-shaped structure.
Described mould is that tool steel 5Cr3W3MoVSi makes, and its heat treatment hardness is 48 ~ 52HRC.
As shown in Figure 1, the locator slide 6 in described mould is fixed with die shoe and is become 25 ° of inclination angles with vertical direction; When lower push rod 10 jack-up, when two half modules move upward in guide pin bushing 16, because they are separately fixed on die fixed block 15, so half die and die fixed block are up and open, the distance of its horizontal opening along slideway 6, just take out forging.
The stroke of described lower push rod 10 is 150mm, and the distance opened along chute when such ejection stroke ensures that locator slide rises, can take out forging smoothly.
When press ram backhaul, along with the whereabouts of push rod, core rod is slipped to bottom die shoe with deadweight, and two-half die closes up.Die cavity put into by blank, along with press ram is descending, drives the patrix and counterdie matched moulds that are fixed on slide block lower plane, carries out extrusion forging to blank.Forging terminates, and push rod ejects forging, forms the demoulding, circulates repeatedly like this, can production traditional mode of production cannot the complex precise part of the demoulding.
3) under leveling die horizontal plane condition, original blank is laid in mold cavity, then by intermediate frequency induction heating device, mould and blank are heated to 650 DEG C, punch is used to carry out the first work step distortion to original blank, namely forward extrusion is shaped, complete the leading edge reinforcing section of semi-finished product sheath 5, as illustrated in figure 1 c.
The deformation velocity of described forward extrusion is 0.3 ~ 0.5mm/min.Storage material is for shaped side walls in the case.
4) in same impression, carry out the second work step, i.e. backward extrusion when punch continues descending, complete the sidewall of backplate 5, as shown in Figure 1 d, and make blank forming become required form, obtain semi-finished product Compound Extrusion part;
The deformation velocity of described backward extrusion is 0.3 ~ 0.5mm/min.
As shown in Figure 4, be state when original blank is out of shape in a mold in above-mentioned steps 1 ~ 4 process and corresponding phase shapes video.
5) as shown in Figure 3, semi-finished product are moved into and adjoins and be heated in the bending die of the similar structures of temperature same with Fig. 1 d, realize the 3rd work step distortion by the punch of v-shaped structure, i.e. bending forming.
Described bending die comprises: with the die of type groove and the punch of v-shaped structure, as shown in Figure 3.
By step 5) forging that obtains detects, and it is unfolded and interlayer defect in shape.From the sample microscopic structure that sheath wall portion and leading edge cut, respectively as shown in Figure 4.
It is 0.3 ~ 0.5 μm by translucent determination of electron microscopy forging average grain size.Crystallite dimension is reduced to 0.3 μm of explanation, and under backward extrusion condition, wall portion metal is subject to severe plastic deformation.The shaping of wall portion is even, reaches e ≈ 3 at wall portion logarithm deformation extent.Store energy and reduce crystallite dimension, making the strength of materials increase by 20 ~ 30%.
According to above-described embodiment result, showing that the utility model can implement the production in enormous quantities of sheath part, as shown in Figure 4, is precision die forgings after small lot batch manufacture.
Above-mentioned concrete enforcement can carry out local directed complete set to it by those skilled in the art in a different manner under the prerequisite not deviating from the utility model principle and aim; protection domain of the present utility model is as the criterion with claims and can't help above-mentioned concrete enforcement and limit, and each implementation within the scope of it is all by the constraint of the utility model.
Claims (5)
1. a Compound Extrusion shaping dies for ultra-fine grain titanium alloy sheath, is characterized in that, comprising: upper die mechanism and the lower die mechanism with core rod, and wherein: be provided with inverted trapezoidal cavity in lower die mechanism, core rod is movably set in cavity also just to upper die mechanism; This core rod by two pieces of identical structures and half die be oppositely arranged form, the punch in two and half dies and upper die mechanism forms mold cavity.
2. Compound Extrusion shaping dies according to claim 1; it is characterized in that; described upper die mechanism comprises: the cope match-plate pattern be from top to bottom fixedly connected sequentially, upper bolster and centring ring, and is movably set in the punch in centring ring, wherein: centring ring is fixedly connected with upper die mechanism.
3. Compound Extrusion shaping dies according to claim 1, is characterized in that, the top of described punch is respectively U-shaped structure and v-shaped structure, is respectively used to backward and forward extrusion and curvature correction process.
4. Compound Extrusion shaping dies according to claim 1; it is characterized in that; described lower die mechanism comprises: be fixedly installed on the core rod fixed block on die shoe and locator slide; and two guide pin bushings be movably set between core rod fixed block and locator slide; wherein: core rod fixed block and locator slide form described inverted trapezoidal cavity, two pieces of identical structures and the guide pin bushing be oppositely arranged are just to the bottom of described half die.
5. a ultra-fine grain titanium alloy sheath, is characterized in that, this sheath is strip inner chamber v-shaped structure, and the interior shape curve shape of this sheath and blade outer rim match, and bonding is fixed in blade outer rim.
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| CN201520945294.5U CN205165702U (en) | 2015-11-24 | 2015-11-24 | Ultra -fine grain titanium alloy sheath and compound extrusion forming die thereof |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105382167A (en) * | 2015-11-24 | 2016-03-09 | 浙江申吉钛业股份有限公司 | Ultra-fine grain titanium alloy sheath and combined extrusion forming die and method of ultra-fine grain titanium alloy sheath |
| CN106374183A (en) * | 2016-09-23 | 2017-02-01 | 浙江申吉钛业股份有限公司 | Apparatus and method for preparing flange bent waveguide tube by forward cold extrusion method |
| CN107962360A (en) * | 2017-12-05 | 2018-04-27 | 成都市鸿侠科技有限责任公司 | A kind of aero-engine obturages blade processing technique and molding die |
-
2015
- 2015-11-24 CN CN201520945294.5U patent/CN205165702U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105382167A (en) * | 2015-11-24 | 2016-03-09 | 浙江申吉钛业股份有限公司 | Ultra-fine grain titanium alloy sheath and combined extrusion forming die and method of ultra-fine grain titanium alloy sheath |
| CN106374183A (en) * | 2016-09-23 | 2017-02-01 | 浙江申吉钛业股份有限公司 | Apparatus and method for preparing flange bent waveguide tube by forward cold extrusion method |
| CN106374183B (en) * | 2016-09-23 | 2021-07-06 | 浙江申吉钛业股份有限公司 | Flanged bending waveguide tube based on positive cold extrusion method and preparation device and method thereof |
| CN107962360A (en) * | 2017-12-05 | 2018-04-27 | 成都市鸿侠科技有限责任公司 | A kind of aero-engine obturages blade processing technique and molding die |
| CN107962360B (en) * | 2017-12-05 | 2020-07-28 | 成都市鸿侠科技有限责任公司 | Machining process and forming die for aeroengine sealing blade |
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