CN105880609B - The moulding technique and molding die of a kind of engine jet pipe - Google Patents
The moulding technique and molding die of a kind of engine jet pipe Download PDFInfo
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- CN105880609B CN105880609B CN201610218412.1A CN201610218412A CN105880609B CN 105880609 B CN105880609 B CN 105880609B CN 201610218412 A CN201610218412 A CN 201610218412A CN 105880609 B CN105880609 B CN 105880609B
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- 238000000465 moulding Methods 0.000 title claims abstract description 41
- 238000000034 method Methods 0.000 title claims abstract description 30
- 238000005728 strengthening Methods 0.000 claims abstract description 18
- 238000001125 extrusion Methods 0.000 claims abstract description 14
- 238000001192 hot extrusion Methods 0.000 claims abstract description 12
- 238000010791 quenching Methods 0.000 claims abstract description 6
- 230000000171 quenching effect Effects 0.000 claims abstract description 6
- 230000008569 process Effects 0.000 claims abstract description 5
- 238000005245 sintering Methods 0.000 claims description 16
- 239000000463 material Substances 0.000 claims description 15
- 239000000843 powder Substances 0.000 claims description 13
- 229910052751 metal Inorganic materials 0.000 claims description 12
- 239000002184 metal Substances 0.000 claims description 12
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 10
- 238000002156 mixing Methods 0.000 claims description 10
- 238000004663 powder metallurgy Methods 0.000 claims description 10
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 claims description 6
- 238000001816 cooling Methods 0.000 claims description 5
- 238000010438 heat treatment Methods 0.000 claims description 5
- 238000010079 rubber tapping Methods 0.000 claims description 4
- 229910021529 ammonia Inorganic materials 0.000 claims description 3
- 238000000137 annealing Methods 0.000 claims description 3
- 238000011049 filling Methods 0.000 claims description 3
- 239000012535 impurity Substances 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 3
- 239000011812 mixed powder Substances 0.000 claims description 3
- 238000004321 preservation Methods 0.000 claims description 3
- 239000002994 raw material Substances 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 238000007873 sieving Methods 0.000 claims description 3
- 238000005303 weighing Methods 0.000 claims description 3
- 238000011068 loading method Methods 0.000 claims 1
- 239000007921 spray Substances 0.000 claims 1
- 210000000867 larynx Anatomy 0.000 abstract description 5
- 239000000567 combustion gas Substances 0.000 abstract description 3
- 239000000203 mixture Substances 0.000 description 11
- 230000002787 reinforcement Effects 0.000 description 4
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 238000005520 cutting process Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 239000003921 oil Substances 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 210000001161 mammalian embryo Anatomy 0.000 description 2
- 239000012778 molding material Substances 0.000 description 2
- 238000005406 washing Methods 0.000 description 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 239000011651 chromium Substances 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 239000010721 machine oil Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- XOOUIPVCVHRTMJ-UHFFFAOYSA-L zinc stearate Chemical compound [Zn+2].CCCCCCCCCCCCCCCCCC([O-])=O.CCCCCCCCCCCCCCCCCC([O-])=O XOOUIPVCVHRTMJ-UHFFFAOYSA-L 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/10—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of articles with cavities or holes, not otherwise provided for in the preceding subgroups
- B22F5/106—Tube or ring forms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F1/00—Metallic powder; Treatment of metallic powder, e.g. to facilitate working or to improve properties
- B22F1/14—Treatment of metallic powder
- B22F1/142—Thermal or thermo-mechanical treatment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/02—Compacting only
- B22F3/03—Press-moulding apparatus therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/20—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by extruding
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/18—Hardening; Quenching with or without subsequent tempering
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/08—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for tubular bodies or pipes
- C21D9/085—Cooling or quenching
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/20—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by extruding
- B22F2003/208—Warm or hot extruding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
- B22F2998/10—Processes characterised by the sequence of their steps
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Powder Metallurgy (AREA)
Abstract
The moulding technique and molding die of a kind of engine jet pipe, it is related to a kind of extrusion process and molding die.The present invention in order to solve the problem of engine jet pipe part there are high temperature resistant, high-voltage performance is poor that combustion gas is caused to wash away scaling loss to jet pipe larynx neck.Method：First, it stocks up：2nd, equipment prepares：3rd, it is preforming：4th, it is sintered：5th, hot extrusion molding：6th, quenching treatment：7th, lonneal：8th, it finishes：9th, phosphorating treatment.Mold：Cushion block is mounted in die holder groove, die holder is connect with cushion block, strengthen die sleeve to be mounted on die holder, restoring board is installed on the limiting shoulder for strengthening die sleeve, strengthens being respectively equipped with multiple release links and Duo Gen guide posts between die sleeve and die holder, and multiple guide sleeves, which are inserted into, to be strengthened on die sleeve, cavity plate, which is mounted on, to be strengthened in die sleeve, lower core model is mounted in cavity plate, and upper core model is installed in the stepped hole of clamping plate, and cope plate, backing plate and clamping plate are from top to bottom arranged successively.The present invention is used for jet pipe extrusion forming.
Description
Technical field
The present invention relates to a kind of moulding technique and molding dies, and in particular to a kind of moulding process of engine jet pipe
Method and molding die.
Background technology
Ammunition engine operating instant, under the action of high temperature, high pressure, burning that propellant powder flame generates jet pipe larynx neck
Damage, can produce a very large impact the running orbit precision of body trajectory.And the carbon constructional quality steel engine of former mechanical processing
Jet pipe part can not meet the performance requirement of jet pipe part by test of many times.It especially can not meet engine jet pipe part
High temperature resistant, high-voltage performance are poor, cause combustion gas to jet pipe larynx neck the problem of washing away scaling loss.
Invention content
The purpose of the present invention is to solve engine jet pipe parts there are high temperature resistant, high-voltage performance are poor, lead to combustion gas pair
The problem of washing away scaling loss of jet pipe larynx neck.And then provide a kind of moulding technique and molding die of engine jet pipe.
The technical scheme is that：A kind of moulding technique of engine jet pipe, it includes the following steps：
Step 1: stock：
First：Iron powder is annealed：
The iron powder of no annealing in 700~750 DEG C of protection of ammonia stove is subjected to deoxidation processing, 1.5~2h is kept the temperature, goes out
Furnace temperature must not exceed 200 DEG C；
Second：Sieving：
Iron powder after cooling of coming out of the stove carried out -150 mesh of 60 mesh sieve；
Third：Dispensing：
According to the total weight of a batch mixing, the weight of each raw material is calculated by ratio requirement；
4th：Batch mixing：
The powder for completing proportioning is encased in batch mixer with 3~4h of speed batch mixing of 20~30r/min；
5th：It is sieved again：
Mixed powder carried out 60 mesh sieve again, removed caking impurity；
Step 2: equipment prepares：
First：Equipment debugging；
Second：Installation mold；
It is Step 3: preforming：
First：Claim single-piece material, weighing is required by weight with balance；
Second：It is die-filling, powder is attached in mold with funnel；
Third：Pre-profiling, mold are pressed onto position；
4th：Depanning；
5th：Clear up overlap；
6th：Mounted box；
Step 4: sintering：
It is good that the blank that makes preforming in step 3 is packed into box interior sealing, is sent into sintering fire door, when running in stove
1.5~2h is sintered during 1100~1150 DEG C of high temperature sections, until coming out of the stove 650~750 DEG C；
Step 5: hot extrusion molding：
The blank that 650~750 DEG C of temperature come out of the stove will be sintered to (to be prevented embryo material temperature too low, and influenced to be molded ruler in 1 minute
Very little and density) it puts into extrusion molding dies and is pressed into place, the parts density after extruding is >=7.8/g.cm3, and reach final
Size requirement；
Step 6: quenching treatment：
The extrusion of depanning is put into oil and is cooled down；
Step 7: lonneal：
It is jet pipe part after extrusion molding, jet pipe part is put into 200~300 DEG C of heat-treatment furnaces, heat preservation 1~
1.5h temper；
Step 8: finishing：
10 holes of φ and outer diameter are machined by pattern；
Step 9: phosphorating treatment：
Jet pipe part after mechanical processing carries out phosphorating treatment by phosphatization requirement.
The present invention also provides a kind of molding die of engine jet pipe include die holder, cushion block, lower core model, upper core model,
Backing plate, clamping plate, cavity plate, restoring board, strengthens die sleeve, multiple resetting springs, multiple release links, multiple washers, multiple spiral shells at cope plate
Female, multiple cope plate fixing screws, multiple die sleeve fixing screws, multiple guide sleeves, multiple die holders connection bolt and Duo Gen guide posts.
The upper surface middle part position of die holder opens up die holder groove, and cushion block is mounted in die holder groove, die holder with
It is bolted between cushion block by the connection of multiple die holders, strengthens die sleeve and be mounted on die holder, and strengthened die sleeve and be sleeved on pad
On the lateral wall of block, the lateral wall top for strengthening die sleeve opens up limiting shoulder, and restoring board is installed on the limiting shoulder for strengthening die sleeve
It goes up and is connect by multiple die sleeve fixing screws with strengthening die sleeve, strengthen being respectively equipped with multiple release links between die sleeve and die holder
With more guide posts, the upper end of each release link passes through restoring board, one is respectively equipped in each release link of restoring board upper end
A washer and a nut, the lower end of each release link are connect with die holder, and every between die sleeve and die holder positioned at strengthening
It is covered there are one resetting spring in a release link, multiple guide sleeves are inserted on restoring board from the bottom to top, and the top of every guide post can
It is slidably mounted on restoring board, the lower part of every guide post is connect with die holder, and cavity plate, which is mounted on, to be strengthened in die sleeve, and cavity plate is with adding
Strong die sleeve is integral by being interference fitted hot charging technique assembling, and lower core model is mounted in cavity plate.
The madial wall of clamping plate is equipped with stepped hole, and upper core model is from top to bottom installed in the stepped hole of clamping plate, cope plate, pad
Plate with clamping plate is from top to bottom arranged and is connected by multiple cope plate fixing screws successively, upper core model be located at lower core model just on
Side is equipped with metal powder metallurgy powder between lower core model and cavity plate inner cavity.
The present invention has the following effects that compared with prior art：
Process：After engine jet pipe part is using the mixing of metal powder metallurgy material, through hot extrusion molding technique side
The jet pipe part of method processing, part machinery performance indicator is reachable, hardness HB >=70, radial pressure P >=40KN.Pass through engine
Static igniting comparative test result shows：Larynx neck size using the jet pipe part of hot extrusion molding does not change.By using
The engine jet pipe part of powdered metallurgical material heat extrusion forming is not only increased part performance indicator, and is added using the technology
The part of work has the following advantages that：With few cutting or without cutting metal dusty material, stock utilization (is cut up to more than 95%
The part material utilization rate for cutting processing method manufacture only has 40%~50%).Also, a large amount of manpowers can be saved and mechanical processing is set
It is standby, processing cost is reduced, is more suitable for producing in batches.
Molding die：When solving the problems, such as jet pipe density and insufficient intensity, two-way hot extrusion shaping mold is employed, is had
The density and intensity that ensure that metal powder metallurgy material of effect, improve service precision, and mould structure is simple, it is easy to accomplish.
Description of the drawings
Fig. 1 is the two-way hot extrusion composite molding die structure diagram of jet pipe：1 die holder；2 resetting springs；3 release links；4
Cushion block；5 washers；6 nuts；7 times core models；Core model on 8；9 backing plates；10 screws；11 cope plates；12 clamping plates；13 screws；14 cavity plates；
15 guide sleeves；16 restoring boards；17 strengthen die sleeve；18 bolts；19 guide posts.Fig. 2 is jet pipe hot extrusion part drawing.
Specific embodiment
Specific embodiment one：A kind of moulding technique of engine jet pipe of present embodiment, it includes following step
Suddenly：
Step 1: stock：
First：Iron powder is annealed：The iron powder of no annealing is subjected to deoxidation processing in 700~750 DEG C of protection of ammonia stove,
1.5~2h is kept the temperature, tapping temperature must not exceed 200 DEG C；
Second：Sieving：Iron powder after cooling of coming out of the stove carried out -150 mesh of 60 mesh sieve；
Third：Dispensing：According to the total weight of a batch mixing, the weight of each raw material is calculated by ratio requirement；
4th：Batch mixing：The powder for completing proportioning is encased in batch mixer with 3~4h of speed batch mixing of 20~30r/min；
5th：It is sieved again：Mixed powder carried out 60 mesh sieve again, removed caking impurity；
Step 2: equipment prepares：
First：Equipment debugging；Second：Installation mold；
It is Step 3: preforming：
First：Claim single-piece material, weighing is required by weight with balance；Second：It is die-filling, powder is attached in mold with funnel；
Third：Pre-profiling, mold are pressed onto position；4th：Depanning；5th：Clear up overlap；6th：Mounted box；
Step 4: sintering：
It is good that the blank that makes preforming in step 3 is packed into box interior sealing, is sent into sintering fire door, when running in stove
1.5~2h is sintered during 1100~1150 DEG C of high temperature sections, until coming out of the stove 650~750 DEG C；
Step 5: hot extrusion molding：
The blank that 650~750 DEG C of temperature come out of the stove will be sintered to (to be prevented embryo material temperature too low, and influenced to be molded ruler in 1 minute
Very little and density) it puts into extrusion molding dies and is pressed into place, the parts density after extruding is >=7.8/g.cm3, and reach final
Size requirement；
Step 6: quenching treatment：
The extrusion of depanning is put into oil and is cooled down；
Step 7: lonneal：
It is jet pipe part after extrusion molding, jet pipe part is put into 200~300 DEG C of heat-treatment furnaces, heat preservation 1~
1.5h carries out temper；
Step 8: finishing：
It is machined by pattern size；
Step 9: phosphorating treatment：
Jet pipe part after mechanical processing carries out phosphorating treatment by phosphatization requirement.
Specific embodiment two：It is sent into the step of present embodiment four in sintering fire door, bringing-up section temperature is 600 DEG C.
Using powder metallurgy sintering furnace under the protection of inert gas, it will be packed into seal box when the blank that precompressed makes, be pushed into import
600 DEG C of bringing-up section temperature, 1100~1150 DEG C of high temperature section (are sintered 1.2~1.5h), in the stove that 650~750 DEG C of tapping temperature, in advance
Sintering time needs 3~4h altogether.Convenient for ensureing sintering quality.Other compositions and connection relation are same as the specific embodiment one.
Specific embodiment three：It is burnt in the step of present embodiment four when running to 1100~1150 DEG C of high temperature sections in stove
1.5~2h of knot, until coming out of the stove 650~750 DEG C.Convenient for ensureing sintering quality.Other compositions and connection relation and specific embodiment party
Formula one or two is identical.
Specific embodiment four：It is sent into the step of present embodiment four in sintering fire door and is pre-sintered the time as 3-4h.Just
In guarantee sintering quality.Other compositions and connection relation are identical with specific embodiment one, two or three.
Specific embodiment five：Jet pipe part is put into 200~300 DEG C of heat-treatment furnaces in the step of present embodiment seven
In, after keeping the temperature 1~1.5h, furnace cooling to room temperature, then temper.Convenient for ensureing sintering quality.Other compositions and connection are closed
System is identical with specific embodiment one, two, three or four.
The blank that 650~750 DEG C of temperature come out of the stove that will be sintered in step 5 is put into extrusion molding dies and is carried out at once
It squeezes, ensures parts density >=7.8/g.cm3.The mold is mounted on 160t hydraulic presses, utilizes the upper core model of upper die component
Downlink is pressed against closure with lower mold assemblies, squeezes out jet pipe part.
It is matched and is molded using metal powder, specific mass percentage composition includes：Iron powder 1~4%, nickel 40~50%, chromium
19~26%, tungsten 13~16%, graphite powder 0.2~1%, zinc stearate 1~4% and machine oil 1~4%.Powdered metallurgical material
Granularity is 60~150 mesh.
Specific embodiment six：The present embodiment will be described with reference to Fig. 1, and present embodiment includes die holder 1, cushion block 4, lower core
Mould 7, backing plate 9, cope plate 11, clamping plate 12, cavity plate 14, restoring board 16, strengthens die sleeve 17, is multiple resetting springs 2, more upper core model 8
A release link 3, multiple nuts 6, multiple cope plate fixing screws 10, multiple die sleeve fixing screws 13, multiple is led at multiple washers 5
Set 15, multiple die holders connection bolt 18 and Duo Gen guide posts 19.
The upper surface middle part position of die holder 1 opens up die holder groove, and cushion block 4 is mounted in die holder groove, die holder 1
Bolt 18 is connect by multiple die holders to connect, strengthen die sleeve 17 and be mounted on die holder 1, and strengthen die sleeve between cushion block 4
17 are sleeved on the lateral wall of cushion block 4, and the lateral wall top for strengthening die sleeve 17 opens up limiting shoulder, and restoring board 16 is installed on reinforcement
It is connect on the limiting shoulder of die sleeve 17 and by multiple die sleeve fixing screws 13 with strengthening die sleeve 17, strengthens die sleeve 17 and die holder
Multiple release links 3 and Duo Gen guide posts 19 are respectively equipped between 1, the upper end of each release link 3 passes through restoring board 16, positioned at restoring board
A washer 5 and a nut 6, lower end and the die holder 1 of each release link 3 are respectively equipped in each release link 3 of 16 upper ends
Connection, and there are one resetting spring 2, multiple guide sleeves for set in each release link 3 strengthened between die sleeve 17 and die holder 1
15 are inserted into from the bottom to top on restoring board 16, and the upper slidable of every guide post 19 is mounted on restoring board 16, every guide post 19
Lower part connect with die holder 1, cavity plate 14 be mounted on strengthen die sleeve 17 in, and cavity plate 14 with strengthen die sleeve 17 pass through interference fit
Hot charging technique assembling is integral, and lower core model 7 is mounted in cavity plate 14.
The madial wall of clamping plate 12 is equipped with stepped hole, and upper core model 8 is from top to bottom installed in the stepped hole of clamping plate 12, upper mold
Plate 11, backing plate 9 and clamping plate 12 are from top to bottom arranged and are connected by multiple cope plate fixing screws 10 successively, and upper core model 8 is located at
The surface of lower core model 7 is equipped with metal powder metallurgy powder between 14 inner cavity of lower core model 7 and cavity plate.
Specific embodiment seven：The present embodiment will be described with reference to Fig. 1, the upper core model 8 of present embodiment and cavity plate 14 and under
The unilateral fit clearance of core model 7 is 0.02~0.03mm, when lower core model 7 is attached in cavity plate 14, it is 0.02 that fit clearance is unilateral~
0.03mm, and pass through the connection of resetting spring 2 and restoring board 16, cavity plate 14 is made to be moved up and down with strengthening die sleeve 17.So set
It puts, it is simple in structure, it is easy to implement cavity plate 14 and is moved up and down with strengthening die sleeve 17.Other compositions and connection relation and specific implementation
Mode six is identical.
Specific embodiment eight：The present embodiment will be described with reference to Fig. 1, is adopted between the lower core model 7 of present embodiment and cushion block 4
With clearance fit ensure gap it is unilateral be 0.01~0.025mm.So set, convenient for ensureing to squeeze precision.Other compositions and company
It is identical with specific embodiment six or seven to connect relationship.
Specific embodiment nine：The present embodiment will be described with reference to Fig. 1, and the cavity plate 14 of present embodiment is recessed for annulus column
Mould.So set, convenient for squeezing out lateral wall as circular jet pipe.Other compositions and connection relation and specific embodiment six,
Seven or eight is identical.
Specific embodiment ten：The present embodiment will be described with reference to Fig. 1, and the internal diameter and outer diameter of the cavity plate 14 of present embodiment are same
Axis.So set, convenient for ensureing to squeeze precision.Other compositions and connection relation and specific embodiment six, seven, eight or nine phases
Together.
Specific embodiment 11：The present embodiment will be described with reference to Fig. 1, and the quantity of multiple guide sleeves 15 of present embodiment is
2, two guide sleeves 15 are symmetrical arranged relative to the central axis of restoring board 16, and are attached using interference fit.So set
It puts, ensures to squeeze precision.Other compositions and connection relation are identical with specific embodiment six, seven, eight, nine or ten.
Specific embodiment 12：The present embodiment will be described with reference to Fig. 1, and the quantity of the guide post 19 of present embodiment is 2,
With being set at two 19 opposite positions of guide post there are two lower guide pillar hole on die holder 1, the lower end of guide post 19 under die holder 1 with leading
Post holes is interference fitted.It is accurately positioned and connects so set, being provided for guide post.Other compositions and connection relation and specific embodiment party
Formula six, seven, eight, nine, ten or 11 are identical.
The upper die component of present embodiment is arranged on by upper core model on clamping plate, and centre is equipped with backing plate, and passes through on multiple M16
Template fixing screws 10 are fixed on cope plate, and aforementioned four part can be removable by multiple M16 cope plates fixing screws 10
Unload connection (being detachably connected in present embodiment using screw).Lower mold assemblies by cavity plate, strengthen die sleeve, restoring board, pass through M12
Screw is fixed, and cushion block connect bolt 18 by multiple die holders with die holder and is attached.Mold using the present invention, into
Jet pipe part (see Fig. 2) outer diameter after type is φ 36mm, outer diameter is φ 30mm, internal diameter is φ 9mm and 27 ° of cone angles of band, high 46mm.
The hot-extrusion mold negative molding material of present embodiment is Gr12MV, upper core model and lower core model material are Gr6WV.
The negative molding material quenching hardness of present embodiment is HRC60~62, and upper core model and lower core model material quenching hardness are
HRC54~56.
The connection of the resetting spring and restoring board of present embodiment can be such that cavity plate is moved up and down with strengthening die sleeve.
Present embodiment is by cavity plate with after reinforcement die sleeve assembling, being assembled with restoring board, and pass through M12 screws and consolidated
It is fixed, by the elastic working principle of resetting spring, make cavity plate that can be moved up and down with strengthening die sleeve.
It is 0.01~0.025mm that the lower core model of present embodiment is unilateral with cushion block fit clearance, and internal diameter, the outer diameter of cavity plate are same
Axis degree is 0.01mm.
Present embodiment by the processing dimension tolerance design of lower core model and cushion block part into unilateral gap for 0.01~
The fit tolerance size of 0.025mm, to ensure that lower core model being capable of proper motion after being assembled with cushion block.
The cavity plate of present embodiment uses hot charging technique with strengthening die sleeve using interference fit.
The cavity plate of present embodiment and the fit tolerance for strengthening using between die sleeve are interference fits, and part adds if do not used
Thermal technology's process can not assemble integral.
The metal powder metallurgy material of present embodiment needs pre-molding blank.
The hot extrusion blank of present embodiment is that metal powder metallurgy blank forming die is mounted on 100t hydraulic presses
Afterwards, metal powder metallurgy powder is placed by funnel in die cavity and suppressed.
Operation principle：Molding metal powder metallurgy jet pipe part as needed, mold are equipped with upper core model, cavity plate, lower core
Mould and other auxiliary components, and they are assembled into a complete hot-extrusion mold.The mold is mounted on 160t hydraulic presses
On, and die holder is fixed on the work top of hydraulic press, upper die component is fixed on the upper slide of hydraulic press (with setting
Standby startup, upper die component move up and down together with upper slide, and it is impulse stroke to move downward, and it is idle running to move upwards), according to
Mold is closed height and determines stroke (the complete joint product pattern of workpiece of being subject to).Before part heat extrusion forming, first by metal powder
Metallurgical material is pressed into jet pipe blank by mold in advance, then by being carried out after being heated to certain temperature to blank, is placed into cavity plate
Die cavity in, click switch, move downward the upper slide of equipment.First, the upper core model downlink of upper die component and lower module
Part, which is pressed against, to be closed, and (during upper die component continues traveling downwardly, the sub-assembly first with cavity plate and reinforcement die sleeve presses, Ran Houshang
The sub-assembly of membrane module and cavity plate and reinforcement die sleeve continues traveling downwardly the relative upward movement for generating lower core model and cavity plate, makes jet pipe zero
Part is improved the uniformity of the global density of jet pipe part by two-way axis extruding force).Open the playback of hydraulic press upper slide uplink
Afterwards, the lower oil cylinder uplink for starting hydraulic press pushes the lower core model of lower mold assemblies to eject jet pipe part outside cavity plate, completes to squeeze pressure
Type works.
Claims (10)
1. a kind of moulding technique of engine jet pipe, it is characterised in that：It includes the following steps：
Step 1: stock：
First：Iron powder is annealed：
The iron powder of no annealing in 700~750 DEG C of protection of ammonia stove is subjected to deoxidation processing, 1.5~2h is kept the temperature, goes out furnace temperature
Degree must not exceed 200 DEG C；
Second：Sieving：
Iron powder after cooling of coming out of the stove carried out -150 mesh of 60 mesh sieve；
Third：Dispensing：
According to the total weight of a batch mixing, the weight of each raw material is calculated by ratio requirement；
4th：Batch mixing：
The powder for completing proportioning is encased in batch mixer with 3~4h of speed batch mixing of 20~30r/min；
5th：It is sieved again：
Mixed powder carried out 60 mesh sieve again, removed caking impurity；
Step 2: equipment prepares：
First：Equipment debugging；
Second：Installation mold；
It is Step 3: preforming：
First：Claim single-piece material, weighing is required by weight with balance；
Second：It is die-filling, powder is attached in mold with funnel；
Third：Pre-profiling, mold are pressed onto position；
4th：Depanning；
5th：Clear up overlap；
6th：Mounted box；
Step 4: sintering：
The blank loading box interior sealing made preforming in step 3 is good, it is sent into sintering fire door, when blank is run in stove
During in 1100~1150 DEG C of high temperature section, 1.5~2h is sintered, until tapping temperature is 650~750 DEG C；
Step 5: hot extrusion molding：
It the blank that 650~750 DEG C of temperature come out of the stove will be sintered to was put into extrusion molding dies in 1 minute and is pressed into place, squeezed
Parts density afterwards is >=7.8/g.cm3, and reach final size requirement；
Step 6: quenching treatment：
The extrusion of depanning is put into oil and is cooled down；
Step 7: lonneal：
Extrusion molding after be jet pipe part, jet pipe part is put into 200~300 DEG C of heat-treatment furnaces, heat preservation 1~1.5h into
Row temper；
Step 8: finishing：
10 holes of φ and outer diameter are machined by pattern；
Step 9: phosphorating treatment：
Jet pipe part after mechanical processing carries out phosphorating treatment by phosphatization requirement.
2. a kind of moulding technique of engine jet pipe according to claim 1, it is characterised in that：It is sent into step 4
It is sintered in fire door, bringing-up section temperature is 600 DEG C.
3. a kind of moulding technique of engine jet pipe according to claim 2, it is characterised in that：Work as hair in step 4
When base is run in stove in 1100~1150 DEG C of high temperature section, 1.5~1.8h is sintered, until tapping temperature is 650~750 DEG C.
4. a kind of moulding technique of engine jet pipe according to claim 2, it is characterised in that：It is sent into step 4
To coming out of the stove in sintering fire door, overall process sintering time is 3-4h.
5. a kind of moulding technique of engine jet pipe according to claim 2, it is characterised in that：It will spray in step 7
Tube components are put into 200~300 DEG C of heat-treatment furnaces, and after keeping the temperature 1~1.5h, furnace cooling to room temperature carries out temper.
6. a kind of molding die used in moulding technique of engine jet pipe, it is characterised in that：It includes die holder
(1), cushion block (4), lower core model (7), upper core model (8), backing plate (9), cope plate (11), clamping plate (12), cavity plate (14), restoring board
(16), strengthen die sleeve (17), multiple resetting springs (2), multiple release links (3), multiple washers (5), multiple nuts (6), multiple
Cope plate fixing screws (10), multiple die sleeve fixing screws (13), multiple guide sleeves (15), multiple die holders connection bolt (18) and
More guide posts (19),
The upper surface middle part position of die holder (1) opens up die holder groove, and cushion block (4) is in die holder groove, die holder
(1) bolt (18) is connect by multiple die holders to connect, strengthen die sleeve (17) on die holder (1) between cushion block (4),
And strengthen die sleeve (17) and be sleeved on the lateral wall of cushion block (4), the lateral wall top for strengthening die sleeve (17) opens up limiting shoulder, multiple
Position plate (16) is installed on the limiting shoulder for strengthening die sleeve (17) and by multiple die sleeve fixing screws (13) with strengthening die sleeve
(17) it connects, strengthens being respectively equipped with multiple release links (3) and more guide posts (19) between die sleeve (17) and die holder (1), each
The upper end of release link (3) passes through restoring board (16), and one is respectively equipped in each release link (3) of restoring board (16) upper end
Washer (5) and a nut (6), the lower end of each release link (3) are connect with die holder (1), and positioned at strengthen die sleeve (17) and
It is covered there are one resetting spring (2) in each release link (3) between die holder (1), multiple guide sleeves (15) to insert from the bottom to top
On restoring board (16), the upper slidable of every guide post (19) is mounted on restoring board (16), the lower part of every guide post (19)
It is connect with die holder (1), cavity plate (14) is interior mounted on die sleeve (17) is strengthened, and cavity plate (14) passes through interference with strengthening die sleeve (17)
Coordinating hot charging technique assembling integrally, lower core model (7) is interior mounted on cavity plate (14),
The madial wall of clamping plate (12) is equipped with stepped hole, and upper core model (8) is from top to bottom installed in the stepped hole of clamping plate (12), on
Template (11), backing plate (9) and clamping plate (12) are from top to bottom arranged and are connected by multiple cope plate fixing screws (10) successively, on
Core model (8) is equipped with metal powder metallurgy powder between the surface of lower core model (7), lower core model (7) and cavity plate (14) inner cavity.
7. molding die used in a kind of moulding technique of engine jet pipe according to claim 6, feature
It is：The unilateral fit clearance of upper core model (8) and cavity plate (14) and lower core model (7) is 0.02~0.03mm, and lower core model (7) is attached to
When cavity plate (14) is interior, unilateral fit clearance is 0.02~0.03mm, and passes through the connection of resetting spring (2) and restoring board (16),
Cavity plate (14) is made to be moved up and down with strengthening die sleeve (17).
8. molding die used in a kind of moulding technique of engine jet pipe according to claim 7, feature
It is：Be gap-matched between lower core model (7) and cushion block (4) ensure gap it is unilateral be 0.01~0.025mm.
9. molding die used in a kind of moulding technique of engine jet pipe according to claim 8, feature
It is：Cavity plate (14) is annulus column cavity plate.
10. molding die used in a kind of moulding technique of engine jet pipe according to claim 9, feature
It is：The internal diameter and outer diameter of cavity plate (14) are coaxial.
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| CN112475297B (en) * | 2020-11-10 | 2023-01-03 | 烟台市红森林节能环保科技有限公司 | Device and method for hot extrusion of deep tubular mechanical parts by reduced iron powder |
| CN115945687A (en) * | 2022-12-28 | 2023-04-11 | 北京浦然轨道交通科技股份有限公司 | A cavity mold, friction body, and brake shoe preparation method |
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| EP0532598B1 (en) * | 1990-06-05 | 1995-08-30 | Asea Brown Boveri Ab | Method of manufacturing tubes |
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