CN107774852A - A kind of compressor blade forging process for fuel forming method - Google Patents
A kind of compressor blade forging process for fuel forming method Download PDFInfo
- Publication number
- CN107774852A CN107774852A CN201711240864.0A CN201711240864A CN107774852A CN 107774852 A CN107774852 A CN 107774852A CN 201711240864 A CN201711240864 A CN 201711240864A CN 107774852 A CN107774852 A CN 107774852A
- Authority
- CN
- China
- Prior art keywords
- forging
- blade
- compressor blade
- void
- forming method
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/002—Hybrid process, e.g. forging following casting
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/02—Die forging; Trimming by making use of special dies ; Punching during forging
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K29/00—Arrangements for heating or cooling during processing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K3/00—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like
- B21K3/04—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like blades, e.g. for turbines; Upsetting of blade roots
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23D—PLANING; SLOTTING; SHEARING; BROACHING; SAWING; FILING; SCRAPING; LIKE OPERATIONS FOR WORKING METAL BY REMOVING MATERIAL, NOT OTHERWISE PROVIDED FOR
- B23D79/00—Methods, machines, or devices not covered elsewhere, for working metal by removal of material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/36—Removing material
- B23K26/38—Removing material by boring or cutting
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Plasma & Fusion (AREA)
- Forging (AREA)
Abstract
The invention provides a kind of compressor blade forging process for fuel forming method.A kind of compressor blade forging process for fuel forming method of the present invention, comprises the following steps：1) compressor blade blank is preforming, obtains blocking blade；2) blocking blade of the step 1) after preforming is cut into void by mold cavity outline approximation；3) step 2) is cut to the blocking blade after void and carries out finish forging.The compressor blade forging process for fuel forming method of the present invention, after preformed, compressor blade forging approximation Die cavity profile is cut into void, forging lifting surface area when reducing forging, open die forging base is excluded simultaneously because the pre- forging die cavity gabarit of blank differs greatly the die forging fold defect brought, is easy to the further forging molding of forging.The compressor blade forging process for fuel forming method of the present invention, reduces projected area in 0.45m2And the forging difficulty of the compressor blade forging of the above.
Description
Technical field
The invention belongs to blade forming technical field, is related to a kind of compressor blade forging process for fuel forming method, especially relates to
And the compressor blade forging process for fuel forming method that a kind of projected area is larger, more particularly to a kind of projected area is in 0.45m2And
Compressor blade forging process for fuel forming method above.
Background technology
Compressor blade forging generally has the characteristics of chord width is wider, blade thinner thickness, and it is larger to be molded difficulty.With combustion engine
Continuous development, gas compressor moving blade first-level blade contour dimension is also increasing.
At present, most of compressor blades pass through forging molding.During forging, because blank is open die forging shaping forming, with
Forging shape difference is larger.During blade forming, forging profile is in irregular shape, and forging each several part completes molding time
Sequencing is different, easily produces folding in blade, while after forging is full of mold cavity, required hitting power increases sharply,
Forging thickness direction wants to continue to be molded, and meets process requirements, more difficult in the range of striking capabilities necessarily forging.Size it is continuous
Become big, also bring the increasing of forging molding difficulty.Size is bigger, generally forges bigger, the required hitting power of projected area
Bigger, and generally manufacturer forging equipment is certain, for hitting power maximum also with regard to restricted requirement, conventional forging method can not be
In the range of certain hitting power, larger blade forging is forged.
CN103028693A discloses a kind of finish forge blade preformation method, and using finish forge mould, mould includes drift, left
Insert, right insert, bar are put into mould；Forging deforms twice in extrusion die, is designed by the bell mouth shape of uniqueness, by material
Material is gathered at boss, and for mould installion on 160 tons of crank presses, the forcing press has ejecting function, can be by left insert and the right side
Insert ejects from mold base, facilitates pickup, using kerosene blastburne, between mould is heated into 180 DEG C -300 DEG C, bar material
For GH4169 alloys, 1020 DEG C are heated to, heating parameters are 1 minute/millimeter, using colloidal graphite mixed with water lubrication mould during forging
Chamber, bar were fetched into extrusion forming time control in 7 seconds from stove.When the forming method of the invention can solve extrusion finish-forging
Occur pulling in blade and scrap, material 10% is saved according to traditional extrusion, meanwhile, when this method reduce forging finish-forging
Requirement to equipment hitting power.
But at present, for large-sized compressor blade, particularly projected area is in 0.45m2And the compressor of the above
The problem of difficulty is big, molding effect has much room for improvement be present in the forging of blade forging.
The content of the invention
In view of the shortcomings of the prior art, it is an object of the invention to provide a kind of compressor blade forging process for fuel shaping side
Method, the effective projected area of forging is reduced, so as to reduce hitting power needed for forging molding, reduces projected area in 0.45m2And
The forging difficulty of compressor blade forging above.
To use following technical scheme up to this purpose, the present invention：
A kind of compressor blade forging process for fuel forming method, comprises the following steps：
1) compressor blade blank is preforming, obtains blocking blade；
2) blocking blade of the step 1) after preforming is cut into void by mold cavity outline approximation；
3) step 2) is cut to the blocking blade after void and carries out finish forging.
In step 1), the preforming concrete technology is：Compressor blade blank is put into mould through One-time forging
It is preforming, obtain blocking blade.Preliminary preforming by the way that blank is put into mould, preforming forging thickness is than finish-forging part
Big more than the 10mm of thickness, different leaves and blank structure are different difference, when preforming forging reaches this thickness, forging
Equipment hitting power reaches substantially to equipment maximum hitting power, and now preforming forging die cavity position has been molded substantially.Wherein, a fire
The technological parameter of forging such as common process, will not be repeated here.
In step 2), it is described cut void concrete technology be：Blocking blade blade is cut through step by void by water knife or laser
2) after cutting void, cut the blade of the blocking blade after void width reduce compressor blade blade width 30~40%, example
As width reduces 30%, 31%, 32%, 33%, 34%, 35%, 36%, 37%, 38%, 39%, 40%.Cut the forging after void
One week profile of part, compared with mold cavity border, reduce one fixed width W, revaluate according to currently with forging thickness decision, typically take
More than the 30% of forging blade width.
Wherein, in the present invention, described void of cutting refers to：By one week profile of mold cavity, one is shunk to die cavity internal direction
Set a distance forms new forging outline, and the forging outline new along this cuts off the part outside preforming forging profile in one week.
In step 3), the concrete technology of the finish forging is：To cut be put into after the heating of empty forging mold cavity continue into
Type, overlap is uniformly discharged.Mold cavity will be put into after empty forging heating will be cut, now because forging will on the basis of preforming
Forging cuts void for one week, i.e., forging is reduced with the area that mould directly contacts, directly reduce the forging continue to be molded it is required
Hitting power, and it is to cut void according to one week profile of mold cavity to cut void, continues to be molded when cutting empty forging, in the substantially uniform row of overlap
Go out, forging shaping terminates.
Further, in step 3), the temperature of the heating is 400~500 DEG C, for example, heating-up temperature is 400 DEG C, 410
℃、420℃、430℃、440℃、450℃、460℃、470℃、480℃、490℃、500℃。
Compared with prior art, beneficial effects of the present invention are：
The compressor blade forging process for fuel forming method of the present invention, after preformed, by compressor blade forging approximation mould
Tool die cavity profile cuts void, forging lifting surface area when reducing forging, while excludes open die forging base because of the pre- forging die cavity gabarit of blank
Differ greatly the die forging fold defect brought, is easy to the further forging molding of forging, the compressor blade forging through the present invention
Compressor blade after method for forging and molding forging, has good performance, and it is larger to solve projected area, particularly projects
Area is in 0.45m2And the compressor blade forging process for fuel equipment of the above hits hypodynamic problem.
Brief description of the drawings
Fig. 1 is the structural representation of the mould of the compressor blade of the present invention；
Fig. 2 is the structural representation of the blocking blade after the compressor blade forging process for fuel forming method of the present invention is preforming
Figure；
Fig. 3 is the structural representation that imaginary component is cut when the compressor blade forging process for fuel forming method through the present invention cuts void；
Fig. 4 is the structural representation of the forging after the compressor blade forging process for fuel forming method of the present invention cuts void；
When Fig. 5 is the compressor blade forging process for fuel forming method finish-forging of the present invention, forging is cut after void in the die cavity of mould
In structural representation.
Reference is as follows：
1- leaves position lug；2- blades；3- blade roots；4- blocking blades；5- blocking blades cut imaginary component；6- is forged after cutting void
Part；The forging after cutting void that 7- is placed in mould.
Embodiment
1-5 below in conjunction with the accompanying drawings, and technical scheme is further illustrated by embodiment.
The mould of compressor blade forging process for fuel forming method of the present invention compressor blade to be processed as shown in figure 1, plus
The structure of compressor blade after work shaping positions lug 1, blade 2 and blade root 3 including leaf.Compressor blade through the present invention
The structure of blocking blade 4 after forging process for fuel forming method is preforming is as shown in Fig. 2 after preformed, substantially close to blade
Irregular shape.Blocking blade cuts the structure of imaginary component 5 when compressor blade forging process for fuel forming method through the present invention cuts void
As shown in figure 3, through step 2) cut it is empty fall part as shown in Figure 3 after, the effective projected area of forging is reduced, so as to reduce forging
The hitting power needed for type is caused, makes forging can continue to thin, meets process requirements, moreover it is possible to is eliminated because open die forging base is in forging
Fold defect caused by upper.Forging 6 is as shown in figure 4, forging is placed in the mold cavity shown in Fig. 1 after void then will be cut after cutting void
Carry out finish-forging, be placed in mould cut void after forging 7 as shown in figure 5, being further processed into calming the anger for required irregular shape
Machine blade.
The compressor blade forging process for fuel forming method of the present invention, comprises the following steps：
1) compressor blade blank is preforming, obtains blocking blade；
2) blocking blade of the step 1) after preforming is cut into void by mold cavity outline approximation；
3) step 2) is cut to the blocking blade after void and carries out finish forging.
Embodiment 1
The compressor blade forging process for fuel forming method of the present embodiment, comprises the following steps：
1) compressor blade blank is put into mould preforming through One-time forging, obtains blocking blade；
2) blade of blocking blade is cut by void by water knife or laser, after step 2) cuts void, cuts the blocking blade after void
Blade width reduce compressor blade blade width 30%；
3) it will cut and be put into mold cavity after the heating of empty forging and continue to be molded, the temperature of heating is 400 DEG C, and overlap is uniformly arranged
Go out, obtain compressor blade.
Embodiment 2
The compressor blade forging process for fuel forming method of the present embodiment, comprises the following steps：
1) compressor blade blank is put into mould preforming through One-time forging, obtains blocking blade；
2) blade of blocking blade is cut by void by water knife or laser, after step 2) cuts void, cuts the blocking blade after void
Blade width reduce compressor blade blade width 32%；
3) it will cut and be put into mold cavity after the heating of empty forging and continue to be molded, the temperature of heating is 450 DEG C, and overlap is uniformly arranged
Go out, obtain compressor blade.
Embodiment 3
The compressor blade forging process for fuel forming method of the present embodiment, comprises the following steps：
1) compressor blade blank is put into mould preforming through One-time forging, obtains blocking blade；
2) blade of blocking blade is cut by void by water knife or laser, after step 2) cuts void, cuts the blocking blade after void
Blade width reduce compressor blade blade width 36%；
3) it will cut and be put into mold cavity after the heating of empty forging and continue to be molded, the temperature of heating is 440 DEG C, and overlap is uniformly arranged
Go out, obtain compressor blade.
Embodiment 4
The compressor blade forging process for fuel forming method of the present embodiment, comprises the following steps：
1) compressor blade blank is put into mould preforming through One-time forging, obtains blocking blade；
2) blade of blocking blade is cut by void by water knife or laser, after step 2) cuts void, cuts the blocking blade after void
Blade width reduce compressor blade blade width 38%；
3) it will cut and be put into mold cavity after the heating of empty forging and continue to be molded, the temperature of heating is 470 DEG C, and overlap is uniformly arranged
Go out, obtain compressor blade.
Embodiment 5
The compressor blade forging process for fuel forming method of the present embodiment, comprises the following steps：
1) compressor blade blank is put into mould preforming through One-time forging, obtains blocking blade；
2) blade of blocking blade is cut by void by water knife or laser, after step 2) cuts void, cuts the blocking blade after void
Blade width reduce compressor blade blade width 33%；
3) it will cut and be put into mold cavity after the heating of empty forging and continue to be molded, the temperature of heating is 420 DEG C, and overlap is uniformly arranged
Go out, obtain compressor blade.
Embodiment 6
The compressor blade forging process for fuel forming method of the present embodiment, comprises the following steps：
1) compressor blade blank is put into mould preforming through One-time forging, obtains blocking blade；
2) blade of blocking blade is cut by void by water knife or laser, after step 2) cuts void, cuts the blocking blade after void
Blade width reduce compressor blade blade width 40%；
3) it will cut and be put into mold cavity after the heating of empty forging and continue to be molded, the temperature of heating is 500 DEG C, and overlap is uniformly arranged
Go out, obtain compressor blade.
The projected area of compressor blade is in 0.45m made from embodiment 1-62More than, compressor blade of the invention
Forging process for fuel forming method, after preformed, compressor blade forging approximation Die cavity profile is cut into void, forged when reducing forging
Part lifting surface area, while open die forging base is excluded because the pre- forging die cavity gabarit of blank differs greatly the die forging fold defect brought,
It is easy to the further forging molding of forging.The compressor blade forging process for fuel forming method of the present invention, reduce forging and effectively throw
Shadow area, so as to reduce hitting power needed for forging molding, projected area is reduced in 0.45m2And the compressor blade forging of the above
The forging difficulty of part.
Above example is only used for the method detailed for illustrating the present invention, the invention is not limited in above-mentioned method detailed, i.e.,
Do not mean that the present invention has to rely on above-mentioned method detailed and could implemented.Person of ordinary skill in the field is it will be clearly understood that right
Any improvement of the present invention, addition, the selection of concrete mode of equivalence replacement and auxiliary element to each raw material of product of the present invention
Deng within the scope of all falling within protection scope of the present invention and disclosing.
Claims (7)
1. a kind of compressor blade forging process for fuel forming method, it is characterised in that comprise the following steps：
1) compressor blade blank is preforming, obtains blocking blade；
2) blocking blade of the step 1) after preforming is cut into void by mold cavity outline approximation；
3) step 2) is cut to the blocking blade after void and carries out finish forging.
2. compressor blade forging process for fuel forming method according to claim 1, it is characterised in that described in step 1)
Preforming concrete technology is：Compressor blade blank is put into mould preforming through One-time forging, obtains blocking blade.
3. compressor blade forging process for fuel forming method according to claim 1 or 2, it is characterised in that pre- through step 1)
The thickness of blocking blade after shaping is bigger more than 10mm than finish-forging part thickness.
4. the compressor blade forging process for fuel forming method according to one of claim 1-3, it is characterised in that step 2)
In, it is described cut void concrete technology be：The blade of blocking blade is cut by void by water knife or laser.
5. compressor blade forging process for fuel forming method according to claim 4, it is characterised in that cut void through step 2)
Afterwards, cut the blade of the blocking blade after void width reduce compressor blade blade width 30~40%.
6. the compressor blade forging process for fuel forming method according to one of claim 1-5, it is characterised in that step 3)
In, the concrete technology of the finish forging is：It will cut and be put into mold cavity after the heating of empty forging and continue to be molded, overlap will uniformly be arranged
Go out.
7. compressor blade forging process for fuel forming method according to claim 6, it is characterised in that the temperature of the heating
For 400~500 DEG C.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711240864.0A CN107774852B (en) | 2017-11-30 | 2017-11-30 | A kind of compressor blade forging process for fuel forming method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711240864.0A CN107774852B (en) | 2017-11-30 | 2017-11-30 | A kind of compressor blade forging process for fuel forming method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107774852A true CN107774852A (en) | 2018-03-09 |
| CN107774852B CN107774852B (en) | 2019-12-03 |
Family
ID=61430058
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711240864.0A Active CN107774852B (en) | 2017-11-30 | 2017-11-30 | A kind of compressor blade forging process for fuel forming method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107774852B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114505430A (en) * | 2021-12-15 | 2022-05-17 | 陕西宏远航空锻造有限责任公司 | Forging method of forging splitting die for changing hitting area of forging piece |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1048994A (en) * | 1989-10-18 | 1991-02-06 | 航空工业部红原锻铸厂 | Large-size steam turbine titanium alloy linear leaf forging and device |
| JP2000197945A (en) * | 1998-12-25 | 2000-07-18 | Sumitomo Metal Ind Ltd | Deburring device of crank shaft forged product |
| CN1861314A (en) * | 2005-05-10 | 2006-11-15 | 南阳二机石油装备(集团)有限公司 | Integral forging method for mfg. petroleum double-arm lifting-ring |
| CN1931496A (en) * | 2006-10-19 | 2007-03-21 | 杨龙兴 | Wire electrode cutting process of steam turbine blade |
| CN103028693A (en) * | 2011-09-29 | 2013-04-10 | 沈阳黎明航空发动机(集团)有限责任公司 | Preforming method for precision forging blades |
| CN105312483A (en) * | 2015-12-03 | 2016-02-10 | 中国南方航空工业(集团)有限公司 | Method for forging beryllium bronze blade of engine |
| CN105803259A (en) * | 2016-04-26 | 2016-07-27 | 沈阳和世泰钛金属应用技术有限公司 | Titanium alloy equilibrium elbow of tank |
-
2017
- 2017-11-30 CN CN201711240864.0A patent/CN107774852B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1048994A (en) * | 1989-10-18 | 1991-02-06 | 航空工业部红原锻铸厂 | Large-size steam turbine titanium alloy linear leaf forging and device |
| JP2000197945A (en) * | 1998-12-25 | 2000-07-18 | Sumitomo Metal Ind Ltd | Deburring device of crank shaft forged product |
| CN1861314A (en) * | 2005-05-10 | 2006-11-15 | 南阳二机石油装备(集团)有限公司 | Integral forging method for mfg. petroleum double-arm lifting-ring |
| CN1931496A (en) * | 2006-10-19 | 2007-03-21 | 杨龙兴 | Wire electrode cutting process of steam turbine blade |
| CN103028693A (en) * | 2011-09-29 | 2013-04-10 | 沈阳黎明航空发动机(集团)有限责任公司 | Preforming method for precision forging blades |
| CN105312483A (en) * | 2015-12-03 | 2016-02-10 | 中国南方航空工业(集团)有限公司 | Method for forging beryllium bronze blade of engine |
| CN105803259A (en) * | 2016-04-26 | 2016-07-27 | 沈阳和世泰钛金属应用技术有限公司 | Titanium alloy equilibrium elbow of tank |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114505430A (en) * | 2021-12-15 | 2022-05-17 | 陕西宏远航空锻造有限责任公司 | Forging method of forging splitting die for changing hitting area of forging piece |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107774852B (en) | 2019-12-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102172755A (en) | Connecting rod manufacturing method capable of improving surface quality of connecting rod of medium-speed/high-speed diesel engine | |
| CN109226618A (en) | Mold is used in the compound Forging Technology of high-power wind turbine main shaft and forging and stamping | |
| CN109226617A (en) | A kind of high-power wind turbine main shaft large flange quick shaping process | |
| CN109676069A (en) | A kind of nozzle body precision forging method | |
| CN106111862A (en) | A kind of forging method of GH4901 sleeve spacer ring | |
| CN107774852B (en) | A kind of compressor blade forging process for fuel forming method | |
| CN103042090B (en) | Turbine runner blade compression-moulding methods | |
| CN101545440B (en) | Method for manufacturing swivel of actuating lever for motorcycle | |
| KR101512164B1 (en) | Manufacturing method of Titanium alloy blade for steam turbine | |
| CN111069492A (en) | Cold-type blank forging method for centrifugal machine | |
| CN107617715A (en) | Close forging technology in automotive hub outer ring | |
| CN105689612A (en) | Near-net forming forging method for novel straight-tooth bevel gear tooth-profile die | |
| CN106040944B (en) | A kind of light-duty slip yoke forging mold and its combined forging technique | |
| CN205324588U (en) | Mould is forged to subdivision formula of bucket tooth | |
| CN117047020A (en) | Free forging forming process on sun gear forging hammer for wind power gear box | |
| CN208357746U (en) | A kind of effective casting mould of diesel exhaust gas for facilitating casting metal liquid to be vented | |
| CN105964846A (en) | Hollow convex tooth type forging and molding method thereof | |
| CN107186140B (en) | A kind of in-flanges tubular high temperature alloy product manufacture method | |
| CN108742790A (en) | A kind of sheet metal structural circumcision stapler resist-nailed seat and preparation method thereof | |
| CN101254517A (en) | Silumin piston contour forging technique and mold | |
| CN103949575A (en) | Gearbox main shaft vertical forging production method and special forging mold | |
| CN101791676A (en) | Integral casting and forging molding process of hoe | |
| CN105880452A (en) | Closed mold and process for producing automotive intake and exhaust flanges by virtue of closed mold | |
| CN105921673A (en) | Method for forging hook forged piece | |
| CN113000754B (en) | Novel process for forging Christmas tree |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |