CN108581397A - Increase and decrease the processing method of material composite manufacturing turbo blade - Google Patents
Increase and decrease the processing method of material composite manufacturing turbo blade Download PDFInfo
- Publication number
- CN108581397A CN108581397A CN201810385756.0A CN201810385756A CN108581397A CN 108581397 A CN108581397 A CN 108581397A CN 201810385756 A CN201810385756 A CN 201810385756A CN 108581397 A CN108581397 A CN 108581397A
- Authority
- CN
- China
- Prior art keywords
- increase
- processing
- turbo blade
- decrease
- processing method
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Laser Beam Processing (AREA)
- Welding Or Cutting Using Electron Beams (AREA)
Abstract
The processing method of increase and decrease material composite manufacturing turbo blade of the present invention is related to a kind of turbo blade machining manufacture, the combined machining method of turbo blade is specially manufactured using increase and decrease material mode.Increase and decrease material composite manufacturing turbo blade processing method include：Increase material forming and subtracts material processing；Increase material forming and is carried out with material processing alternate cycles are subtracted；Increasing material forming includes：A1, Holistic modeling layering；A2, the special layering in part；A3, planning increase material path；A4, monocycle increase material processing；Subtract material processing to be divided into：Two kinds of processing types of end mill and side milling；Subtracting material processing method according to processing type difference includes：B1, machining area divide；B2, setting technological parameter；B3, local special parameter setting；B4, monocycle subtract material processing；Increase material forming and subtract the repetition of material fabrication cycles, until completing entire turbo blade.The present invention has the characteristics that method novelty, simple process, raising machining accuracy, especially minutia finish, improve processing efficiency, is applied widely, therefore belongs to a kind of processing method integrating economy and the increase and decrease material composite manufacturing turbo blade of practicability.
Description
Technical field
The processing method of increase and decrease material composite manufacturing turbo blade of the present invention is related to a kind of turbo blade processing and manufacturing
Method specially manufactures the combined machining method of turbo blade using increase and decrease material mode.
Background technology
Turbo blade is the important foundation part of aviation industry, and the method for manufacture turbo blade traditional at present is essence
Casting processing, this method there are problems that processing as follows：
1. model casting turbo blade is limited by casting technique, there are certain reverse mould angles for blade, de- for convenience
Mould, the turbo blade shape and size and design requirement for resulting in founding to shape in this way are inconsistent；The minutia of blade interior,
Such as chamfering, aditus laryngis feature can not finish in the later stage, and these minutias significantly affect the flow of blade, it is difficult to convection current
Amount is accurately controlled；
2. manufacture mold takes time and effort with modification mold, R＆D costs are increased；
3. the later stage machining clamping of pair cast member there are problems that being difficult to position and cutter accessibility；Since later stage machine adds
Work causes all parts material removal amount for increasing material molded part to have differences, it cannot be guaranteed that size there are the deviation of Set and Positioning
Precision and surface quality；Since the blade height for increasing material drip molding is higher, and aditus laryngis size is small, and later stage machining is caused to exist
Cutter interference problem, in addition exist processing less than region.
The problem of in the presence of for the above-mentioned prior art, a kind of new increase and decrease material composite manufacturing turbo blade of research and design
Processing method, be the problems of in the prior art very necessary to overcome.
Invention content
In view of it is above-mentioned the problems of in the prior art, it is multiple that the purpose of the present invention is a kind of new increase and decrease materials of research and design
The processing method for closing manufacture turbo blade.A kind of good processing stability is provided, research and development speed can be shortened while improving processing quality
The method for manufacturing turbo blade with the increase and decrease material of efficiency.
What technical solution of the invention was realized in：
It is of the present invention increase and decrease material composite manufacturing turbo blade processing method include：Increase material forming and subtracts material processing；
Increase material forming and is carried out with material processing alternate cycles are subtracted；
Increasing material of the present invention shapes：
A1, Holistic modeling layering：The metal works model for drawing up standby is drawn using 3 d modeling software, uses Slice Software
By threedimensional model slicing delamination；
A2, the special layering in part：For the interior details characteristic area for thering is size to require, reduce the thickness of slicing delamination, really
The special size that guarantor's increasing material obtains is closer to design size, to subtract the removal amount of material processing；
A3, planning increase material path：According to the working ability subtracted needed for material processing using cutter, each period heap is reasonably selected
Lamination number；
A4, monocycle increase material processing：Each layer of the laser path obtained according to A3 steps, high energy beam is radiated at centainly
On the powder bed of thickness, it is subjected to the process of fusing/solidification, is successively scanned, obtains the three-dimensional feature in signal period；
The material processing that subtracts is divided into：Two kinds of processing types of end mill and side milling；Subtract material processing side according to processing type difference
Method includes：
B1, machining area divide：Identify that the threedimensional model for standby metal works of drawing up determines processing type, according to processing class
Type divides end mill region and side milling region；The top of turbo blade is end mill region with the upper surface of turbo blade bottom surface；Turbine
The side of blade, turbo blade endoporus are side milling region；
B2, setting technological parameter：Technological parameter is set in machining area, generates cutter path；
B3, local special parameter setting：For the interior details characteristic area for having size to require, work is arranged according to concrete structure
Skill parameter generates cutter path；For the interior details characteristic area for thering is size to require and turbo blade and turbo blade bottom surface
When angle is fillet, according to the radius size of fillet, subtract the axial feeding of material cutter path, it is ensured that the circle being fitted
The requirement of angular radius composite design；
B4, monocycle subtract material processing：According to the technological parameter that B2 and B3 steps obtain, to the three-dimensional feature body of drawing up standby into
Row subtracts material processing, makes to have increased material layer and reaches required surface quality and dimensional accuracy；
Increasing material of the present invention shapes and subtracts the repetition of material fabrication cycles, until completing entire turbo blade.
Standby metal works of the present invention of drawing up have the turbo blade of dimensional accuracy and surface quality requirements, turbine leaf
Piece surface is curved surface or plane.
It is of the present invention to increase the high energy beam that uses in material forming process and include：Swashing with high power or high brightness heat source
Light beam, electron beam, electric arc and ion beam etc., will be metal material melting.High energy beam scan path includes band-like, island and planar etc.
Mode improves the purpose of forming efficiency to reach reduction residual stress.
Metal material is used in increasing material forming of the present invention：Suitable for increasing the molding powdery of material, Filamentous or plate
Shape metal material can meet quick, the precise forming of small structure and large-scale feature.
It is of the present invention to subtract material processing when increasing material is molded and subtracts material process tool accessibility to satisfaction, it can be in part
Portion minutia region carries out precision and subtracts material processing；Inside parts minutia includes：Rounded corner, bevelling, deep hole, deep trouth and
Complicated water runner etc..Such as：Between the blade and bottom plate of turbo blade to be processed there are one have size require fillet, two
There is the aditus laryngis that is formed apart from gradual change between blade, the processing quality of the fillet and aditus laryngis significantly affects the stream of turbo blade
Amount.For traditional single increasing material molding it cannot be guaranteed that processing quality；Material processing is subtracted for tradition, since blade height is higher,
There are the interference of cutter and blade；Tradition, which subtracts the turbo blade of material processing and subtracts material cutter, can form interference；And the increasing of the present invention
Subtract material composite manufacturing turbo blade and subtract material cutter just be not present interference, and using increase and decrease material composite manufacturing method not by
The limitation of blade height does not consider the interference problem for subtracting material cutter and turbo blade.
Increasing material of the present invention is molded over the increased number of plies or height in cycle every time, according to the molding turbo blade of institute
Size and the cutting power of cutter determine；In the position for needing to subtract material processing, increase the suitable number of plies or height；For not needing
Subtracting the position of material processing only needs to increase material molding.
Of the present invention to subtract material processing, there is certain coincidence area in cutter shaft in the adjacent material region that subtracts twice upwards,
Guarantee subtracts material path and apparent interface is not present twice, influences surface quality；Subtract the axial feed of the tool amount and increasing material of material processing
Molding surplus can control parts size precision and surface quality.
The material of the present invention that subtracts is processed using milling or grinding etc., the surface quality got well.
It is an advantage of the invention that it will be apparent that being mainly manifested in：
1, the present invention does not need mold using the method for increase and decrease material composite manufacturing turbo blade, therefore saves manufacture mold
With the time of modification mold；
2, the present invention is manufactured turbo blade and reverse mould angle is not present using the method for increase and decrease material composite manufacturing turbo blade,
Internal labyrinth can be finished, it is ensured that part can reach design accuracy；
3, the present invention is increased material molding with material processing is subtracted and is shared a seat using the method for increase and decrease material composite manufacturing turbo blade
Mark system, eliminates the error of conventional method resetting；
4, the problem of using the method for increasing and decreasing material composite manufacturing turbo blade, avoiding process tool accessibility of the invention,
The region that interference can be generated to conventional cast+machine tool is processed.
The present invention has method novelty, simple process, raising machining accuracy, raising processing efficiency, applied widely etc. excellent
Point, high-volume, which puts goods on the market, will generate positive social benefit and significant economic benefit.
Description of the drawings
The present invention shares 8 width attached drawings, wherein：
Attached drawing 1 is present invention increase and decrease material composite manufacturing turbo blade schematic diagram；
Attached drawing 2 is turbine blade arrangement vertical view of the present invention；
Attached drawing 3 is turbine blade arrangement shaft side figure of the present invention；
Attached drawing 4 is the portions A enlarged drawing in attached drawing 3；
Attached drawing 5 is B partial enlarged views in attached drawing 3；
Attached drawing 6 is that tradition subtracts material turbine blades tool position schematic diagram；
Attached drawing 7 is present invention increase and decrease material composite manufacturing turbo blade tool position schematic diagram；
Attached drawing 8 is present invention increase and decrease material composite manufacturing turbine blade arrangement local tool path profile.
In figure：1, high energy beam 2, increase material machined layer 3, subtract material cutter 4, subtract material finished surface 5, turbo blade 6,
Angle 7, turbo blade bottom surface 8, turbo blade endoporus 9, aditus laryngis.
Specific implementation mode
Specific embodiments of the present invention are as shown in the picture, and the processing method of increase and decrease material composite manufacturing turbo blade includes：Increase
Material shapes and subtracts material processing；Increase material forming and is carried out with material processing alternate cycles are subtracted；
Increase material molding：Standby Turbine Blade Model of drawing up is drawn using 3 d modeling software, it will be three-dimensional using Slice Software
Model slice is layered, small in view of turbo blade fillet size, and the thickness of layering is thinned at turbo blade angle 6 (fillet), makes
Characteristic size that material obtains must be increased closer to design size, it is possible to reduce subtract the removal amount of material processing, planning increases material laser scanning
Path；High energy beam 1 obtains increasing material and adds according to the high energy beam scan path planned, the metal material of the certain number of plies of fusing/solidification
Turbo blade angle 6 (fillet) rough surface formed between work layer 2, turbo blade 5 at this time and turbo blade bottom surface 7, no
Design requirement can be met；
Subtract material processing：Since the size of turbo blade 5 is small, subtract the axial feeding of material cutter 3 so that the spy of fitting
Sign size meets design requirement, generates the path for subtracting material cutter 3；According to the path of planning, subtract material cutter 3 to increasing material machined layer 2
It carries out subtracting material processing, includes the processing to turbine fillet 6；Forming at angle (fillet) is complete using the method for small size interpolation
At, it is ensured that fillet dimensional accuracy meets technology requirement with surface quality；
It repeats to increase material molding and subtracts processing of the material processing until completing entire turbo blade.
The above, only preferable specific implementation mode of the invention, but protection scope of the present invention is not limited to
This, all those familiar with the art are in technical scope disclosed by the invention, according to the technique and scheme of the present invention
And its design of the present invention is subject to equivalent substitution or change and is covered by the protection scope of the present invention.
Claims (9)
1. a kind of processing method of increase and decrease material composite manufacturing turbo blade, it is characterised in that the processing method includes：Increase material
Shape and subtract material processing；Increase material forming and is carried out with material processing alternate cycles are subtracted；
The increasing material shapes：
A1, Holistic modeling layering：The metal works model for drawing up standby is drawn using 3 d modeling software, using Slice Software by three
Dimension module slicing delamination；
A2, the special layering in part：For the interior details characteristic area for thering is size to require, reduce the thickness of slicing delamination, it is ensured that increase
The special size that material obtains is closer to design size, to subtract the removal amount of material processing；
A3, planning increase material path：According to the working ability subtracted needed for material processing using cutter, each period stack layer is reasonably selected
Number；
A4, monocycle increase material processing：Each layer of the laser path obtained according to A3 steps, certain thickness is radiated at by high energy beam
Powder bed on, be subjected to the process of fusing/solidification, successively scan, obtain the three-dimensional feature in signal period；
The material processing that subtracts is divided into：Two kinds of processing types of end mill and side milling；Subtract material processing method packet according to processing type difference
It includes：
B1, machining area divide：It identifies that the threedimensional model for standby metal works of drawing up determines processing type, is drawn according to processing type
Divide end mill region and side milling region；The top of turbo blade (5) is end mill region with the upper surface of turbo blade bottom surface (7)；Whirlpool
The side of impeller blade (5), turbo blade endoporus (8) are side milling region；
B2, setting technological parameter：Technological parameter is set in machining area, generates cutter path；
B3, local special parameter setting：For the interior details characteristic area for thering is size to require, technique is arranged according to concrete structure and is joined
Number generates cutter path；For the interior details characteristic area for thering is size to require and turbo blade (5) and turbo blade bottom surface (7)
Angle (6) be fillet when, according to the radius size of fillet, subtract the axial feeding of material cutter path, it is ensured that be fitted
The radius of corner composite design requirement arrived；
B4, monocycle subtract material processing：According to the technological parameter that B2 and B3 steps obtain, the three-dimensional feature body for drawing up standby is subtracted
Material is processed, and is made to have increased material layer and is reached required surface quality and dimensional accuracy；
The increasing material shapes and subtracts the repetition of material fabrication cycles, until completing entire turbo blade.
2. the processing method of increase and decrease material composite manufacturing turbo blade according to claim 1, it is characterised in that described is quasi-
Preparing metal works, there is the turbo blade (5) of dimensional accuracy and surface quality requirements, turbo blade (5) surface to be curved surface or put down
Face.
3. the processing method of increase and decrease material composite manufacturing turbo blade according to claim 1, it is characterised in that the increasing
The high energy beam used in material forming process includes：Laser beam, electron beam, electric arc with high power or high brightness heat source and ion
Beam etc., will be metal material melting.
4. the processing method of increase and decrease material composite manufacturing turbo blade according to claim 3, it is characterised in that the height
Beam scan path includes that the modes such as band-like, island and planar improve the purpose of forming efficiency to reach reduction residual stress.
5. the processing method of increase and decrease material composite manufacturing turbo blade according to claim 3, it is characterised in that the increasing
Metal material is used in material forming：Suitable for increasing the molding powdery of material, Filamentous or plate-shaped metal material can meet tiny knot
Quick, the precise forming of structure and large-scale feature.
6. the processing method of increase and decrease material composite manufacturing turbo blade according to claim 1, it is characterised in that the increasing
Material is molded over the increased number of plies or height in cycle every time, according to molding turbo blade size and cutter cutting power it is true
It is fixed；In the position for needing to subtract material processing, increase the suitable number of plies or height；Position for that need not subtract material processing only needs to increase material
Molding.
7. the processing method of increase and decrease material composite manufacturing turbo blade according to claim 6, it is characterised in that described subtracts
Material processing is using milling or grinding etc., the surface quality got well.
8. the processing method of increase and decrease material composite manufacturing turbo blade according to claim 7, it is characterised in that described subtracts
Material processing can carry out inside parts minutia region accurate when increasing material is molded and subtracts material process tool accessibility to satisfaction
Subtract material processing；Inside parts minutia includes：Rounded corner, bevelling, deep hole, deep trouth and complicated water runner etc..
9. the processing method of increase and decrease material composite manufacturing turbo blade according to claim 8, it is characterised in that described subtracts
Material is processed, and the adjacent material region that subtracts twice has certain coincidence area in cutter shaft upwards, and guarantee subtracts material path and is not present twice
Apparent interface, influences surface quality；Part ruler can be controlled with material molding surplus is increased by subtracting the axial feed of the tool amount of material processing
Very little precision and surface quality.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810385756.0A CN108581397B (en) | 2018-04-26 | 2018-04-26 | Machining method for manufacturing turbine blade by adding and subtracting materials in composite mode |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810385756.0A CN108581397B (en) | 2018-04-26 | 2018-04-26 | Machining method for manufacturing turbine blade by adding and subtracting materials in composite mode |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108581397A true CN108581397A (en) | 2018-09-28 |
| CN108581397B CN108581397B (en) | 2020-02-18 |
Family
ID=63610189
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810385756.0A Active CN108581397B (en) | 2018-04-26 | 2018-04-26 | Machining method for manufacturing turbine blade by adding and subtracting materials in composite mode |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108581397B (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109139333A (en) * | 2018-09-29 | 2019-01-04 | 东方电气集团东方电机有限公司 | A kind of split-type hydraulic turbine model runner and its manufacturing method with rounded structure |
| CN110052713A (en) * | 2019-03-22 | 2019-07-26 | 江南大学 | Part increases and decreases material composite manufacturing technology |
| CN110394448A (en) * | 2019-09-03 | 2019-11-01 | 深圳大学 | A kind of metal 3D printing method and system |
| CN110823581A (en) * | 2019-11-13 | 2020-02-21 | 中国航发动力股份有限公司 | Method for processing swirler and verifying air flow of swirler |
| CN110936171A (en) * | 2019-12-17 | 2020-03-31 | 中国航发动力股份有限公司 | Machining method for inner surface of additive manufacturing part |
| CN111037808A (en) * | 2020-01-20 | 2020-04-21 | 湖南华曙高科技有限责任公司 | Shoe mold and preparation method thereof |
| CN112388972A (en) * | 2020-11-18 | 2021-02-23 | 嘉兴学院 | Flexible complex material increasing/decreasing hybrid manufacturing process |
| CN113020778A (en) * | 2021-03-19 | 2021-06-25 | 南京中科煜宸激光技术有限公司 | Material increasing and decreasing processing device and method for ultra-long pipe fitting |
| CN113369832A (en) * | 2021-06-30 | 2021-09-10 | 中国航发动力股份有限公司 | Method for processing hollow blade |
| CN113560597A (en) * | 2021-05-31 | 2021-10-29 | 东方电气集团东方电机有限公司 | Composite manufacturing method for increasing and decreasing materials of rotating wheel of water turbine |
| CN113732624A (en) * | 2021-08-11 | 2021-12-03 | 中国核电工程有限公司 | Vertical material increasing and decreasing composite manufacturing method of closed impeller |
| CN115070364A (en) * | 2022-06-10 | 2022-09-20 | 上海涵鲲科技有限公司 | Processing method for metal edge sealing of fan blade |
| CN117718561A (en) * | 2024-02-07 | 2024-03-19 | 南京理工大学 | Arc increase-decrease material composite manufacturing process planning method and system |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010094273A3 (en) * | 2009-02-21 | 2011-01-20 | Mtu Aero Engines Gmbh | Production of a turbine blisk having an oxidation and/or corrosion protection layer |
| CN106273440A (en) * | 2015-05-14 | 2017-01-04 | 王晓光 | Rapid shaping technique in high precision |
| CN106593945A (en) * | 2015-10-14 | 2017-04-26 | 阿特拉斯·科普柯能源有限公司 | Turbine wheel for a radial turbine |
| CN106694872A (en) * | 2016-11-18 | 2017-05-24 | 华中科技大学 | Compound additional material manufacturing method applicable to parts and dies |
| CN106770634A (en) * | 2016-12-08 | 2017-05-31 | 大连理工大学 | A kind of metal material high energy beam increases and decreases the online EDDY CURRENT combined machining method of material |
| CN107102061A (en) * | 2017-05-17 | 2017-08-29 | 大连理工大学 | Metal material high energy beam increases and decreases the online laser ultrasonic detection combined machining method of material |
| CN107097036A (en) * | 2017-05-24 | 2017-08-29 | 西北工业大学 | Metal parts restorative procedure based on increase and decrease material manufacture |
| CN107457529A (en) * | 2017-06-12 | 2017-12-12 | 广东工业大学 | A kind of manufacture method of cavity turbine disk |
| CN107511683A (en) * | 2017-08-11 | 2017-12-26 | 西安增材制造国家研究院有限公司 | A kind of large complicated hardware increase and decrease material manufacture device and method |
-
2018
- 2018-04-26 CN CN201810385756.0A patent/CN108581397B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010094273A3 (en) * | 2009-02-21 | 2011-01-20 | Mtu Aero Engines Gmbh | Production of a turbine blisk having an oxidation and/or corrosion protection layer |
| CN106273440A (en) * | 2015-05-14 | 2017-01-04 | 王晓光 | Rapid shaping technique in high precision |
| CN106593945A (en) * | 2015-10-14 | 2017-04-26 | 阿特拉斯·科普柯能源有限公司 | Turbine wheel for a radial turbine |
| CN106694872A (en) * | 2016-11-18 | 2017-05-24 | 华中科技大学 | Compound additional material manufacturing method applicable to parts and dies |
| CN106770634A (en) * | 2016-12-08 | 2017-05-31 | 大连理工大学 | A kind of metal material high energy beam increases and decreases the online EDDY CURRENT combined machining method of material |
| CN107102061A (en) * | 2017-05-17 | 2017-08-29 | 大连理工大学 | Metal material high energy beam increases and decreases the online laser ultrasonic detection combined machining method of material |
| CN107097036A (en) * | 2017-05-24 | 2017-08-29 | 西北工业大学 | Metal parts restorative procedure based on increase and decrease material manufacture |
| CN107457529A (en) * | 2017-06-12 | 2017-12-12 | 广东工业大学 | A kind of manufacture method of cavity turbine disk |
| CN107511683A (en) * | 2017-08-11 | 2017-12-26 | 西安增材制造国家研究院有限公司 | A kind of large complicated hardware increase and decrease material manufacture device and method |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109139333A (en) * | 2018-09-29 | 2019-01-04 | 东方电气集团东方电机有限公司 | A kind of split-type hydraulic turbine model runner and its manufacturing method with rounded structure |
| CN110052713A (en) * | 2019-03-22 | 2019-07-26 | 江南大学 | Part increases and decreases material composite manufacturing technology |
| CN110052713B (en) * | 2019-03-22 | 2020-04-10 | 江南大学 | Composite manufacturing process for increasing and decreasing materials of parts |
| CN110394448A (en) * | 2019-09-03 | 2019-11-01 | 深圳大学 | A kind of metal 3D printing method and system |
| CN110823581A (en) * | 2019-11-13 | 2020-02-21 | 中国航发动力股份有限公司 | Method for processing swirler and verifying air flow of swirler |
| CN110936171A (en) * | 2019-12-17 | 2020-03-31 | 中国航发动力股份有限公司 | Machining method for inner surface of additive manufacturing part |
| CN111037808A (en) * | 2020-01-20 | 2020-04-21 | 湖南华曙高科技有限责任公司 | Shoe mold and preparation method thereof |
| CN112388972A (en) * | 2020-11-18 | 2021-02-23 | 嘉兴学院 | Flexible complex material increasing/decreasing hybrid manufacturing process |
| CN113020778A (en) * | 2021-03-19 | 2021-06-25 | 南京中科煜宸激光技术有限公司 | Material increasing and decreasing processing device and method for ultra-long pipe fitting |
| CN113560597A (en) * | 2021-05-31 | 2021-10-29 | 东方电气集团东方电机有限公司 | Composite manufacturing method for increasing and decreasing materials of rotating wheel of water turbine |
| CN113369832A (en) * | 2021-06-30 | 2021-09-10 | 中国航发动力股份有限公司 | Method for processing hollow blade |
| CN113732624A (en) * | 2021-08-11 | 2021-12-03 | 中国核电工程有限公司 | Vertical material increasing and decreasing composite manufacturing method of closed impeller |
| CN113732624B (en) * | 2021-08-11 | 2023-01-17 | 中国核电工程有限公司 | Vertical material increasing and decreasing composite manufacturing method of closed impeller |
| CN115070364A (en) * | 2022-06-10 | 2022-09-20 | 上海涵鲲科技有限公司 | Processing method for metal edge sealing of fan blade |
| CN115070364B (en) * | 2022-06-10 | 2024-05-07 | 上海涵鲲科技有限公司 | Processing method of fan blade metal edge sealing |
| CN117718561A (en) * | 2024-02-07 | 2024-03-19 | 南京理工大学 | Arc increase-decrease material composite manufacturing process planning method and system |
| CN117718561B (en) * | 2024-02-07 | 2024-05-17 | 南京理工大学 | Arc increase-decrease material composite manufacturing process planning method and system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108581397B (en) | 2020-02-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108581397A (en) | Increase and decrease the processing method of material composite manufacturing turbo blade | |
| CN106808681B (en) | A method of improving increasing material manufacturing element precision | |
| CN107717364B (en) | The cold and hot composite manufacturing method of hollow turbine vane inner cavity hot investment casting shape machining | |
| CN108889948B (en) | Partition scanning method for thin-walled part additive manufacturing | |
| CN104786078B (en) | The numerical-control processing method and its matching tooling fixture of overall titanium alloy impeller | |
| CN107584115B (en) | The five-axle linkage Method of printing of the impeller blade of spatial warping curved surface | |
| CN105269277A (en) | Method for machining arc-tooth tenon blade of aircraft engine gas compressor | |
| CN110000381A (en) | A kind of electric arc increase and decrease material composite integrated manufacturing method of Propeller Model | |
| JPH09150228A (en) | Manufacture of metallic plate laminated metallic mold | |
| CN110523981A (en) | The 3D printing method of more performance composite constructions | |
| CN106891167A (en) | Increase and decrease combined machining method based on electron beam fuse | |
| CN109570907B (en) | Groove cavity and machining method | |
| CN113377069A (en) | Method for generating mixed milling cutter path for machining blisk blade profile | |
| CN109352048B (en) | Spatial dead axle milling method for integral titanium alloy air compressing impeller | |
| CN105436819A (en) | Processing method for metallic reinforced edges of aero-engine fan blades | |
| CN105881821A (en) | Injection mold and manufacturing method of injection mold | |
| CN106270515B (en) | 3D printing, heat treatment and finishing integral processing method | |
| CN107505913B (en) | Maximum based on the four-shaft numerically controlled processing in integral blade disk channel is applicable in tool radius calculation method | |
| KR101917061B1 (en) | Method for setting shaping angle for three-dimensional shaped product | |
| CN106077775B (en) | A kind of processing method of three axis machine tooling back-off class workpiece | |
| CN111230194B (en) | Edge line design method for end tooth linear edge of cylindrical flat-end milling cutter with chamfer | |
| CN110695422B (en) | Milling method for fixed shaft of closed blisk cavity | |
| CN116604334A (en) | Composite manufacturing method and system for increasing and decreasing materials of centrifugal wheel structure | |
| CN205702605U (en) | Compound many internal groove milling cutters | |
| CN107065767B (en) | Method for generating 3D contour chamfering processing path |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |