CN106623586A - Hot trimming device and method for aviation engine blade type forgings - Google Patents
Hot trimming device and method for aviation engine blade type forgings Download PDFInfo
- Publication number
- CN106623586A CN106623586A CN201611209168.9A CN201611209168A CN106623586A CN 106623586 A CN106623586 A CN 106623586A CN 201611209168 A CN201611209168 A CN 201611209168A CN 106623586 A CN106623586 A CN 106623586A
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- blade
- forging
- section
- pedestal
- pillar
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D28/00—Shaping by press-cutting; Perforating
- B21D28/02—Punching blanks or articles with or without obtaining scrap; Notching
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D28/00—Shaping by press-cutting; Perforating
- B21D28/02—Punching blanks or articles with or without obtaining scrap; Notching
- B21D28/04—Centering the work; Positioning the tools
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D28/00—Shaping by press-cutting; Perforating
- B21D28/02—Punching blanks or articles with or without obtaining scrap; Notching
- B21D28/14—Dies
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Forging (AREA)
Abstract
The invention provides a hot trimming device for aviation engine blade type forgings. The hot trimming device comprises a base, springs for providing reverse extruding force for the trimmed blade type forgings, guide pillars used for guiding the springs, an ejecting plate, a cushion plate, a female die, a support block, support columns, a punch and a guiding plate. The invention also provides a hot trimming method adopting the hot trimming device, and the method includes the following steps that (1) one blade type forging which is finally forged and formed is placed on the support block of the hot trimming device; (2) trimming equipment is started, the punch of the hot trimming device is driven by the trimming equipment to move downwards so as to exert force on the blade type forging, and burrs of the blade type forging are removed under the action of shearing force; and (3) when the punch moves to the position of a bottom dead center, the springs, the ejecting plate, the cushion plate and the support block are linked with the punch and move upwards under the action of resilience of the springs, the trimmed blade type forging is ejected out, and then the punch is separated from the blade type forging and restores to the original position.
Description
Technical field
The present invention relates to the burr of blade of aviation engine forging remove field, it is more particularly to a kind of to be used for aeroplane engine
The hot trimming apparatus and method of machine blade forging.
Background technology
Blade of aviation engine forging is mainly formed by the forging of the difficult-to-deformation materials such as titanium alloy, high temperature alloy, due to sky
Aerodynamics requires that twist angle of blade is big, thus this forging adopts curve parting line, the forging of gained to remove Burr removal.At present,
Blade of aviation engine forging goes the trimming mode that Burr removal is adopted mainly to use common shaving die earnestly, also there is part
Aluminium alloy vane forging burr adopt cold cut, but either earnestly still cold cut, and forging blade can twist during trimming
Deformation.In order to solve the problems, such as forging blade torsional deflection, usual way is corrected with original mould, but timing forging
The plastic deformation that not allowing easily occurs in surface (because plastic deformation can cause material in the deformation of critical strain area, organizes forging
State changes), affect the performance of blade parts.
The content of the invention
It is an object of the invention to overcome the deficiencies in the prior art, there is provided a kind of for blade of aviation engine forging
Hot trimming apparatus and method, to solve the problems, such as that trimming process Leaf forging blade twists deformation.
Hot trimming device for blade of aviation engine forging of the present invention, including base, to be trimmed blade
Forging provides spring, the guide pillar for spring guiding and top board, backing plate, former, tray, pillar, the punching of reverse extrusion power
Head and guide plate；The quantity of the spring is at least three, and the quantity of the guide pillar is the twice of number of springs, the pillar
Quantity is at least three；The base is integrated or solid by the first pedestal and on the first pedestal and with the first pedestal
The second pedestal even is constituted, and the centre of the second pedestal is provided with cavity；The shape and size of the top board and the second pedestal
The shape and size of cavity that centre is arranged match, the shape and size of the backing plate and the shape and size phase of top board
Matching；The tray is integrated by limit base and on limit base and with limit base or the holding body that is connected is constituted,
The shape and size of holding body top surface are identical with the blade back type face of the blade forging being trimmed, the centre of the former from
Under the stopper slot that matches of the supreme limit base offered with tray and holding shape and size and holding body installation cavity；It is described
Drift is made up of formpiston section, limited step and linkage section, and the upper surface of limited step is integrated with linkage section or is connected,
The lower surface of limited step is integrated or is connected with formpiston section, shape and size and the leaf being trimmed of formpiston section bottom surface
The leaf basin type face of piece forging is identical；The centre of the guide plate offers and the formpiston section shape of cross section phase on drift
Same pilot hole, periphery is provided with and props up the via of column combination；When using, die shoe of the floor installation in trimming equipment
On, the pocket base wall and top board undersurface arranged in the second pedestal centre is respectively mounted and number of springs identical guide pillar, respectively
Spring is set on the corresponding guide pillar for being installed on pocket base wall, and each guide pillar installed in top board undersurface is inserted respectively accordingly
The bottom surface of spring bores and top board contacts with spring, and the backing plate is placed on top board, and the former is fixed on base second
The cavity side walls top surface of body, the tray is arranged in stopper slot and holding body installation cavity that former centre is arranged, and is held in the palm
The limit base bottom surface of block and pad contact, each pillar is separately mounted to the cavity side walls top surface of the pedestal of base second, and props up two-by-two
Post is axisymmetricly distributed with the center line of the second pedestal, and the guide plate is supported and detachable with each pillar solid by pillar
Even, the linkage section of the drift is connected with the upper bolster of trimming equipment, and the formpiston section of drift is opened up through guide plate centre
Pilot hole be located at guide plate lower section.
Above-mentioned hot trimming device, the preferred cuboid of the shape of the first pedestal and the second pedestal of the base, the second pedestal
The cavity of upper setting is rectangle cavity.Therefore, the quantity of the spring preferably four, the quantity of the pillar preferably four.
Above-mentioned hot trimming device, the pillar is the solid post that tubular type post or two ends are provided with external thread section.
Above-mentioned hot trimming device, the preferred structure of the guide pillar is：By the thread segment of integral structure, guide section and nut
Duan Zucheng, guide section is located between thread segment and nut section.
Hot trimming method for blade of aviation engine forging of the present invention, using above-mentioned hot trimming device, step
It is rapid as follows：
1. the blade forging that finish-forging shapes is placed on the tray of hot trimming device, and makes its blade back type face with tray
Holding body top surface is contacted；
2. trimming equipment is started, the drift of hot trimming device is moved downward and to blade forging in the case where trimming equipment drives
Force, the burr for making blade forging are removed under shearing force；
3. when drift moves to lower dead point position, in the presence of spring restoring force, spring, top board, backing plate and tray
Link upwards with drift, the blade forging after trimming is ejected, the blade forging of drift disengaging immediately returns back to original position.
Compared with prior art, the invention has the advantages that：
1st, because hot trimming device of the present invention is provided with spring, move downward to being trimmed blade forging in drift
During force, spring can provide a reverse extrusion power to being trimmed blade forging simultaneously, thus efficiently solve trimming process
Leaf forging blade twists the problem of deformation.Test shows, using hot trimming apparatus and method of the present invention, leaf
Piece forging will not deform.
2nd, because the component of hot trimming device of the present invention optimizes shape and structure, thus when in use stress is closed
Reason, stable working state.
3rd, it is not result in blade due to carrying out trimming to blade forging using hot trimming apparatus and method of the present invention
Deform, thus avoid follow-up correcting process again, can not only reduce the occupancy to equipment and energy resource consumption, and contract
The short process-cycle, cost can be greatly lowered.
Description of the drawings
Fig. 1 is the structural representation of the device for blade of aviation engine forging hot trimming of the present invention；
Fig. 2 is the schematic diagram of the base in the device for blade of aviation engine forging hot trimming of the present invention；
Fig. 3 is the A-A sectional views of Fig. 2；
Fig. 4 is the schematic diagram of the guide pillar in the device for blade of aviation engine forging hot trimming of the present invention；
Fig. 5 is the schematic diagram of the top board in the device for blade of aviation engine forging hot trimming of the present invention；
Fig. 6 is the top view of Fig. 5；
Fig. 7 is the schematic diagram of the backing plate in the device for blade of aviation engine forging hot trimming of the present invention；
Fig. 8 is the left view of Fig. 7；
Fig. 9 is the schematic diagram of the tray in the device for blade of aviation engine forging hot trimming of the present invention；
The top view of Figure 10 Fig. 9
Figure 11 is the schematic diagram of the former in the device for blade of aviation engine forging hot trimming of the present invention；
Figure 12 is the schematic diagram of the drift in the device for blade of aviation engine forging hot trimming of the present invention；
Figure 13 is the upward view in the leaf basin type face that Figure 12 middle-jiao yang, function of the spleen and stomach mold segments lower end is arranged；
Figure 14 is the signal of the guide plate in the device for blade of aviation engine forging hot trimming of the present invention
Figure；
Figure 15 is the top view of Figure 14.
In figure, 1-base, 1-1-the first pedestal, 1-2-the second pedestal, 1-3-cavity, 1-4-the first screw, 1-
5-the second screw, 1-6-hole for hoist, 2-spring, 3-guide pillar, 3-1 thread segments, 3-2-guide section, 3-3-nut section, 4-
Top board, the screws of 4-1-the 3rd, 5-backing plate, 6-tray, 6-1-limit base, 6-2-holding body, 6-3-holding body top surface,
7-former, 7-1-stopper slot, 7-2-holding body installation cavity, 8-pillar, 9-bolt (or nut), 10-drift, 10-1-
Formpiston section bottom surface, 10-2-formpiston section, 10-3-limited step, 10-4-linkage section, 11-guide plate, 11-1-pilot hole,
11-2-via.
Specific embodiment
Below by specific embodiment and accompanying drawing is combined to the heat for blade of aviation engine forging of the present invention
Trimming device is described further with method.
In the present embodiment, the blade of aviation engine forging being trimmed forging and molding on a hydraulic press, forge piece blank reheating Jing
High-temperature electric resistance furnace is incubated, and the uniform coating glass lubricant of blank surface in forging process carries out immediately hot trimming after forging.
In the present embodiment, trimming equipment is fluid pressure type bead cutter, and model К Б 262, Russia produces.
In the present embodiment, hot trimming device including base 1, to be trimmed blade forging as shown in figure 1, provide reversely crowded
The spring 2 of pressure, the guide pillar 3 being oriented to for the spring and top board 4, backing plate 5, former 7, tray 6, pillar 8, drift 10 and guiding
Plate 11.
The base 1 is one by the first pedestal 1-1 and on the first pedestal and with the first pedestal as shown in Figure 2 and Figure 3
The second pedestal of body structure 1-2 is constituted, and the shape of the first pedestal 1-1 and the second pedestal 1-2 of base is cuboid, second
The centre of body 1-2 is provided with rectangle cavity 1-3；In view of the shape of base 1, the quantity of the spring 2 is four, described
The quantity of guide pillar 3 is eight, and the quantity of the pillar 8 is four；Therefore, the rectangle cavity that the second pedestal centre is arranged
Four the second screw 1-5 for installing guide pillar, the rectangle cavity that the second pedestal centre is arranged are provided with 1-3 diapires
1-3 sides wall top surface is provided with four the first screw 1-4 for mounting column, moving for the ease of base, the second pedestal 1-2
Side be also provided with four hole for hoist 1-6.
As shown in figure 1, the spring 2 is cylindrically coiled spring, as shown in figure 4, spiral shell of the guide pillar 3 by integral structure
Line section 3-1, guide section 3-2 and nut section 3-3 composition, guide section 3-2 is located between thread segment 3-1 and nut section 3-3.
As shown in Figure 5, Figure 6, the rectangle cavity that the shape and size of the top board 4 are arranged with the second pedestal centre
The shape and size of 1-3 match, as shown in Figure 7, Figure 8, the shape and size of the backing plate 5 and the shape and size of top board 4
Match.
As shown in Figure 9, Figure 10, the tray 6 by limit base 6-1 and on limit base and with the integrated knot of limit base
Structure holding body 6-2 constitute, limit base be rectangle plate body, shape and size and the blade class being trimmed of holding body top surface 6-3
The blade back type face of forging is identical；As shown in figure 11, the centre of the former 7 offers from bottom to up the limit base with tray
The stopper slot 7-1 matched with holding shape and size and holding body installation cavity 7-2.
As shown in Figure 12 and Figure 13, the drift 10 is made up of formpiston section 10-2, limited step 10-3 and linkage section 10-4,
The upper surface of limited step 10-3 is integrated with linkage section 10-4, lower surface and formpiston section 10-2 of limited step 10-3
It is integrated, the shape and size of formpiston section bottom surface 10-1 are identical with the leaf basin type face of the blade forging being trimmed.
As shown in Figure 14, Figure 15, the guide plate 11 is rectangular slab, the centre of guide plate offer with drift
Formpiston section shape of cross section identical pilot hole 11-1, periphery is provided with the four via 11-2 combined with pillar 8；Described
Post 8 is hollow pipe-type post.
In the present embodiment, base 1, pillar 8, top board 4, backing plate 5 and guide plate 11 select 45# steel (HRC 32～36), bullet
Spring 2 selects 60SiMnA (HRC 45～50), guide pillar 3 to select 45 steel (HRC 45～50), and tray 6, former 7 and drift 10 are selected
4Cr5MoV1Si (HRC50～54).
When using, the base 1 is arranged on the die shoe of trimming equipment, is arranged in the second pedestal 1-2 centres
Four guide pillars 3 are respectively installed in cavity 1-3 diapires and the bottom surface of top board 4, and four springs are set in the phase for being installed on cavity 1-3 diapires
Answer on guide pillar 3, the bottom surface for inserting corresponding spring bores and top board respectively installed in each guide pillar 3 of top board undersurface connects with spring
Touch, the backing plate 5 is placed on top board, and the former 7 is fixed on the cavity side walls top surface of base the second pedestal 1-2, the support
Block 6 is arranged in stopper slot 7-1 and holding body installation cavity 7-2 that the centre of former 7 is arranged, and the limit base 6-1 bottoms of tray
Face contacts with backing plate 5, and four pillars 8 are separately mounted to the cavity side walls top surface of base the second pedestal 1-2 by bolt 9, described
Guide plate 11 is placed on the top surface of pillar 8, and four vias that its periphery is arranged are corresponding with four pillars respectively, by bolt 9 with
Pillar is fixed together, and the linkage section 10-4 of the drift 10 is connected with the upper bolster of trimming equipment, and formpiston section 10-2 of drift is worn
Cross the pilot hole 11-1 that the centre of guide plate 11 opens up and be located at guide plate lower section, then operate according to the following steps：
1. the blade forging that finish-forging shapes is placed on the tray 6 of hot trimming device, and makes its blade back type face and tray
Holding body top surface 6-3 contact；
2. trimming equipment is started, the drift 10 of hot trimming device moves downward and blade class is forged in the case where trimming equipment drives
Part exerts a force, and the burr for making blade forging are removed under shearing force；
3. when drift moves to lower dead point position, in the presence of the restoring force of spring 2, spring 2, top board 4, the and of backing plate 5
Tray 6 links upwards with drift, and the blade forging after trimming is ejected, and the blade forging of drift disengaging immediately returns back to original
Position.
Using above-mentioned hot trimming apparatus and method, blade forging is trimmed without deformation, molding surface size 100% is qualified.
Claims (7)
1. a kind of hot trimming device for blade of aviation engine forging, it is characterised in that including base (1), to be trimmed
The spring (2) of blade forging offer reverse extrusion power, the guide pillar (3) being oriented to for the spring and top board (4), backing plate (5), the moon
Mould (7), tray (6), pillar (8), drift (10) and guide plate (11)；
The quantity of the spring (2) is at least three, the quantity of the guide pillar (3) for number of springs twice, the pillar (8)
Quantity be at least three；
The base (1) is integrated or is connected by the first pedestal (1-1) and on the first pedestal and with the first pedestal
The second pedestal (1-2) constitute, the centre of the second pedestal (1-2) is provided with cavity (1-3)；The shape of the top board (4)
The shape and size of the cavity (1-3) arranged with the second pedestal centre with size match, the shape of the backing plate (5) and
Size matches with the shape and size of top board (4)；
The holding that the tray (6) is integrated by limit base (6-1) and on limit base and with limit base or is connected
Body (6-2) is constituted, and the shape and size of holding body top surface (6-3) are identical with the blade back type face of the blade forging being trimmed, institute
State what the limit base and holding shape and size that the centre of former (7) offered from bottom to up with tray (6) matched
Stopper slot (7-1) and holding body installation cavity (7-2)；
The drift (10) is made up of formpiston section (10-2), limited step (10-3) and linkage section (10-4), limited step (10-
3) upper surface is integrated or is connected with linkage section (10-4), lower surface and the formpiston section (10- of limited step (10-3)
2) it is integrated or is connected, the leaf basin type of the shape and size of formpiston section bottom surface (10-1) and the blade forging being trimmed
Face is identical；The centre of the guide plate (11) offers and the formpiston section shape of cross section identical pilot hole on drift
(11-1), periphery is provided with the via (11-2) combined with pillar (8)；
When using, the base (1) is arranged on the die shoe of trimming equipment in the second pedestal (1-2) centre
Cavity (1-3) diapire and top board (4) bottom surface are respectively mounted and number of springs identical guide pillar (3), and each spring is set in peace
On corresponding guide pillar (3) loaded on cavity (1-3) diapire, each guide pillar (3) installed in top board undersurface inserts respectively corresponding spring
The bottom surface of endoporus and top board contacts with spring, and the backing plate (5) is placed on top board, and the former (7) is fixed on base second
The cavity side walls top surface of pedestal (1-2), stopper slot (7-1) and support that the tray (6) is arranged installed in former (7) centre
Hold in body installation cavity (7-2), and limit base (6-1) bottom surface of tray contacts with backing plate (5), each pillar (8) is separately mounted to bottom
The cavity side walls top surface of the second pedestal of seat (1-2), and two-by-two pillar is axisymmetricly distributed with the center line of the second pedestal (1-2),
The guide plate (11) by pillar support and it is detachable with each pillar be connected, the linkage section (10-4) of the drift (10) with
The upper bolster connection of trimming equipment, the pilot hole (11- that the formpiston section (10-2) of drift is opened up through guide plate (11) centre
1) positioned at guide plate lower section.
2. the hot trimming device of blade of aviation engine forging is used for according to claim 1, it is characterised in that the bottom
First pedestal (1-1) of seat and the shape of the second pedestal (1-2) are cuboid, the cavity (1- arranged on the second pedestal (1-2)
3) it is rectangle cavity.
3. the hot trimming device of blade of aviation engine forging is used for according to claim 2, it is characterised in that the bullet
The quantity of spring (2) is four, and the quantity of the pillar (8) is four.
4. the hot trimming device of blade of aviation engine forging is used for according to any claim in claims 1 to 3,
It is characterized in that the pillar (8) is provided with the solid post of external thread section for tubular type post or two ends.
5. the hot trimming device of blade of aviation engine forging is used for according to any claim in claims 1 to 3,
It is characterized in that the guide pillar (3) is made up of the thread segment (3-1) of integral structure, guide section (3-2) and nut section (3-3),
Guide section (3-2) is located between thread segment (3-1) and nut section (3-3).
6. the hot trimming device of blade of aviation engine forging is used for according to claim 4, it is characterised in that described to lead
Post (3) is made up of the thread segment (3-1) of integral structure, guide section (3-2) and nut section (3-3), and guide section (3-2) is located at spiral shell
Between line section (3-1) and nut section (3-3).
7. a kind of hot trimming method for blade of aviation engine forging, it is characterised in that usage right is appointed in requiring 1 to 6
Hot trimming device described in one claim, step is as follows：
1. the blade forging that finish-forging shapes is placed on the tray of hot trimming device (6), and makes its blade back type face with tray
Holding body top surface (6-3) is contacted；
2. trimming equipment is started, the drift (10) of hot trimming device is moved downward and to blade forging in the case where trimming equipment drives
Force, the burr for making blade forging are removed under shearing force；
3. when drift moves to lower dead point position, in the presence of spring (2) restoring force, spring (2), top board (4), backing plate
(5) link upwards with drift with tray (6), the blade forging after trimming is ejected, and immediately drift departs from blade forging and returns
It is multiple extremely in situ.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611209168.9A CN106623586A (en) | 2016-12-23 | 2016-12-23 | Hot trimming device and method for aviation engine blade type forgings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611209168.9A CN106623586A (en) | 2016-12-23 | 2016-12-23 | Hot trimming device and method for aviation engine blade type forgings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106623586A true CN106623586A (en) | 2017-05-10 |
Family
ID=58827505
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611209168.9A Pending CN106623586A (en) | 2016-12-23 | 2016-12-23 | Hot trimming device and method for aviation engine blade type forgings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106623586A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110102631A (en) * | 2019-06-03 | 2019-08-09 | 遵义航天新力精密铸锻有限公司 | Superthin structure non-ferrous metal nearly shaped component edge grinding buster only |
| CN113798431A (en) * | 2021-08-29 | 2021-12-17 | 湖北三环锻造有限公司 | Automatic trimming, sorting and feeding device for steering knuckle arm |
| CN114570872A (en) * | 2022-03-18 | 2022-06-03 | 北京机电研究所有限公司 | Blade precision forging method and production line |
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| US5830518A (en) * | 1993-08-16 | 1998-11-03 | Nissen Chemitec Corporation | Device for tucking covering materials |
| CN101508003A (en) * | 2009-03-19 | 2009-08-19 | 无锡透平叶片有限公司 | TC4 alloy large-size fan blade forged piece hot edge-cutting method |
| CN201768801U (en) * | 2010-08-13 | 2011-03-23 | 东风汽车有限公司 | Trimming die for flange plate forge piece |
| CN202087674U (en) * | 2011-06-10 | 2011-12-28 | 西南大学 | Back pressure type trimming mold capable of controlling deformation quantity after forging crankshaft trimming |
| CN204799865U (en) * | 2015-07-17 | 2015-11-25 | 西安航空动力股份有限公司 | Modular finish forge blade side cut mould |
-
2016
- 2016-12-23 CN CN201611209168.9A patent/CN106623586A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5830518A (en) * | 1993-08-16 | 1998-11-03 | Nissen Chemitec Corporation | Device for tucking covering materials |
| CN101508003A (en) * | 2009-03-19 | 2009-08-19 | 无锡透平叶片有限公司 | TC4 alloy large-size fan blade forged piece hot edge-cutting method |
| CN201768801U (en) * | 2010-08-13 | 2011-03-23 | 东风汽车有限公司 | Trimming die for flange plate forge piece |
| CN202087674U (en) * | 2011-06-10 | 2011-12-28 | 西南大学 | Back pressure type trimming mold capable of controlling deformation quantity after forging crankshaft trimming |
| CN204799865U (en) * | 2015-07-17 | 2015-11-25 | 西安航空动力股份有限公司 | Modular finish forge blade side cut mould |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110102631A (en) * | 2019-06-03 | 2019-08-09 | 遵义航天新力精密铸锻有限公司 | Superthin structure non-ferrous metal nearly shaped component edge grinding buster only |
| CN113798431A (en) * | 2021-08-29 | 2021-12-17 | 湖北三环锻造有限公司 | Automatic trimming, sorting and feeding device for steering knuckle arm |
| CN114570872A (en) * | 2022-03-18 | 2022-06-03 | 北京机电研究所有限公司 | Blade precision forging method and production line |
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Address after: 610503 Cheng Fa Industrial Park, Shu long road, Xindu District, Chengdu, Sichuan Applicant after: Chengdu Engine (Group) Co., Ltd. Address before: 610503 Cheng Fa technical center, Sichuan dragon Industrial Park, Chengdu, Sichuan Applicant before: Chengdu Engine (Group) Co., Ltd. |
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Application publication date: 20170510 |