CN106670365B - A kind of big blade forging surplus compensation method - Google Patents
A kind of big blade forging surplus compensation method Download PDFInfo
- Publication number
- CN106670365B CN106670365B CN201611228892.6A CN201611228892A CN106670365B CN 106670365 B CN106670365 B CN 106670365B CN 201611228892 A CN201611228892 A CN 201611228892A CN 106670365 B CN106670365 B CN 106670365B
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- Prior art keywords
- blade
- surplus
- forging
- rotation
- compensation method
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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
-
- 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
Abstract
The invention discloses a kind of big blade forging surplus compensation methodes, are directed to blade molded line, using thick side high point as rotation center, rotate by a certain angle α °, and direction of rotation is the direction for making thin side surplus increase, the rotation angleVertical spacing distance between Die cavity profiles of the wherein H for theoretical forging profile and after moving horizontally, L is the horizontal distance of rotation center and the thin side overlap cutting edge of blade.Wide string blade significant effect of the above-mentioned big blade forging surplus compensation method to disengaging gas side difference in thickness great disparity.Can effective compensation cause blade surplus uneven because of mold dislocation：The situation that air inlet lateral deviation is thick, outlet lateral deviation is thin.Substantially increase product qualification rate.
Description
Technical field
The invention belongs to big blade forging forming techniques, more particularly, to a kind of wide string of disengaging gas side difference in thickness great disparity
Big blade forging surplus compensation method.
Background technology
Currently, for the wide string blade of disengaging gas side difference in thickness great disparity.It is complete to fill type for each position when in view of die forging, and one
All overlaps are discharged simultaneously and overlap even width.Practical die forging effect disleaf top sharp corner has slight misrun, remaining each position flies
Hem width degree is relatively uniform.It can be seen that the selection of forging corner is reasonable.But it is found in blade after being detected to forging part
Arc surplus is seriously uneven：Same blade section is gradually reduced from air inlet side to gas side, forging surplus is gone out, goes out gas side surplus very
Small or even empty 5~6mm, as shown in Figure 1, Fig. 1 is blade actual profile and theoretical profile contrast schematic diagram.Profile a is zero in figure
Part profile, profile b are theoretical forging profile, and profile c is practical forging profile, it can be seen that from blade root to leaf top with blade into
Go out gas side difference in thickness to become larger, forging material object surplus deviation also becomes larger.
It please refers to shown in Fig. 2 and Fig. 3, Fig. 2 is the stress diagram of forging, and Fig. 3 is the stress diagram of upper mold.To forging
Force analysis is carried out, pressure F of the upper mold to forging one perpendicular to contact surface is decomposed into horizontal direction power Fx and vertical direction power
Fy.Upper mold is decomposed into horizontal direction power Fx ' and vertical direction power Fy ' by reaction force F '.Upper mold is moved to the directions Fx ', is led
Cause the dislocation of upper and lower mould horizontal direction.The directions the Fx ' movement of upper mold can cause forging blade air inlet side surplus obviously to increase, and outlet
Side is since molded line is relatively flat, and surplus is without significant change.But when forging thickness is gradually thinned, air inlet side surplus reaches design value
When, go out gas side surplus with regard to very little, or even void.Therefore since blade inner arc shape determines the horizontal component Fx ' suffered by upper mold very
Greatly, cause upper mold will produce it is larger move horizontally, forging inner arc surplus will be made seriously uneven.Such case is difficult to pass through mode transfer
It is reduced or eliminated, moreover die forging mode transfer is very time-consuming, greatly reduces production efficiency.
Invention content
The purpose of the present invention is to provide a kind of big blade forging surplus compensation methodes, simply and are significantly carried with method
The characteristics of high product qualification rate, exist when solving big blade forging in the prior art because mold dislocation leads to blade surplus not
Equal problem.
For this purpose, the present invention uses following technical scheme：
A kind of big blade forging surplus compensation method is directed to blade molded line, using thick side high point as rotation center, rotation
Turn α ° of certain angle, direction of rotation is the direction for making thin side surplus increase.
Particularly, the rotation angleMolds of the wherein H for theoretical forging profile and after moving horizontally
Vertical spacing distance between cavity profile, L are the horizontal distance of rotation center and the thin side overlap cutting edge of blade.
Particularly, the blade is separated into several grades of molded line, and surplus compensation is carried out for every grade of molded line.
Beneficial effects of the present invention are that the big blade forging surplus compensation method is to passing in and out gas side compared with prior art
The wide string blade significant effect of difference in thickness great disparity.Can effective compensation cause blade surplus uneven because of mold dislocation：Air inlet lateral deviation
Situation thick, outlet lateral deviation is thin.Substantially increase product qualification rate.
Description of the drawings
Fig. 1 is blade actual profile and theoretical profile contrast schematic diagram；
Fig. 2 is the stress diagram of forging；
Fig. 3 is the stress diagram of upper mold；
Fig. 4 is the compensation schematic diagram for the big blade forging surplus compensation method that the specific embodiment of the invention 1 provides.
Specific implementation mode
Technical solution to further illustrate the present invention below with reference to the accompanying drawings and specific embodiments.
It please refers to shown in Fig. 4, Fig. 4 is the big blade forging surplus compensation method that the specific embodiment of the invention 1 provides
Compensate schematic diagram.
In the present embodiment, blade is separated into several grades of molded line, for every by a kind of big blade forging surplus compensation method
Shelves blade molded line rotates by a certain angle α °, direction of rotation is to make thin side surplus using thick side high point as rotation center O
The direction of increasing.The rotation angleMold cavities of the wherein H for theoretical forging profile and after moving horizontally
Vertical spacing distance between profile, i.e. H is according to this forging actual production data or specific forging trial-production data and permission
Die horizontal offsetting amount determine.L is the horizontal distance of rotation center and the thin side overlap cutting edge of blade.
In the present embodiment, it is 350mm to choose blade section, and permission mold offsetting amount is 3mm, when upper mold moves horizontally
When 3mm, H 0.39mm, this section L are 272mm.Therefore
Above example is to elaborate that the basic principle and characteristic of the present invention, the present invention are not limited by above-mentioned example,
Without departing from the spirit and scope, the present invention also has various changes, these changes and modifications are both fallen within
In scope of the claimed invention.The scope of the present invention is defined by the appended claims and its equivalents.
Claims (2)
1. a kind of big blade forging surplus compensation method, which is characterized in that it is directed to blade molded line, is with thick side high point
Rotation center rotates by a certain angle α °, and direction of rotation is the direction for making thin side surplus increase, the rotation angle, wherein H be theoretical forging profile and move horizontally after Die cavity profile between vertical spacing distance, L
For the horizontal distance of rotation center and the thin side overlap cutting edge of blade.
2. big blade forging surplus compensation method according to claim 1, which is characterized in that the blade is separated into several
Shelves molded line carries out surplus compensation for every grade of molded line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611228892.6A CN106670365B (en) | 2016-12-27 | 2016-12-27 | A kind of big blade forging surplus compensation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611228892.6A CN106670365B (en) | 2016-12-27 | 2016-12-27 | A kind of big blade forging surplus compensation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106670365A CN106670365A (en) | 2017-05-17 |
| CN106670365B true CN106670365B (en) | 2018-10-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611228892.6A Active CN106670365B (en) | 2016-12-27 | 2016-12-27 | A kind of big blade forging surplus compensation method |
Country Status (1)
| Country | Link |
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| CN (1) | CN106670365B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112439861A (en) * | 2020-10-26 | 2021-03-05 | 无锡透平叶片有限公司 | Method for designing baffle stationary blade forging for reducing transverse offset |
| CN112872273B (en) * | 2021-03-17 | 2022-06-14 | 中国航发动力股份有限公司 | Molded line compensation method for precision forging blade die |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002046030A (en) * | 2000-08-04 | 2002-02-12 | Yutaka Seimitsu Kogyo Ltd | Manufacturing method for bevel gear, bevel gear material, and bevel gear |
| CN103604394A (en) * | 2013-10-19 | 2014-02-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for processing blade forging member having mounting plate with spatial angle |
| CN104331560A (en) * | 2014-11-05 | 2015-02-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for profile compensation design of rolling die |
| CN105626163A (en) * | 2015-12-28 | 2016-06-01 | 无锡透平叶片有限公司 | Forging corner determination method of separation plate stationary blade |
| CN105798214A (en) * | 2014-12-30 | 2016-07-27 | 天津重型装备工程研究有限公司 | Method for forming turbine blade through round bar multi-directional die forging |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10035224A1 (en) * | 2000-07-20 | 2002-01-31 | Man Turbomasch Ag Ghh Borsig | Process and blank for producing rhomboid blades for axial turbomachines |
-
2016
- 2016-12-27 CN CN201611228892.6A patent/CN106670365B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002046030A (en) * | 2000-08-04 | 2002-02-12 | Yutaka Seimitsu Kogyo Ltd | Manufacturing method for bevel gear, bevel gear material, and bevel gear |
| CN103604394A (en) * | 2013-10-19 | 2014-02-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for processing blade forging member having mounting plate with spatial angle |
| CN104331560A (en) * | 2014-11-05 | 2015-02-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for profile compensation design of rolling die |
| CN105798214A (en) * | 2014-12-30 | 2016-07-27 | 天津重型装备工程研究有限公司 | Method for forming turbine blade through round bar multi-directional die forging |
| CN105626163A (en) * | 2015-12-28 | 2016-06-01 | 无锡透平叶片有限公司 | Forging corner determination method of separation plate stationary blade |
Non-Patent Citations (2)
| Title |
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| 叶片锻件余量加放技术的研究;盖超等;《热加工工艺(铸锻版)》;20060710;第35卷(第13期);第51-53页 * |
| 基于Deform-3D的叶片模锻模具设计研究;邵燃等;《热加工工艺》;20140310;第43卷(第5期);第148-153页 * |
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| CN106670365A (en) | 2017-05-17 |
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