CN107774852B - 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
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- CN107774852B CN107774852B CN201711240864.0A CN201711240864A CN107774852B CN 107774852 B CN107774852 B CN 107774852B CN 201711240864 A CN201711240864 A CN 201711240864A CN 107774852 B CN107774852 B CN 107774852B
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- forging
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- compressor blade
- void
- compressor
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- 238000005242 forging Methods 0.000 claims abstract description 138
- 238000000034 method Methods 0.000 claims abstract description 72
- 239000011800 void material Substances 0.000 claims abstract description 47
- 230000000903 blocking effect Effects 0.000 claims abstract description 40
- 239000000446 fuel Substances 0.000 claims abstract description 29
- 238000010438 heat treatment Methods 0.000 claims description 18
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 9
- 238000000465 moulding Methods 0.000 abstract description 14
- 230000007547 defect Effects 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000001125 extrusion Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 230000001788 irregular Effects 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000001914 calming effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000012163 sequencing technique Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
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 present invention provides a kind of compressor blade forging process for fuel forming methods.A kind of compressor blade forging process for fuel forming method of the invention includes the following steps: that 1) compressor blade blank is preforming, obtains blocking blade；2) the blocking blade by step 1) after preforming cuts void by mold cavity outer profile approximation；3) the blocking blade after step 2) to be cut to void carries out finish forging.Compressor blade forging process for fuel forming method of the invention, after preformed, compressor blade forging approximation Die cavity profile is cut into void, forging forced area when reducing forging, open die forging base is excluded simultaneously because the pre- forging type chamber gabarit of blank differs greatly bring die forging fold defect, convenient for the further forging molding of forging.Compressor blade forging process for fuel forming method of the invention, reduces projected area in 0.45m2Or more compressor blade forging forging difficulty.
Description
Technical field
The invention belongs to blade forming technical fields, are related to a kind of compressor blade forging process for fuel forming method, especially relate to
And a kind of biggish compressor blade forging process for fuel forming method of projected area more particularly to a kind of projected area are in 0.45m2And
Above compressor blade forging process for fuel forming method.
Background technique
The characteristics of compressor blade forging usually has chord width wider, blade thinner thickness, molding difficulty are larger.With combustion engine
Continuous development, gas compressor moving blade first-level blade contour dimension is also increasing.
Currently, most of compressor blades pass through forging molding.When forging, because blank is open die forging shaping forming, with
Forging shape difference is larger.During blade forming, forging shape is in irregular shape, and forging each section completes molding time
Sequencing is different, is easy to generate folding in blade, while after forging is full of mold cavity, required hitting power increases sharply,
Forging thickness direction wants to continue forming, and meets process requirements, more difficult within the scope of centainly forging striking capabilities.Size it is continuous
Become larger, also brings the increasing of forging molding difficulty.Size is bigger, usually forges bigger, the required hitting power of projected area
Bigger, and usually manufacturer forging equipment is certain, for hitting power maximum value also with regard to restricted requirement, conventional forging method can not be
Within the scope of certain hitting power, larger blade forging is forged.
CN103028693A discloses a kind of precision forged blade preformation method, and using finish forge mould, mold includes formed punch, left
Insert, right insert, bar are put into mold；Forging deforms twice in extrusion die, is designed by unique bell mouth shape, by material
Material gathers at boss, and mold is mounted on 160 tons of crank presses, which has ejecting function, can be by left insert and the right side
Insert is ejected from mold base, facilitates pickup, using kerosene blastburne, mold is heated between 180 DEG C -300 DEG C, bar material
For GH4169 alloy, it is heated to 1020 DEG C, heating parameters are 1 minute/millimeter, lubricate mould using colloidal graphite mixed with water when forging
Chamber, bar control in 7 seconds from the extrusion forming time is fetched into furnace.When the forming method of the invention can solve extrusion finish-forging
Occur pulling in blade and scrap, saves material 10% according to traditional extrusion, meanwhile, this method reduce when forging finish-forging
Requirement to equipment hitting power.
But currently, especially projected area is in 0.45m for large-sized compressor blade2Or more compressor
The forging of blade forging has that difficulty is big, molding effect is to be improved.
Summary of the invention
In view of the deficiencies of the prior art, the purpose of the present invention is to provide a kind of compressor blade forging process for fuel molding sides
Method, reducing the effective projected area of forging to reduce hitting power needed for forging molding reduces projected area in 0.45m2And
The forging difficulty of above compressor blade forging.
To achieve this purpose, the present invention adopts the following technical scheme:
A kind of compressor blade forging process for fuel forming method, includes the following steps:
1) compressor blade blank is preforming, obtains blocking blade；
2) the blocking blade by step 1) after preforming cuts void by mold cavity outer profile approximation；
3) the blocking blade after step 2) to be cut to void carries out finish forging.
It is described preforming in step 1) specifically comprises the processes of: compressor blade blank is put into mold through One-time forging
It is preforming, obtain blocking blade.Preliminary preforming by the way that blank to be put into mold, preforming forging thickness is than finish-forging part
The big 10mm or more of thickness, different leaves and blank structure difference can difference have been forged when preforming forging reaches this thickness
Equipment hitting power reaches substantially to equipment maximum hitting power, and preforming forging type cavity portion position has formed substantially at this time.Wherein, a fire
The technological parameter of forging such as common process, details are not described herein.
In step 2), it is described cut it is empty specifically comprises the processes of: blocking blade blade is cut through step by void by water knife or laser
2) after cutting void, the width of the blade of the blocking blade after cutting void reduces the 30~40% of the blade width of compressor blade, example
As width reduces 30%, 31%, 32%, 33%, 34%, 35%, 36%, 37%, 38%, 39%, 40%.Forging after cutting void
One week profile of part, compared with mold cavity boundary, reduce one fixed width W, revaluate according to currently with forging thickness decision, generally take
30% or more of forging blade width.
Wherein, in the present invention, the void of cutting refers to: by one week profile of mold cavity, shrinking one to type chamber internal direction
Set a distance forms new forging outer profile, cuts off the part outside preforming forging profile within forging outer profile one week new along this.
In step 3), the finish forging specifically comprises the processes of: will cut be put into after the heating of empty forging mold cavity continue at
Overlap is uniformly discharged type.It will be put into mold cavity after empty forging heating will be cut, at this time because forging will on the basis of preforming
Cut within forging one week void, i.e., forging is reduced with the area that mold directly contacts, directly reduce the forging continue to form it is required
Hitting power, and cutting void is that void is cut according to one week profile of mold cavity, continues to form when cutting empty forging, in the substantially uniform row of overlap
Out, forging molding terminates.
Further, in step 3), the temperature of the heating is 400~500 DEG C, such as heating temperature is 400 DEG C, 410
℃、420℃、430℃、440℃、450℃、460℃、470℃、480℃、490℃、500℃。
Compared with prior art, the invention has the benefit that
Compressor blade forging process for fuel forming method of the invention, after preformed, by compressor blade forging approximation mould
Tool type chamber profile cuts void, forging forced area when reducing forging, while excluding open die forging base because of the pre- forging type chamber gabarit of blank
The bring that differs greatly die forging fold defect, convenient for the further forging molding of forging, through compressor blade forging of the invention
Compressor blade after method for forging and molding forging, with good performance, it is biggish to solve projected area, especially projects
Area is in 0.45m2Or more compressor blade forging process for fuel equipment hit hypodynamic problem.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the mold of compressor blade of the invention；
Fig. 2 is the structural representation of the blocking blade after compressor blade forging process for fuel forming method of the invention is preforming
Figure；
Fig. 3 is the structural schematic diagram that imaginary component is cut when cutting void through compressor blade forging process for fuel forming method of the invention；
Fig. 4 is the structural schematic diagram of the forging after compressor blade forging process for fuel forming method of the invention cuts void；
When Fig. 5 is compressor blade forging process for fuel forming method finish-forging of the invention, forging is cut after void in the type chamber of mold
In structural schematic diagram.
Appended drawing reference is as follows:
1- leaf positions lug；2- blade；3- blade root；4- blocking blade；5- blocking blade cuts imaginary component；6- is forged after cutting void
Part；7- is placed in the forging after cutting void in mold.
Specific embodiment
1-5 with reference to the accompanying drawing, and pass through specific embodiment to further illustrate the technical scheme of the present invention.
The mold 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 work compressor blade after molding includes that leaf positions lug 1, blade 2 and blade root 3.Through compressor blade of the 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 cutting void through compressor blade forging process for fuel forming method of the invention
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, to reduce forging
Hitting power needed for causing type makes forging can continue to thin, meets process requirements, moreover it is possible to eliminate because open die forging base is in forging
The fold defect of upper generation.Forging 6 is as shown in figure 4, forging is placed in mold cavity shown in FIG. 1 after void then will be cut after cutting void
Carry out finish-forging, be placed in mold cut void after forging 7 as shown in figure 5, being further processed into calming the anger for required irregular shape
Machine blade.
Compressor blade forging process for fuel forming method of the invention, includes the following steps:
1) compressor blade blank is preforming, obtains blocking blade；
2) the blocking blade by step 1) after preforming cuts void by mold cavity outer profile approximation；
3) the blocking blade after step 2) to be cut to void carries out finish forging.
Embodiment 1
The compressor blade forging process for fuel forming method of the present embodiment, includes the following steps:
1) compressor blade blank is put into mold preforming through One-time forging, obtains blocking blade；
2) blade of blocking blade is cut by void by water knife or laser, the blocking blade after step 2) cuts void, after cutting 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 form, the temperature of heating is 400 DEG C, and overlap is uniformly arranged
Out, compressor blade is obtained.
Embodiment 2
The compressor blade forging process for fuel forming method of the present embodiment, includes the following steps:
1) compressor blade blank is put into mold preforming through One-time forging, obtains blocking blade；
2) blade of blocking blade is cut by void by water knife or laser, the blocking blade after step 2) cuts void, after cutting 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 form, the temperature of heating is 450 DEG C, and overlap is uniformly arranged
Out, compressor blade is obtained.
Embodiment 3
The compressor blade forging process for fuel forming method of the present embodiment, includes the following steps:
1) compressor blade blank is put into mold preforming through One-time forging, obtains blocking blade；
2) blade of blocking blade is cut by void by water knife or laser, the blocking blade after step 2) cuts void, after cutting 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 form, the temperature of heating is 440 DEG C, and overlap is uniformly arranged
Out, compressor blade is obtained.
Embodiment 4
The compressor blade forging process for fuel forming method of the present embodiment, includes the following steps:
1) compressor blade blank is put into mold preforming through One-time forging, obtains blocking blade；
2) blade of blocking blade is cut by void by water knife or laser, the blocking blade after step 2) cuts void, after cutting 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 form, the temperature of heating is 470 DEG C, and overlap is uniformly arranged
Out, compressor blade is obtained.
Embodiment 5
The compressor blade forging process for fuel forming method of the present embodiment, includes the following steps:
1) compressor blade blank is put into mold preforming through One-time forging, obtains blocking blade；
2) blade of blocking blade is cut by void by water knife or laser, the blocking blade after step 2) cuts void, after cutting 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 form, the temperature of heating is 420 DEG C, and overlap is uniformly arranged
Out, compressor blade is obtained.
Embodiment 6
The compressor blade forging process for fuel forming method of the present embodiment, includes the following steps:
1) compressor blade blank is put into mold preforming through One-time forging, obtains blocking blade；
2) blade of blocking blade is cut by void by water knife or laser, the blocking blade after step 2) cuts void, after cutting 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 form, the temperature of heating is 500 DEG C, and overlap is uniformly arranged
Out, compressor blade is obtained.
The projected area of compressor blade made from embodiment 1-6 is in 0.45m2More than, compressor blade of the invention
Compressor blade forging approximation Die cavity profile after preformed, cut void, forged when reducing forging by forging process for fuel forming method
Part forced area, while excluding open die forging base because the pre- forging type chamber gabarit of blank differs greatly bring die forging fold defect,
Convenient for the further forging molding of forging.Compressor blade forging process for fuel forming method of the invention reduces forging and effectively throws
Shadow area reduces projected area in 0.45m to reduce hitting power needed for forging molding2Or more compressor blade forging
The forging difficulty of part.
Above embodiments are only used to illustrate method detailed of the invention, and the invention is not limited to above-mentioned method detaileds, i.e.,
Do not mean that the invention must rely on the above detailed methods to implement.It should be clear to those skilled in the art, right
Any improvement of the invention, the addition of equivalence replacement and auxiliary element to each raw material of product of the present invention, the selection of concrete mode
Deng all of which fall within the scope of protection and disclosure of the present invention.
Claims (1)
1. a kind of projected area is in 0.45m2Or more compressor blade forging process for fuel forming method, which is characterized in that including such as
Lower step:
1) compressor blade blank is put into preforming through One-time forging in mold, obtains blocking blade；After step 1) is preforming
Blocking blade thickness it is 10mm or more bigger than finish-forging part thickness；
2) blade of the blocking blade by water knife or laser by step 1) after preforming cuts void by mold cavity outer profile approximation,
The width of the blade of blocking blade after cutting void reduces the 30~40% of the blade width of compressor blade；
3) mold cavity is put into after 400~500 DEG C of blocking blade heating after step 2) to be cut to void to continue to form, overlap is uniform
Discharge carries out finish forging.
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 |
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| Publication Number | Publication Date |
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| CN107774852A CN107774852A (en) | 2018-03-09 |
| CN107774852B true CN107774852B (en) | 2019-12-03 |
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| CN114505430B (en) * | 2021-12-15 | 2024-09-13 | 陕西宏远航空锻造有限责任公司 | Forging method of split forging die for changing hit area of forging |
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| 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 for crankshaft forgings |
| CN100396434C (en) * | 2005-05-10 | 2008-06-25 | 南阳二机石油装备(集团)有限公司 | Integral forging method for mfg. petroleum double-arm lifting-ring |
| CN100450686C (en) * | 2006-10-19 | 2009-01-14 | 杨龙兴 | Wire electrode cutting process of steam turbine blade |
| CN103028693B (en) * | 2011-09-29 | 2016-01-27 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of finish forge blade preformation method |
| CN105312483B (en) * | 2015-12-03 | 2017-04-19 | 中国南方航空工业(集团)有限公司 | Method for forging beryllium bronze blade of engine |
| CN105803259B (en) * | 2016-04-26 | 2017-12-08 | 沈阳中钛装备制造有限公司 | Tank titanium alloy balance arm |
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