CN113400850A - Retrospective marking method for aviation precision-forged blade - Google Patents
Retrospective marking method for aviation precision-forged blade Download PDFInfo
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- CN113400850A CN113400850A CN202110838095.4A CN202110838095A CN113400850A CN 113400850 A CN113400850 A CN 113400850A CN 202110838095 A CN202110838095 A CN 202110838095A CN 113400850 A CN113400850 A CN 113400850A
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- 238000000034 method Methods 0.000 title claims abstract description 48
- 238000005242 forging Methods 0.000 claims abstract description 101
- 230000007246 mechanism Effects 0.000 claims abstract description 40
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 12
- 239000010959 steel Substances 0.000 claims abstract description 12
- 238000007781 pre-processing Methods 0.000 claims abstract description 11
- 230000008569 process Effects 0.000 claims abstract description 9
- 238000010438 heat treatment Methods 0.000 claims description 37
- 239000000126 substance Substances 0.000 claims description 16
- 239000012535 impurity Substances 0.000 claims description 9
- 238000005498 polishing Methods 0.000 claims description 9
- 238000004140 cleaning Methods 0.000 claims description 8
- 238000013329 compounding Methods 0.000 claims description 8
- 230000007797 corrosion Effects 0.000 claims description 8
- 238000005260 corrosion Methods 0.000 claims description 8
- 238000003801 milling Methods 0.000 claims description 8
- 238000005507 spraying Methods 0.000 claims description 8
- 238000003754 machining Methods 0.000 claims description 5
- 238000007689 inspection Methods 0.000 claims description 4
- 238000011179 visual inspection Methods 0.000 claims description 4
- 238000005452 bending Methods 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 2
- 238000004321 preservation Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 abstract description 13
- 230000000694 effects Effects 0.000 description 5
- 238000003825 pressing Methods 0.000 description 4
- 230000006872 improvement Effects 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 230000003749 cleanliness Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007514 turning Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B44—DECORATIVE ARTS
- B44B—MACHINES, APPARATUS OR TOOLS FOR ARTISTIC WORK, e.g. FOR SCULPTURING, GUILLOCHING, CARVING, BRANDING, INLAYING
- B44B5/00—Machines or apparatus for embossing decorations or marks, e.g. embossing coins
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B44—DECORATIVE ARTS
- B44B—MACHINES, APPARATUS OR TOOLS FOR ARTISTIC WORK, e.g. FOR SCULPTURING, GUILLOCHING, CARVING, BRANDING, INLAYING
- B44B5/00—Machines or apparatus for embossing decorations or marks, e.g. embossing coins
- B44B5/009—Machines or apparatus for embossing decorations or marks, e.g. embossing coins by multi-step processes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B44—DECORATIVE ARTS
- B44B—MACHINES, APPARATUS OR TOOLS FOR ARTISTIC WORK, e.g. FOR SCULPTURING, GUILLOCHING, CARVING, BRANDING, INLAYING
- B44B5/00—Machines or apparatus for embossing decorations or marks, e.g. embossing coins
- B44B5/02—Dies; Accessories
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B44—DECORATIVE ARTS
- B44B—MACHINES, APPARATUS OR TOOLS FOR ARTISTIC WORK, e.g. FOR SCULPTURING, GUILLOCHING, CARVING, BRANDING, INLAYING
- B44B5/00—Machines or apparatus for embossing decorations or marks, e.g. embossing coins
- B44B5/02—Dies; Accessories
- B44B5/022—Devices for holding or supporting work
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Abstract
The invention relates to the technical field of aviation precision forging blade processing, in particular to a retrospective marking method of an aviation precision forging blade, which comprises the following steps: the first step is as follows: preprocessing a forging piece; the second step is as follows: marking the preprocessed forge piece; the third step: the forging processed in the marking procedure is fixed through a clamp mechanism; the fourth step: the invention can design corresponding marking clamps aiming at blades with different shapes and structures, simultaneously design a feeler block mechanism on the marking clamps to ensure the accurate guiding of a character die, and simultaneously process materials in a steel seal marking mode.
Description
Technical Field
The invention relates to the technical field of aviation precision forging blade processing, in particular to a retrospective marking method for an aviation precision forging blade.
Background
The compressor blade is used as one of key parts of the aero-engine, has the characteristics of complex structure, high precision, complex processing technology and large quantity, and generally, the processing workload of the compressor blade accounts for 30-40% of that of the whole engine; the precision forging manufacturing technique for compressor blades is extremely complex in manufacturing due to the necessity for compressor blades having good metallurgical properties, precise dimensions, and excellent surface integrity.
In the prior art, the following problems exist:
(1) the existing compressor blade has a complex structure and high dimensional precision, the surface integrity of the blade cannot be guaranteed to be not damaged when marking, meanwhile, the phenomenon of fuzziness of marked writing is easy to occur, the external shapes of the blade can be different, and when general fixture equipment is used, the fixing effect of the blade cannot be guaranteed, and the installation effect of the blade is reduced.
(2) The existing aviation compressor blade has extremely high requirement on the dimensional precision, the marking force cannot be ensured during marking, the surface integrity of the blade is easy to damage, and the marking processing quality of the blade is reduced.
(3) The existing blade is easy to mix in the processing process, so that the material is processed for many times, and the processing quality and efficiency of the material are influenced.
Disclosure of Invention
The invention aims to provide a retrospective marking method for an aviation precision forging blade, which aims to solve the problems in the background technology.
The technical scheme of the invention is as follows: a retrospective marking method for an aviation precision forging blade comprises the following steps:
the first step is as follows: preprocessing a forging piece;
the second step is as follows: marking the preprocessed forge piece;
the third step: the forging processed in the marking procedure is fixed through a clamp mechanism;
the fourth step: and (4) carrying out steel seal marking on the forge piece fixed by the clamp mechanism.
Preferably, the forging is preprocessed, and the preprocessing comprises forging surface cleaning, forging heating, heat preservation and cooling, wherein the forging surface cleaning is performed through equipment to clean the forging surface so as to remove impurities on the forging surface, the forging heating is performed through a vacuum heat treatment device to heat, preserve heat and cool the forging, the state of the forging after heat treatment is identified, and material mixing is prevented.
Preferably, the marking process comprises forging polishing, finishing and chemical milling, wherein the forging polishing, finishing and chemical milling comprise the steps of blanking, chemical corrosion, spraying, heating, blank making, surface cleaning, spraying, heating, finish forging, vibration finishing, deburring, bending and twisting correction, heat treatment, marking, chemical corrosion, sample inspection, dimension and visual inspection, and finally the forged piece is transferred to machining.
Preferably, the fixture mechanism comprises a control console, the outside of the control console is L-shaped, a horizontal nut sliding plate is arranged on the inner side of the control console, a pushing mechanism is fixed at the upper end of the control console, the telescopic end of the pushing mechanism is connected with a spring connecting piece, two sliding grooves with the inner part being convex are formed in the outer wall of the nut sliding plate, a T-shaped nut is arranged in each sliding groove in the outer wall of the nut sliding plate in a sliding mode, and a bottom plate is fixed at the upper end of the T-shaped nut through a second inner hexagonal socket head cap screw.
Preferably, the bottom plate is fixed with flat-nose pliers through four third hexagon socket head cap head screws, the one side that the bottom plate was kept away from to flat-nose pliers is "U" shape, the inner wall of open end one side of flat-nose pliers is fixed with first clamp splice through the screw, and the open end opposite side inner wall of flat-nose pliers is provided with link gear, link gear comprises two cylindrical connecting rods that rotate the connection, and the one end of connecting rod is connected with the push pedal, and the one side that the push pedal is close to first clamp splice is fixed with the second clamp splice through the screw.
Preferably, a groove is formed above the first clamping block, an L-shaped feeler block is clamped in the groove above the first clamping block, a stop block is fixed on the side surface of the first clamping block through a screw, a threaded hole is formed in the short edge of the feeler block, a first inner hexagonal socket head cap screw is arranged in the threaded hole of the short edge of the feeler block, one end of the first inner hexagonal socket head cap screw is fixed on the outer wall of the first clamping block, and a rectangular groove is formed in the long edge of the feeler block.
Preferably, the outer wall of the flat tongs is provided with a through hole matched with the third hexagon socket head cap screw, and the inside of the through hole in the outer wall of the flat tongs is in a long strip shape.
Preferably, the number of the T-shaped nuts is four, and the external shape of the T-shaped nuts is matched with the internal shape of the convex grooves on the nut sliding plate.
The invention provides a retrospective marking method of an aviation precision forging blade by improvement, and compared with the prior art, the retrospective marking method has the following improvements and advantages:
one is as follows: the marking method has the advantages that the corresponding marking clamp can be designed aiming at the blades with different shapes and structures, the feeler block mechanism is simultaneously designed on the marking clamp, the accurate guiding of the matrix is ensured, meanwhile, the material is processed in a steel seal marking mode, the marking method has small damage to the surface of the blade, the pneumatic principle is utilized to release pressure instantly, the handwriting can be effectively marked, and the marking depth is ensured;
the second step is as follows: the clamping mechanism of the clamp can be replaced according to the shape of the blade, so that the fixing effect of the blade is improved, and the blade with different shapes can be conveniently fixed.
And thirdly: the invention can be used for cleaning the surface of the blade by pretreating the blade, increasing the cleanliness of the blade, treating the blade in a heating mode, controlling the pressing force of the marking machine by adjusting the tightness of a pressing spring of the equipment, and controlling the marking depth to adapt to the hardness of different materials, thereby achieving the purpose of clear marking.
Drawings
The invention is further explained below with reference to the figures and examples:
FIG. 1 is an exploded view of a part of the present invention;
FIG. 2 is a top plan view of the flat-nose pliers of the present invention;
FIG. 3 is a side view of flat-nose pliers of the present invention;
description of reference numerals: 1. the tool setting device comprises a base plate, 2, a first clamping block, 3, a second clamping block, 4, a stop block, 5, a tool setting block, 6, a first inner hexagonal socket head cap screw, 7, a second inner hexagonal socket head cap screw, 8, a T-shaped nut, 9, flat tongs, 10, a third inner hexagonal socket head cap screw, 11, a control table, 12, a linkage mechanism, 13, a stop block fixing seat, 14, a spring connecting piece, 15, a nut sliding plate, 16, a pushing mechanism, 17 and a pushing plate.
Detailed Description
The present invention is described in detail below, and technical solutions in the embodiments of the present invention are clearly and completely described, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention provides a retrospective marking method of an aviation precision forging blade through improvement, and the technical scheme of the retrospective marking method is as follows:
the first embodiment is as follows:
as shown in fig. 1 to 3, a retrospective marking method for an aviation precision-forged blade includes the following steps:
the first step is as follows: preprocessing a forging piece;
the second step is as follows: marking the preprocessed forge piece;
the third step: the forging processed in the marking procedure is fixed through a clamp mechanism;
the fourth step: and (4) carrying out steel seal marking on the forge piece fixed by the clamp mechanism.
Through carrying out the preliminary treatment to the forging, make the impurity on forging surface reduce, heat the forging through heating device simultaneously, the user discerns the state after the forging heat treatment like this, prevents the compounding, and the back forging that is heated simultaneously carries out the work of processing more easily.
The forging carries out the preliminary treatment including forging surface cleaning and forging heating, and wherein the forging clearance is cleared up the forging surface through equipment for clear away forging surface impurity, the forging heating is passed through vacuum heat treatment device and is heated the forging, discerns the state after the forging heat treatment, prevents the compounding simultaneously.
The marking process comprises forging polishing, finishing and chemical milling, wherein the forging polishing, finishing and chemical milling comprise the steps of blanking, chemical corrosion, spraying, heating, blank making, surface cleaning, spraying, heating, finish forging, vibration polishing, deburring, torsion correction, heat treatment, marking, chemical corrosion, sample inspection, dimension and visual inspection, and finally the forged piece is transferred to machining.
The workpiece is provided with a marking process after forging, polishing, chemical milling and other processes, so that the marked writing is effectively clear and visible, meanwhile, the marking method has small surface damage to the blade through a steel seal marking mode, pressure is released instantly by utilizing a pneumatic principle, the writing can be effectively marked, the marking depth is ensured, the marking efficiency is greatly improved, and one-time marking can be completed by one-time inching of equipment.
Example two:
a retrospective marking method for an aviation precision forging blade comprises the following steps:
the first step is as follows: preprocessing a forging piece;
the second step is as follows: marking the preprocessed forge piece;
the third step: the forging processed in the marking procedure is fixed through a clamp mechanism;
the fourth step: and (4) carrying out steel seal marking on the forge piece fixed by the clamp mechanism.
Through carrying out the preliminary treatment to the forging, make the impurity on forging surface reduce, heat the forging through heating device simultaneously, the user discerns the state after the forging heat treatment like this, prevents the compounding, and the back forging that is heated simultaneously carries out the work of processing more easily.
The clamp mechanism comprises a control console 11, the outside of the control console 11 is L-shaped, the inner side of the control console 11 is provided with a horizontal nut sliding plate 15, the upper end of the control console 11 is fixed with a pushing mechanism 16, the telescopic end of the pushing mechanism 16 is connected with a spring connecting piece 14, the outer wall of the nut sliding plate 15 is provided with two sliding chutes, the inner part of each sliding chute is convex, a T-shaped nut 8 is arranged in each sliding chute on the outer wall of the nut sliding plate 15 in a sliding way, the upper end of the T-shaped nut 8 is fixed with a bottom plate 1 through a second inner hexagonal cylinder head screw 7, the pushing mechanism 16 at the upper end of the control console 11 of the structure pushes the spring connecting piece 14 to move up and down through an air cylinder, so that the spring connecting piece 14 can extrude materials to be processed, the compression force of the marking machine is controlled through the spring connecting piece 14, the marking depth is controlled to adapt to the hardness of different materials, and the purpose of clear marking is achieved, and the grooves on the nut sliding plate 15 serve to receive the T-nuts 8 so that the T-nuts 8 can slide and the position of the bottom plate 1 can be adjusted by the T-nuts 8.
The difference between the second embodiment and the first embodiment is that the air cylinder on the console 11 can extrude the material through the spring connecting piece 14, and the pressure of the material is controlled through the spring connecting piece 14, so that the pressing force of the device is controlled, and the situation that the pressing force of the device is too large or too small is avoided.
Example three:
a retrospective marking method for an aviation precision forging blade comprises the following steps:
the first step is as follows: preprocessing a forging piece;
the second step is as follows: marking the preprocessed forge piece;
the third step: the forging processed in the marking procedure is fixed through a clamp mechanism;
the fourth step: and (4) carrying out steel seal marking on the forge piece fixed by the clamp mechanism.
Through carrying out the preliminary treatment to the forging, make the impurity on forging surface reduce, heat the forging through heating device simultaneously, the user discerns the state after the forging heat treatment like this, prevents the compounding, and the back forging that is heated simultaneously carries out the work of processing more easily.
The bottom plate 1 is fixed with flat tongs 9 through four third inner hexagonal socket head cap screws 10, one side of the flat tongs 9 far away from the bottom plate 1 is U-shaped, the inner wall of one side of the open end of the flat tongs 9 is fixed with a first clamping block 2 through screws, the inner wall of the other side of the open end of the flat tongs 9 is provided with a linkage mechanism 12, the linkage mechanism 12 consists of two cylindrical connecting rods which are rotatably connected, one end of each connecting rod is connected with a push plate 17, one side of each push plate 17 close to the first clamping block 2 is fixed with a second clamping block 3 through screws, the U-shaped end of one side of the flat tongs 9 of the structure plays a role of limiting the first clamping block 2 and the second clamping block 3, the maximum moving distance of the two sides of the first clamping block 2 and the second clamping block 3 is limited, meanwhile, the linkage mechanism 12 can push the second clamping block 3 to move towards the direction of the first clamping block 2 through the push plate 17, so that the first clamping block 2 and the second clamping block 3 can fix materials, simultaneously first clamp splice 2 and second clamp splice 3 are directly fixed through the screw, change through first clamp splice 2 and the second clamp splice 3 to different shapes like this, can fix different materials.
The difference between the third embodiment and the first embodiment is that the flat tongs 9 plays a role of fixing the first clamping block 2 and the second clamping block 3, the maximum distance between the first clamping block 2 and the second clamping block 3 can be controlled, and the linkage mechanism 12 can push the second clamping block 3 to move towards the first clamping block 2 through the push plate 17, so that the first clamping block 2 and the second clamping block 3 can fix the material.
Example four:
a retrospective marking method for an aviation precision forging blade comprises the following steps:
the first step is as follows: preprocessing a forging piece;
the second step is as follows: marking the preprocessed forge piece;
the third step: the forging processed in the marking procedure is fixed through a clamp mechanism;
the fourth step: and (4) carrying out steel seal marking on the forge piece fixed by the clamp mechanism.
Through carrying out the preliminary treatment to the forging, make the impurity on forging surface reduce, heat the forging through heating device simultaneously, the user discerns the state after the forging heat treatment like this, prevents the compounding, and the back forging that is heated simultaneously carries out the work of processing more easily.
A groove is formed in the upper portion of the first clamping block 2, an L-shaped tool setting block 5 is clamped in the groove above the first clamping block 2, a stop block 4 is fixed on the side face of the first clamping block 2 through a screw, a threaded hole is formed in the short edge of the tool setting block 5, a first inner hexagonal socket head cap screw 6 is arranged in the threaded hole of the short edge of the tool setting block 5, one end of the first inner hexagonal socket head cap screw 6 is fixed on the outer wall of the first clamping block 2, a rectangular groove is formed in the long edge of the tool setting block 5, the tool setting block 5 on the first clamping block 2 of the structure can guarantee guiding accuracy of a character die, marking accuracy is improved, and meanwhile the stop block 4 on the first clamping block 2 can increase fixing effect of a forge piece.
The difference between the fourth embodiment and the first embodiment is that the first clamping block 2 is provided with the tool setting block 5, so that the guiding accuracy of the matrix can be ensured, and the accuracy of marking is improved.
Example five:
a retrospective marking method for an aviation precision forging blade comprises the following steps:
the first step is as follows: preprocessing a forging piece;
the second step is as follows: marking the preprocessed forge piece;
the third step: the forging processed in the marking procedure is fixed through a clamp mechanism;
the fourth step: and (4) carrying out steel seal marking on the forge piece fixed by the clamp mechanism.
Through carrying out the preliminary treatment to the forging, make the impurity on forging surface reduce, heat the forging through heating device simultaneously, the user discerns the state after the forging heat treatment like this, prevents the compounding, and the back forging that is heated simultaneously carries out the work of processing more easily.
The outer wall of flat-nose pliers 9 is seted up with third hexagon socket head cap screw 10 assorted through-hole, and the inside rectangular form that is of flat-nose pliers 9 outer wall through-hole, and the bar through-hole of the flat-nose pliers 9 outer wall of this structure plays the effect that holds third hexagon socket head cap screw 10, and when unscrewing third hexagon socket head cap screw 10 like this, flat-nose pliers 9 can remove along the direction of bar through-hole, can adjust the position of flat-nose pliers 9 like this.
The difference between the fifth embodiment and the first embodiment is that the flat tongs 9 is provided with a strip-shaped through hole, and the third socket head cap screw 10 can slide in the strip-shaped through hole, so that the position of the flat tongs 9 can be adjusted, and the position of a workpiece on the flat tongs 9 can be conveniently adjusted.
Example six:
a retrospective marking method for an aviation precision forging blade comprises the following steps:
the first step is as follows: preprocessing a forging piece;
the second step is as follows: marking the preprocessed forge piece;
the third step: the forging processed in the marking procedure is fixed through a clamp mechanism;
the fourth step: and (4) carrying out steel seal marking on the forge piece fixed by the clamp mechanism.
Through carrying out preliminary treatment to the forging, make the surperficial impurity of forging reduce, heat the forging through heating device simultaneously, the user discerns the state after the forging heat treatment like this, prevents the compounding, and the back forging that is heated simultaneously carries out the work of processing more easily
The difference between the sixth embodiment and the first embodiment is that the position of the bottom plate 1 can be conveniently adjusted by arranging the T-shaped nut 8 to slide in the convex groove of the sliding plate 15.
The working principle is as follows: firstly, preprocessing a forged piece, then performing forging polishing, finishing, chemical milling and other processes on the forged piece, and then performing a marking process on the forged piece, wherein the specific setting is as follows: blanking → chemical corrosion → spraying → heating, blank making → surface cleaning → spraying → heating, finish forging → vibration finishing → burring → bending correction → heat treatment → marking → chemical corrosion → sample inspection → size and visual inspection → turning to machining, in the machining step, the machined blade is arranged at the position between the first clamping block 2 and the second clamping block 3, then the push plate 17 is pushed to move through the linkage mechanism 12, the push plate 17 can push the second clamping block 3 to move towards the direction of the first clamping block 2, then the first clamping block 2 and the second clamping block 3 can clamp one end of the blade, simultaneously the pushing mechanism 16 is started, the cylinder in the pushing mechanism 16 can push the other end of the blade through the spring connecting piece 14, so that the blade is not inclined, moreover, the knife block mechanism on the first clamping block 2 ensures the accurate guiding of the matrix, finally the blade is marked by steel seal marking, the marking method has little damage to the surface of the blade, and can effectively mark the handwriting and ensure the marking depth by utilizing the pneumatic principle to release the pressure instantly.
The previous description is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (8)
1. A retrospective marking method for an aviation precision-forged blade is characterized by comprising the following steps: the method comprises the following steps:
the first step is as follows: preprocessing a forging piece;
the second step is as follows: marking the preprocessed forge piece;
the third step: the forging processed in the marking procedure is fixed through a clamp mechanism;
the fourth step: and (4) carrying out steel seal marking on the forge piece fixed by the clamp mechanism.
2. The retrospective marking method of the aviation precision-forged blade according to claim 1, characterized in that: the forging carries out the preliminary treatment including forging surface clearance and forging heating, heat preservation, cooling, wherein the forging clearance is cleared up the forging surface through equipment for clear away forging surface impurity, the forging heating is heated, is kept warm, is cooled off the forging through vacuum heat treatment device, discerns the state after the forging heat treatment, prevents the compounding simultaneously.
3. The retrospective marking method of the aviation precision-forged blade according to claim 1, characterized in that: the marking process comprises forging polishing, finishing and chemical milling, wherein the forging polishing, finishing and chemical milling comprise the steps of blanking, chemical corrosion, spraying, heating, blank making, surface cleaning, spraying, heating, finish forging, vibration finishing, deburring, bending and twisting correction, heat treatment, marking, chemical corrosion, sample inspection, dimension and visual inspection, and finally the forged piece is transferred to machining.
4. The retrospective marking method of the aviation precision-forged blade according to claim 1, characterized in that: the fixture mechanism comprises a control console (11), the outside of the control console (11) is L-shaped, a horizontal nut sliding plate (15) is arranged on the inner side of the control console (11), a pushing mechanism (16) is fixed at the upper end of the control console (11), the telescopic end of the pushing mechanism (16) is connected with a spring connecting piece (14), two sliding grooves with the inner part being convex-shaped are formed in the outer wall of the nut sliding plate (15), a T-shaped nut (8) is arranged in each sliding groove in the outer wall of the nut sliding plate (15), and a bottom plate (1) is fixed at the upper end of the T-shaped nut (8) through a second inner hexagonal socket head cap screw (7).
5. The retrospective marking method of the aviation precision-forged blade according to claim 4, characterized in that: the bottom plate (1) is fixed with flat-nose pliers (9) through four third hexagon socket head cap screws (10), and the one side that bottom plate (1) was kept away from in flat-nose pliers (9) is "U" shape, the inner wall of open end one side of flat-nose pliers (9) has first clamp splice (2) through the screw fixation, and the open end opposite side inner wall of flat-nose pliers (9) is provided with link gear (12), link gear (12) comprise two cylindrical connecting rods that rotate the connection, and the one end of connecting rod is connected with push pedal (17), and the one side that push pedal (17) are close to first clamp splice (2) is fixed with second clamp splice (3) through the screw fixation.
6. The retrospective marking method of the aviation precision-forged blade according to claim 5, characterized in that: a groove is formed in the upper portion of the first clamping block (2), an L-shaped feeler block (5) is clamped in the groove in the upper portion of the first clamping block (2), a stop block (4) is fixed on the side face of the first clamping block (2) through a screw, a threaded hole is formed in the short edge of the feeler block (5), a first inner hexagonal socket head cap screw (6) is arranged in the threaded hole of the short edge of the feeler block (5), one end of the first inner hexagonal socket head cap screw (6) is fixed on the outer wall of the first clamping block (2), and a rectangular groove is formed in the long edge of the feeler block (5).
7. The retrospective marking method of the aviation precision-forged blade according to claim 5, characterized in that: the outer wall of the flat tongs (9) is provided with a through hole matched with the third hexagon socket head cap screw (10), and the inside of the through hole in the outer wall of the flat tongs (9) is in a long strip shape.
8. The retrospective marking method of the aviation precision-forged blade according to claim 4, characterized in that: the number of the T-shaped nuts (8) is four, and the external shape of the T-shaped nuts (8) is matched with the internal shape of the convex grooves on the nut sliding plate (15).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110838095.4A CN113400850A (en) | 2021-07-23 | 2021-07-23 | Retrospective marking method for aviation precision-forged blade |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110838095.4A CN113400850A (en) | 2021-07-23 | 2021-07-23 | Retrospective marking method for aviation precision-forged blade |
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| CN113400850A true CN113400850A (en) | 2021-09-17 |
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| CN202110838095.4A Pending CN113400850A (en) | 2021-07-23 | 2021-07-23 | Retrospective marking method for aviation precision-forged blade |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113733796A (en) * | 2021-09-22 | 2021-12-03 | 龙港市鑫鑫印刷机械有限公司 | Embossing machine fixed mounting system |
| CN114226894A (en) * | 2022-02-23 | 2022-03-25 | 成都和鸿科技股份有限公司 | Electrode tool setting method for machining turbine blade and electrode connecting piece |
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| CN107363202A (en) * | 2017-06-30 | 2017-11-21 | 陕西宏远航空锻造有限责任公司 | A kind of forming method of the small surplus blade of nickel base superalloy |
| CN107745574A (en) * | 2017-10-09 | 2018-03-02 | 张文斌 | A kind of packing box trade mark efficient printing machine |
| CN111975672A (en) * | 2020-07-24 | 2020-11-24 | 江苏大学 | Blade measuring clamp and measuring method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113733796A (en) * | 2021-09-22 | 2021-12-03 | 龙港市鑫鑫印刷机械有限公司 | Embossing machine fixed mounting system |
| CN113733796B (en) * | 2021-09-22 | 2024-06-04 | 龙港市鑫鑫印刷机械有限公司 | Embossing machine fixed mounting system |
| CN114226894A (en) * | 2022-02-23 | 2022-03-25 | 成都和鸿科技股份有限公司 | Electrode tool setting method for machining turbine blade and electrode connecting piece |
| CN114226894B (en) * | 2022-02-23 | 2022-05-17 | 成都和鸿科技股份有限公司 | Electrode tool setting method for machining turbine blade |
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Application publication date: 20210917 |