CN105290285A - Manufacturing method for directly forming blade forging piece through extrusion - Google Patents
Manufacturing method for directly forming blade forging piece through extrusion Download PDFInfo
- Publication number
- CN105290285A CN105290285A CN201510810432.3A CN201510810432A CN105290285A CN 105290285 A CN105290285 A CN 105290285A CN 201510810432 A CN201510810432 A CN 201510810432A CN 105290285 A CN105290285 A CN 105290285A
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- CN
- China
- Prior art keywords
- blade
- die
- drift
- extrusion
- extrusion molding
- 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.)
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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
- B21J5/02—Die forging; Trimming by making use of special dies ; Punching during forging
- B21J5/022—Open die forging
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J13/00—Details of machines for forging, pressing, or hammering
- B21J13/02—Dies or mountings therefor
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Forging (AREA)
Abstract
The invention relates to a manufacturing method of a blade forging piece, in particular to a manufacturing method for directly forming a blade forging piece through extrusion. According to the technical scheme of the manufacturing method, the blade forging piece is composed of a blade body and a tenon; the manufacturing method includes the following steps that firstly, an extrusion die is prepared, wherein the extrusion die is composed of a left female die, a right female die and a punch; and secondly, a blade is formed through direct extrusion, wherein a heated rectangular blank is placed in the left female die and the right female die, the punch is arranged on the blank, extrusion is conducted through a high-energy and high-speed hammer, and the blade forming piece is directly formed through extrusion. According to the manufacturing method for directly forming the blade forging piece through extrusion, because the number of procedures is small, the number of repeated heating times of the blade forging piece is decreased, the structure and performance of the blade forging piece are higher than those of ordinary formed forge pieces, the internal quality of the blade forging piece is improved, the production period is shortened, and the production efficiency is improved.
Description
Technical field
The present invention relates to a kind of manufacture method of blade forging, be specifically related to the manufacture method of the direct extrusion molding of a kind of blade forging.
Background technology
A kind of GH2787 alloy vane forging, be characterized in that blade torsional angle is large, blade profile is thin, front and rear edge thickness is little, the alloying level of blade material is high, in addition the subsequent handling of blade accessory processing is cold roll milling technology, all very high to the allowance of blade forging, dimensional accuracy and surface quality requirements, these factors all increase the difficulty of blade forging forging and molding.In prior art, blade forging is all the technical process adopting first base forging and molding again, and frock quantity is many, and the manufacturing cycle is long, and cost is high.Existing blade forging precision forging technology flow process is: cylindrical blank, and------------heat treatment---Physico-chemical tests---examines payment to trimming eventually for whole shaping tenon and blade for extruded rhombus blade and tenon.
Summary of the invention
The invention provides the manufacture method of the direct extrusion molding of a kind of blade forging, because operation is few, decrease the number of times that blade forging heats repeatedly, make the tissue of blade forging, performance higher than the forging of common shaping, improve the inherent quality of blade forging, shorten the production cycle, improve production efficiency.
Technical scheme of the present invention is as follows:
A manufacture method for the direct extrusion molding of blade forging, wherein blade forging is made up of blade and tenon, and this manufacture method comprises the steps:
One, the preparation of extrusion die: extrusion die is made up of left die, right die and drift, the extrusion die die cavity be made up of left die and right die comprises blade type and tenon type, the shape of extrusion die die cavity is consistent with the shape of blade part, blade molded dimension is that the blade size of blade part adds single-sided process surplus 0.3mm ~ 0.5mm, and tenon molded dimension is that the tenon size of blade part adds single-sided process surplus 1.5mm ~ 2.0mm; Drift is rectangle, drift and left die, right die matched in clearance, and the length of drift targeting part is no less than 1/2 of drift total length;
Two, direct extrusion molding blade: the rectangle blank after heating is put into left die and right die, described drift is placed on blank, utilizes high-energy-rate foging to extrude, direct extrusion molding blade forging.
The manufacture method of the direct extrusion molding of described blade, its preferred version is, the gap between drift and left die and right die is 0.05 ~ 0.10mm.
The manufacture method of the direct extrusion molding of described blade, its preferred version is, high-energy-rate foging is that 20KNm drains the oil formula liquid pneumatic hammer fast.
The manufacture method of the direct extrusion molding of described blade, its preferred version is, blank is that shaped steel or bar flattening cutting stock are produced.
The manufacture method of the direct extrusion molding of described blade, its preferred version is, left die and right negative molding material are 4Cr5W2VSi, HRC=50 ~ 55; Drift material is W18Cr4V, HRC=54 ~ 57.
Beneficial effect of the present invention is as follows:
1, the blade forging of manufacturing process production of the present invention, compared with traditional die-forging forming forging: 1) only need one set of die, save 4 cover frocks (squeezing bar, heading, blocking, shaving die), saved Making mold expense, shortened the production cycle; 2) material consumption 0.5 kilogram saved by single piece vanes forging; 3) decrease the number of times of blade repeated heating, make the tissue of blade forging, performance higher than the forging of common shaping, improve the inherent quality of blade forging.
2, the equipment of direct extruded blade is high-energy-rate foging, and extrusion process is a kind of deformation technique of metal three dimension stress, and therefore it is a kind of forming technology needing deformation force maximum in flow of metal.It is more difficult that other low speed forging equipment realizes extrusion molding.High-energy-rate foging extruding blade can adopt one set of die, and once heat, once-forming method squeezes out half finish forge blade of little surplus.High-energy-rate foging extruding blade, fiber is along blade profile genesis analysis, consistent with blade working state lower stress direction, and stress is good, therefore improves the service life of blade.
3, drift when each extruding by operator by hand mode of operation put into left and right die, this structure operation is convenient, prevents due to equipment attrition, and gap increases causes drift and die dislocation.
4, the blank extruding blade adopts shaped steel or bar to flatten cutting stock and produces, and be applicable to the extrusion molding of blade, the blade forging surface quality obtained is good, dimensional accuracy is high, and the mold use life-span is extended.
Accompanying drawing explanation
Fig. 1 is extrusion die structure chart;
Fig. 2 is A-A sectional view in Fig. 1.
Detailed description of the invention
As shown in Fig. 1 ~ 2, the manufacture method of the direct extrusion molding of a kind of blade forging, wherein blade forging is made up of blade and tenon, and this manufacture method comprises the steps:
One, the preparation of extrusion die: extrusion die is made up of left die 1, right die 2 and drift 3, the extrusion die die cavity be made up of left die 1 and right die 2 comprises blade type and tenon type, the shape of extrusion die die cavity is consistent with the shape of blade part, blade molded dimension is that the blade size of blade part adds single-sided process surplus 0.3mm ~ 0.5mm, and tenon molded dimension is that the tenon size of blade part adds single-sided process surplus 1.5mm ~ 2.0mm; Drift 3 is rectangle, drift 3 and left die 1, right die 2 matched in clearance, and the gap between drift 3 and left die 1 and right die 2 is 0.10mm, and the length of drift targeting part is 1/2 of drift 3 total length; Left die 1 and right die 2 material are 4Cr5W2VSi, HRC=50 ~ 55; Drift 3 material is W18Cr4V, HRC=54 ~ 57;
Two, direct extrusion molding blade: the rectangle blank after heating is put into left die 1 and right die 2, blank is structural steel making, described drift 3 is placed on blank, utilizes 20KNm formula liquid pneumatic hammer of draining the oil fast to extrude, direct extrusion molding blade forging.
Claims (5)
1. a manufacture method for the direct extrusion molding of blade forging, is characterized in that, blade forging is made up of blade and tenon, and this manufacture method comprises the steps:
One, the preparation of extrusion die: extrusion die is made up of left die, right die and drift, the extrusion die die cavity be made up of left die and right die comprises blade type and tenon type, the shape of extrusion die die cavity is consistent with the shape of blade part, blade molded dimension is that the blade size of blade part adds single-sided process surplus 0.3mm ~ 0.5mm, and tenon molded dimension is that the tenon size of blade part adds single-sided process surplus 1.5mm ~ 2.0mm; Drift is rectangle, drift and left die, right die matched in clearance, and the length of drift targeting part is no less than 1/2 of drift total length;
Two, direct extrusion molding blade: the rectangle blank after heating is put into left die and right die, described drift is placed on blank, utilizes high-energy-rate foging to extrude, direct extrusion molding blade forging.
2. the manufacture method of the direct extrusion molding of blade according to claim 1, is characterized in that, the gap between drift and left die and right die is 0.05 ~ 0.10mm.
3. the manufacture method of the direct extrusion molding of blade according to claim 1, is characterized in that, high-energy-rate foging is that 20KNm drains the oil formula liquid pneumatic hammer fast.
4. the manufacture method of the direct extrusion molding of blade according to claim 1, is characterized in that, blank is that shaped steel or bar flattening cutting stock are produced.
5. the manufacture method of the direct extrusion molding of blade according to claim 1, is characterized in that, left die, right negative molding material are 4Cr5W2VSi, HRC=50 ~ 55; Drift material is W18Cr4V, HRC=54 ~ 57.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510810432.3A CN105290285A (en) | 2015-11-20 | 2015-11-20 | Manufacturing method for directly forming blade forging piece through extrusion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510810432.3A CN105290285A (en) | 2015-11-20 | 2015-11-20 | Manufacturing method for directly forming blade forging piece through extrusion |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105290285A true CN105290285A (en) | 2016-02-03 |
Family
ID=55188483
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510810432.3A Pending CN105290285A (en) | 2015-11-20 | 2015-11-20 | Manufacturing method for directly forming blade forging piece through extrusion |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105290285A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110756714A (en) * | 2019-11-10 | 2020-02-07 | 中国航发南方工业有限公司 | High-speed extrusion forming die for blades |
| CN110773699A (en) * | 2019-11-10 | 2020-02-11 | 中国航发南方工业有限公司 | Method for controlling extrusion forming residual stress of forged blade |
| CN110773694A (en) * | 2019-11-10 | 2020-02-11 | 中国航发南方工业有限公司 | Die for forging blade |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0446651A (en) * | 1990-06-12 | 1992-02-17 | Agency Of Ind Science & Technol | Manufacture of turbine blade |
| CN102310154A (en) * | 2011-09-20 | 2012-01-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Die in alloy blade precision forging process |
| CN103009018A (en) * | 2011-09-20 | 2013-04-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Manufacture method for ultra-fine grain and high-intensity alloy blade forged piece |
| 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 |
| CN103586391A (en) * | 2013-11-11 | 2014-02-19 | 沈阳黎明航空发动机(集团)有限责任公司 | Extrusion forming method for blade made of GH2787 high-temperature alloy |
| CN104308058A (en) * | 2014-11-07 | 2015-01-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Titanium alloy blade forging forming method |
-
2015
- 2015-11-20 CN CN201510810432.3A patent/CN105290285A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0446651A (en) * | 1990-06-12 | 1992-02-17 | Agency Of Ind Science & Technol | Manufacture of turbine blade |
| CN102310154A (en) * | 2011-09-20 | 2012-01-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Die in alloy blade precision forging process |
| CN103009018A (en) * | 2011-09-20 | 2013-04-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Manufacture method for ultra-fine grain and high-intensity alloy blade forged piece |
| 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 |
| CN103586391A (en) * | 2013-11-11 | 2014-02-19 | 沈阳黎明航空发动机(集团)有限责任公司 | Extrusion forming method for blade made of GH2787 high-temperature alloy |
| CN104308058A (en) * | 2014-11-07 | 2015-01-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Titanium alloy blade forging forming method |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110756714A (en) * | 2019-11-10 | 2020-02-07 | 中国航发南方工业有限公司 | High-speed extrusion forming die for blades |
| CN110773699A (en) * | 2019-11-10 | 2020-02-11 | 中国航发南方工业有限公司 | Method for controlling extrusion forming residual stress of forged blade |
| CN110773694A (en) * | 2019-11-10 | 2020-02-11 | 中国航发南方工业有限公司 | Die for forging blade |
| CN110773699B (en) * | 2019-11-10 | 2021-02-09 | 中国航发南方工业有限公司 | Method for controlling extrusion forming residual stress of forged blade |
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Application publication date: 20160203 |
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