CN104331561A - Method for building blade rolling process model - Google Patents
Method for building blade rolling process model Download PDFInfo
- Publication number
- CN104331561A CN104331561A CN201410620490.5A CN201410620490A CN104331561A CN 104331561 A CN104331561 A CN 104331561A CN 201410620490 A CN201410620490 A CN 201410620490A CN 104331561 A CN104331561 A CN 104331561A
- Authority
- CN
- China
- Prior art keywords
- blade
- line
- section line
- model
- point
- 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.)
- Pending
Links
Abstract
The invention discloses a method for building a blade rolling process model, which aims at solving the technical problem of low design accuracy of the blade rolling die in the prior art. The method adopts the technical scheme that on the basis of an UG three-dimensional modeling platform and a secondary development platform, designing the process compensations of a blade intake side, a blade exhaust side, a blade tip and a blade root, establishing the reference of the process model, and finally obtaining the blade rolling process model. The method has the advantages that the profile process addition at the intake side and the exhaust side shall be in smooth connection and in a bottleneck shape, so the fluctuating wave and cracking of a blade is avoided, the uniform tissues in the extrusion process are guaranteed, and the misrun is avoided; the process addition of the blade tip and the blade root shall be in smooth torsion and uniform transition, so the change of engaging and loosening in the rolling process is stable; the reference of the process model can establish the positioning reference for rolling forming and blade measurement, and the design accuracy of the blade rolling die is improved.
Description
Technical field
The present invention relates to a kind of modeling method, particularly relate to a kind of method setting up rolling vane process modeling.
Background technology
The advantages such as blade roll milling Accurate Shaping technology is the blade machining process of a kind of advanced person, and high with its production efficiency, dimensional accuracy is high, and structure property is good, have become the important job operation of aeromotor vanelets.Roll die die cavity is the most important factor affecting rolling vane precision, and the foundation of Roll die die cavity is based on roll milling technology model, and therefore the rationality of rolling vane Technology Modeling method is most important.
Document " Authorization Notice No. is the Chinese invention patent of CN102110180B " discloses the method for designing of a kind of blade roll milling mould inlet and outlet edge profile.The method is carried out front and back rafter head based on three-dimensional computer Autocad to given blade roll milling mould cross section SPL and is extended and fairing, generates cross section, flash limit.The design of the method not mentioned process modeling, only design die cavity section line, between different cross section line, relation is unspecified with space orientation, mold cavity modeling process and the unknown of intermediate conversion process.In blade roll milling mould cavity design process, need a process modeling badly be connected blade profile to the conversion of mold cavity profile, therefore, propose rational rolling vane process modeling modeling method, to rolling design of mould cavity, there is important Auxiliary Significance.
Summary of the invention
In order to overcome the low deficiency of existing method blade roll milling mould design accuracy, the invention provides a kind of method setting up rolling vane process modeling.The method is based on UG three-dimensional modeling platform and secondary developing platform, and the design of technological compensa tion aspect of carry out blade inlet and outlet limit and blade tip, following, and set up process modeling benchmark, finally obtains rolling vane process modeling.Inlet and outlet limit profile technique is added should be connected fairing also in bottleneck shape, and the ripple that height rises and falls even chaps to prevent blade from occurring, in guarantee extrusion process, even tissue prevents misrun.Blade tip, to add with technique and answer fairing bending gradual change even, roll milling process is nipped, goes out change steadily.Process modeling benchmark is that rolling and forming and Blade measuring set up positioning datum, improves blade roll milling mould design accuracy.
The technical solution adopted for the present invention to solve the technical problems is: a kind of method setting up rolling vane process modeling, is characterized in adopting following steps:
Step 1: start 3 d modeling software UG NX7.0, enter MBM and import compressor blade model 3.
Step 2: by compressor blade model 3 blade tip section line along the blade half of continuation section line incircle maximum gauge and Cmax/2 in the other direction, formed and be connected blade tip process transition 2; By compressor blade model 3 blade root section line along the blade half of continuation section line incircle maximum gauge and Cmax/2 in the other direction, formed and be connected blade root process transition 4.
Step 3: extract blade tip process transition 2 tip line, by it along blade skew in the other direction, by biased section line group, uses and sets up entity by curve group command, set up blade tip technological compensa tion 1.
Step 4: extract blade root process transition 4 tail end section line, by it along blade skew in the other direction, by biased section line group, uses and sets up entity by curve group command, set up blade root technological compensa tion 5.
Step 5: use boolean sum computing compressor blade model leaf model 3 and blade tip process transition 2, blade tip technological compensa tion 1, blade root process transition 4 and blade root technological compensa tion 5 to be merged, and fairing processing is carried out to model joining place, form B-spline surface.
Step 6: allow tolerance δ according to blade design, setting section line spacing; Blade profile line group 6 is set up along blade root in turn to blade tip direction according to permission tolerance δ.
Step 7: use point set order to carry out point to each section line discrete, the number of point should ensure that the number put near front and rear edge is more than 20.Obtain circle matching order by UG secondary development, use round matching order to obtain trailing edge curve and point 7; Round matching order is used to obtain leading edge curve and point 9.Remaining some position leaf basin blade back curve point, uses B-SPL to carry out matching and obtains blade back curve and point 8; Use B-SPL to carry out matching and obtain leaf pelvic curvature line and point 10.
Step 8: obtain incircle iterative program by UG secondary development, uses incircle iterative program to set up the incircle of leaf basin blade back curve, makes diameter of a circle maximum, and define this section thickness of blade Cmax.
Step 9: in blade this section thickness Cmax both sides, this section thickness of spaced vanes Cmax sets up the incircle 14 of leaf basin blade back curve respectively, and ensures correspondent equal in the circular diameter and step 7 of the matching of front and rear edge place.
Step 10: use B-SPL to sequentially pass through each center of circle, set up mean camber line 12.Mean camber line two ends are respectively extended Cmax.
Step 11: set up arithmetic progression with adjacent three radius of circles in front and rear edge place, obtains mean camber line end points place's radius of circle after extension and sets up circle.Leaf basin blade back curve is carried out extending and with set up circle tangent.
Step 12: blade back curve two end points after extending are extended along section line horizontal direction, formation process model blade back curve 11; Leaf pelvic curvature line two end points after extending are extended along section line horizontal direction, formation process model leaf pelvic curvature line 13.Joining Technology model blade back curve 11 and process modeling leaf pelvic curvature line 13 two-end-point, form closed process modeling section line.
Step 13: use and set up vertical entity by curve group command by the process modeling section line closed.Joining place carries out fairing processing, forms B-spline surface, obtains blade production model blade 15.
Step 14: extract blade root and add tail end section line, uses incircle iterative program to set up the incircle of leaf basin blade back curve, makes diameter of a circle maximum, i.e. Cmax.
Step 15: take the center of circle as true origin, sets up coordinate system Z axis perpendicular to engine rotation axial line, and points to blade tip by blade root; X-axis in the horizontal direction, i.e. engine rotation direction of axis line, point to batch exhaust limit by the leading edge at blade interface, determined by Dikal coordinate system criterion, sets up process modeling coordinate system 16 thus by Y-axis.
Step 16: set up a rectangular parallelepiped, three faces of mutually disposing are locating benchmark, are connected and are integrated, formation process model orientation benchmark 17 between rectangular parallelepiped with process modeling by blockage.
The invention has the beneficial effects as follows: the method is based on UG three-dimensional modeling platform and secondary developing platform, and the design of technological compensa tion aspect of carry out blade inlet and outlet limit and blade tip, following, and set up process modeling benchmark, finally obtains rolling vane process modeling.Inlet and outlet limit profile technique is added should be connected fairing also in bottleneck shape, and the ripple that height rises and falls even chaps to prevent blade from occurring, in guarantee extrusion process, even tissue prevents misrun.Blade tip, to add with technique and answer fairing bending gradual change even, roll milling process is nipped, goes out change steadily.Process modeling benchmark is that rolling and forming and Blade measuring set up positioning datum, improves blade roll milling mould design accuracy.
Below in conjunction with the drawings and specific embodiments, the present invention is elaborated.
Accompanying drawing explanation
Fig. 1 is blade tip in the inventive method, blade root technique adds schematic diagram.
Fig. 2 is that schematic diagram chosen by the inventive method section line.
Fig. 3 is the method for designing key diagram of the inventive method blade profile line segmentation.
Fig. 4 is that the inventive method builds mean camber line and blade production model cross-sectional design method schematic diagram.
Fig. 5 is the rolling vane process modeling that the inventive method is set up.
In figure, 1-blade tip technological compensa tion, 2-blade tip process transition, 3-compressor blade model, 4-blade root process transition, 5-blade root technological compensa tion, 6-blade profile line group, 7-trailing edge curve and point, 8-blade back curve and point, 9-leading edge curve and point, 10-leaf pelvic curvature line and point, 11-process modeling blade back curve, 12-mean camber line, 13-process modeling leaf pelvic curvature line, 14-incircle, 15-process modeling blade, 16-process modeling coordinate system, 17-process modeling positioning datum.
Embodiment
With reference to Fig. 1-5.The method concrete steps that the present invention sets up rolling vane process modeling are as follows:
To set up compressor blade roll milling technology model in UG NX7.0 software, the inventive method is described.
Step 1: start 3 d modeling software UG NX7.0, enter MBM and import compressor blade model 3.
Step 2: by compressor blade model 3 blade tip section line along the blade half of continuation section line incircle maximum gauge and Cmax/2 in the other direction, formed and be connected blade tip process transition 2; By compressor blade model 3 blade root section line along the blade half of continuation section line incircle maximum gauge and Cmax/2 in the other direction, formed and be connected blade root process transition 4.
Step 3: extract blade tip process transition 2 tip line, by it along blade skew in the other direction 5 times, spacing is 2mm, by biased section line group, uses " by curve group " order to set up entity, sets up blade tip technological compensa tion 1.
Step 4: extract blade root process transition 4 tail end section line, by it along blade skew in the other direction 3 times, spacing is 2mm, by biased section line group, uses " by curve group " order to set up entity, sets up blade root technological compensa tion 5.
Step 5: use " boolean sum computing " compressor blade model leaf model 3 and blade tip process transition 2, blade tip technological compensa tion 1, blade root process transition 4 and blade root technological compensa tion 5 to be merged, and fairing processing is carried out to model joining place, form B-spline surface.
Step 6: allow tolerance δ according to blade design, setting section line spacing; Blade profile line group 6 is set up along blade root in turn to blade tip direction according to permission tolerance δ.
Step 7: use " point set " order to carry out point to each section line discrete, the number of point should ensure that the number put near front and rear edge is more than 20.Obtain " circle matching " order by UG secondary development, use " circle matching " order to obtain trailing edge curve and point 7; " circle matching " order is in like manner used to obtain leading edge curve and point 9.Remaining some position leaf basin blade back curve point, uses B-SPL to carry out matching and obtains blade back curve and point 8; In like manner use B-SPL to carry out matching and obtain leaf pelvic curvature line and point 10.
Step 8: obtain " incircle iterative program " by UG secondary development, uses " incircle iterative program " to set up the incircle of leaf basin blade back curve, makes diameter of a circle maximum, and define this section thickness of blade, i.e. Cmax.
Step 9: in Cmax both sides, interval is about the incircle 14 that Cmax sets up leaf basin blade back curve respectively, and ensures correspondent equal in the circular diameter and step 7 of the matching of front and rear edge place.
Step 10: use B-SPL to sequentially pass through each center of circle, set up mean camber line 12.Mean camber line two ends are respectively extended Cmax.
Step 11: set up arithmetic progression with adjacent three radius of circles in front and rear edge place, obtains mean camber line end points place's radius of circle after extension and sets up circle.Leaf basin blade back curve is carried out extending and with set up circle tangent.
Step 12: blade back curve two end points after extending are extended 3mm along section line horizontal direction, formation process model blade back curve 11; In like manner leaf pelvic curvature line two end points after extension are extended 3mm along section line horizontal direction, formation process model leaf pelvic curvature line 13.Joining Technology model blade back curve 11 and process modeling leaf pelvic curvature line 13 two-end-point, form closed process modeling section line.
Step 13: use " by curve group " order to set up vertical entity by the process modeling section line closed.Joining place carries out fairing processing, forms B-spline surface, obtains blade production model blade 15.
Step 14: extract blade root and add tail end section line, uses " incircle iterative program " to set up the incircle of leaf basin blade back curve, makes the maximum i.e. Cmax of diameter of a circle.
Step 15: take the center of circle as true origin, sets up coordinate system Z axis perpendicular to engine rotation axial line, and points to blade tip by blade root; X-axis in the horizontal direction, i.e. engine rotation direction of axis line, point to batch exhaust limit by the leading edge at blade interface, determined by Dikal coordinate system criterion, sets up process modeling coordinate system 16 thus by Y-axis.
Step 16: set up a rectangular parallelepiped, three faces of mutually disposing are locating benchmark, are connected and are integrated, formation process model orientation benchmark 17 between rectangular parallelepiped with process modeling by blockage.
The present invention is based on UG three-dimensional modeling and secondary developing platform, the design of technological compensa tion aspect of realize blade inlet and outlet limit and blade tip, following, sets up technological datum, finally obtains rolling vane process modeling.
1. blade tip, the technological compensa tion of following.
1) by its half along blade continuation in the other direction section line incircle maximum gauge and Cmax/2, formed and be connected transition section;
2) extract blade tip, with continuation section section line, offset 5 times, spacing is section line incircle maximum gauge, i.e. Cmax;
3) respectively by its biased curve group, UG NX7.0 " by curve group " order is used to set up blade tip respectively, with technological compensa tion;
4) technological compensa tion and blade are carried out boolean sum computing;
5) fairing processing is carried out at joining place;
2. blade inlet and outlet limit technological compensa tion.
1) tolerance is allowed according to blade, setting section line spacing δ; Blade profile line is extracted in turn along blade direction according to δ;
2) carry out point to each group section line discrete, obtain leading edge trailing edge curve point by circle matching, non-leading edge trailing edge point is leaf basin blade back curve point, uses B-SPL to carry out matching acquisition leaf basin blade back and leading edge trailing edge curve;
3) using iterative program to set up the incircle of leaf basin blade back curve to often organizing section line, making diameter of a circle maximum, and defining this section thickness of blade, i.e. Cmax;
4) to often organizing section line in Cmax both sides, interval 2Cmax sets up the incircle of leaf basin blade back curve respectively;
5) use B-SPL by each center of circle, set up leaf basin blade back mean camber line;
6) mean camber line two ends are respectively extended Cmax;
7) set up arithmetic progression with adjacent three radius of circles in front and rear edge place, obtain mean camber line end points place's radius of circle after extension and set up circle;
8) leaf basin blade back curve is carried out extending and with set up circle tangent;
9) connect point of contact, obtain closed curve, be rolling vane process modeling section line;
9) the section line group by closing, sets up blade model, and carries out fairing to blade model at section line place;
3. set up process modeling location.
1) add tail end section line for object with blade root, using iterative algorithm to obtain this section line maximum gauge Cmax and incircle, take the center of circle as absolute coordinate system initial point;
2) coordinate system Z axis is perpendicular to engine rotation axial line, and points to blade tip by blade root; X-axis engine rotation axial line overlaps, and point to batch exhaust limit by the leading edge at blade interface, Y-axis is determined by Dikal coordinate system rule;
3) setting up is that orthogonal three faces are positioning process positioning datum, be connected be integrated between rectangular parallelepiped with process modeling by blockage, formation process model orientation benchmark with rectangular parallelepiped.
Claims (1)
1. set up a method for rolling vane process modeling, it is characterized in that comprising the following steps:
Step 1: start 3 d modeling software UG NX7.0, enter MBM and import compressor blade model (3);
Step 2: by compressor blade model (3) blade tip section line along the blade half of continuation section line incircle maximum gauge and Cmax/2 in the other direction, formed and be connected blade tip process transition (2); By compressor blade model (3) blade root section line along the blade half of continuation section line incircle maximum gauge and Cmax/2 in the other direction, formed and be connected blade root process transition (4);
Step 3: extract blade tip process transition (2) tip line, by it along blade skew in the other direction, by biased section line group, uses and sets up entity by curve group command, set up blade tip technological compensa tion (1);
Step 4: extract blade root process transition (4) tail end section line, by it along blade skew in the other direction, by biased section line group, uses and sets up entity by curve group command, set up blade root technological compensa tion (5);
Step 5: use boolean sum computing compressor blade model leaf model (3) and blade tip process transition (2), blade tip technological compensa tion (1), blade root process transition (4) and blade root technological compensa tion (5) to be merged, and fairing processing is carried out to model joining place, form B-spline surface;
Step 6: allow tolerance δ according to blade design, setting section line spacing; Blade profile line group (6) is set up along blade root in turn to blade tip direction according to permission tolerance δ;
Step 7: use point set order to carry out point to each section line discrete, the number of point should ensure that the number put near front and rear edge is more than 20; Obtain circle matching order by UG secondary development, use round matching order to obtain trailing edge curve and point (7); Round matching order is used to obtain leading edge curve and point (9); Remaining some position leaf basin blade back curve point, uses B-SPL to carry out matching and obtains blade back curve and point (8); Use B-SPL to carry out matching and obtain leaf pelvic curvature line and point (10);
Step 8: obtain incircle iterative program by UG secondary development, uses incircle iterative program to set up the incircle of leaf basin blade back curve, makes diameter of a circle maximum, and define this section thickness of blade Cmax;
Step 9: in blade this section thickness Cmax both sides, this section thickness of spaced vanes Cmax sets up the incircle (14) of leaf basin blade back curve respectively, and ensures correspondent equal in the circular diameter and step 7 of the matching of front and rear edge place;
Step 10: use B-SPL to sequentially pass through each center of circle, set up mean camber line (12); Mean camber line two ends are respectively extended Cmax;
Step 11: set up arithmetic progression with adjacent three radius of circles in front and rear edge place, obtains mean camber line end points place's radius of circle after extension and sets up circle; Leaf basin blade back curve is carried out extending and with set up circle tangent;
Step 12: blade back curve two end points after extending are extended along section line horizontal direction, formation process model blade back curve (11); Leaf pelvic curvature line two end points after extending are extended along section line horizontal direction, formation process model leaf pelvic curvature line (13); Joining Technology model blade back curve (11) and process modeling leaf pelvic curvature line (13) two-end-point, form closed process modeling section line;
Step 13: use and set up vertical entity by curve group command by the process modeling section line closed; Joining place carries out fairing processing, forms B-spline surface, obtains blade production model blade (15);
Step 14: extract blade root and add tail end section line, uses incircle iterative program to set up the incircle of leaf basin blade back curve, makes diameter of a circle maximum, i.e. Cmax;
Step 15: take the center of circle as true origin, sets up coordinate system Z axis perpendicular to engine rotation axial line, and points to blade tip by blade root; X-axis in the horizontal direction, i.e. engine rotation direction of axis line, by blade interface leading edge point to batch exhaust limit, Y-axis is determined by Dikal coordinate system criterion, sets up process modeling coordinate system (16) thus;
Step 16: set up a rectangular parallelepiped, three faces of mutually disposing are locating benchmark, are connected and are integrated, formation process model orientation benchmark (17) between rectangular parallelepiped with process modeling by blockage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410620490.5A CN104331561A (en) | 2014-11-06 | 2014-11-06 | Method for building blade rolling process model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410620490.5A CN104331561A (en) | 2014-11-06 | 2014-11-06 | Method for building blade rolling process model |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104331561A true CN104331561A (en) | 2015-02-04 |
Family
ID=52406286
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410620490.5A Pending CN104331561A (en) | 2014-11-06 | 2014-11-06 | Method for building blade rolling process model |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104331561A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109684687A (en) * | 2018-12-11 | 2019-04-26 | 中国航发贵州黎阳航空动力有限公司 | A kind of modeling method of rotor blade forging blade tip technique extended segment |
| CN110773699A (en) * | 2019-11-10 | 2020-02-11 | 中国航发南方工业有限公司 | Method for controlling extrusion forming residual stress of forged blade |
| CN110773694A (en) * | 2019-11-10 | 2020-02-11 | 中国航发南方工业有限公司 | Die for forging blade |
| CN110969697A (en) * | 2019-12-20 | 2020-04-07 | 杭州汽轮动力集团有限公司 | Gas turbine moving blade key structure detection device and processing method |
| CN111814271A (en) * | 2020-07-06 | 2020-10-23 | 山西大学 | Rolled blade front and rear edge processing curved surface reconstruction method based on curved surface shape regulation |
| CN112464393A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Method for molding through-flow blade of transition section of gas compressor of ship gas turbine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102110180A (en) * | 2009-12-23 | 2011-06-29 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for designing intake and exhaust edge profile of blade rolling die |
| CN103136426A (en) * | 2013-03-01 | 2013-06-05 | 西北工业大学 | Aviation blade circular arc leading-trailing edge process model generation method |
| CN103252536A (en) * | 2013-05-20 | 2013-08-21 | 西北工业大学 | Rolled blade flange head smooth transferring machining method |
| CN103577635A (en) * | 2013-10-19 | 2014-02-12 | 沈阳黎明航空发动机(集团)有限责任公司 | Fitting method of blade surface data |
| KR20140087653A (en) * | 2012-12-31 | 2014-07-09 | (주) 디엔디이 | Method for designing and analyzing wind turbine blade |
-
2014
- 2014-11-06 CN CN201410620490.5A patent/CN104331561A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102110180A (en) * | 2009-12-23 | 2011-06-29 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for designing intake and exhaust edge profile of blade rolling die |
| KR20140087653A (en) * | 2012-12-31 | 2014-07-09 | (주) 디엔디이 | Method for designing and analyzing wind turbine blade |
| CN103136426A (en) * | 2013-03-01 | 2013-06-05 | 西北工业大学 | Aviation blade circular arc leading-trailing edge process model generation method |
| CN103252536A (en) * | 2013-05-20 | 2013-08-21 | 西北工业大学 | Rolled blade flange head smooth transferring machining method |
| CN103577635A (en) * | 2013-10-19 | 2014-02-12 | 沈阳黎明航空发动机(集团)有限责任公司 | Fitting method of blade surface data |
Non-Patent Citations (5)
| Title |
|---|
| 乔立红等: "《计算机辅助设计与制造》", 1 October 2014, 机械工业出版社 * |
| 何雪军: "模锻叶片及工装计算机辅助设计研究", 《中国优秀硕士学位论文全文数据库 工程科技II辑（月刊）》 * |
| 岳珠峰等: "《航空发动机涡轮叶片多学科设计优化》", 1 September 2007, 科学出版社 * |
| 张定华等: "《涡轮叶片精密铸造模具技术》", 1 April 2014, 国防工业出版社 * |
| 赵遵成: "基于UGII的叶片精锻模CAD系统研究", 《中国优秀博硕士学位论文全文数据库（硕士）信息科技辑（半年刊）》 * |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109684687A (en) * | 2018-12-11 | 2019-04-26 | 中国航发贵州黎阳航空动力有限公司 | A kind of modeling method of rotor blade forging blade tip technique extended segment |
| CN109684687B (en) * | 2018-12-11 | 2023-02-28 | 中国航发贵州黎阳航空动力有限公司 | Modeling method for rotor blade forging tip process extension section |
| CN110773699A (en) * | 2019-11-10 | 2020-02-11 | 中国航发南方工业有限公司 | Method for controlling extrusion forming residual stress of forged blade |
| CN110773694A (en) * | 2019-11-10 | 2020-02-11 | 中国航发南方工业有限公司 | Die for forging blade |
| CN110773699B (en) * | 2019-11-10 | 2021-02-09 | 中国航发南方工业有限公司 | Method for controlling extrusion forming residual stress of forged blade |
| CN110969697A (en) * | 2019-12-20 | 2020-04-07 | 杭州汽轮动力集团有限公司 | Gas turbine moving blade key structure detection device and processing method |
| CN110969697B (en) * | 2019-12-20 | 2023-09-19 | 杭州汽轮控股有限公司 | Gas turbine moving blade key structure detection device and processing method |
| CN111814271A (en) * | 2020-07-06 | 2020-10-23 | 山西大学 | Rolled blade front and rear edge processing curved surface reconstruction method based on curved surface shape regulation |
| CN111814271B (en) * | 2020-07-06 | 2023-04-18 | 山西大学 | Rolled blade front and rear edge processing curved surface reconstruction method based on curved surface shape regulation |
| CN112464393A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Method for molding through-flow blade of transition section of gas compressor of ship gas turbine |
| CN112464393B (en) * | 2020-10-27 | 2022-06-14 | 中国船舶重工集团公司第七0三研究所 | Method for molding through-flow blade of transition section of gas compressor of ship gas turbine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104331561A (en) | Method for building blade rolling process model | |
| CN103411574B (en) | Blade of aviation engine profile three-coordinate measuring method | |
| CN102231170B (en) | Parameterized sizing method for turbine blade mould cavity | |
| CN103488832B (en) | A kind of geometry restorative procedure of complex curved surface parts damaged area | |
| CN101692257B (en) | Method for registering complex curved surface | |
| CN104697462B (en) | A kind of aerial blade surface-type feature parameter extracting method based on axis | |
| CN103586737B (en) | A kind of compensation method of blade profile high precision numerical control Milling Machining | |
| CN103473391B (en) | Pneumatic plant experiment blade mold die cavity reverse adjustment method | |
| CN103008497B (en) | Unfolding method for complex flange of frame rib sheet metal part | |
| CN104881540A (en) | Accurate wall thickness control modeling method for inside profile of blade body of turbine air cooling blade | |
| CN110990994B (en) | Matlab and UG-based turbine blade parametric modeling method | |
| CN102735175B (en) | A kind of method based on Moving Least determination maximum blade thickness | |
| CN104408236A (en) | Method for establishing rolling blade die cavity | |
| CN110688709A (en) | Workpiece point cloud model-based skin process model correction method | |
| CN106021782A (en) | Mean-line-based blade front and back edge fitting and section line smooth reconstruction method | |
| CN106563754A (en) | Symmetrical forging formation method for double-body blades | |
| CN106844966B (en) | A kind of propeller blade face blade back Precise modeling | |
| CN113607119A (en) | Method for measuring throat area of marine gas turbine blade based on characteristic dimension | |
| CN109434020B (en) | Method for selecting section plate for casting and molding special-shaped blade | |
| CN102230786A (en) | Optical-measurement-based method for testing wall thickness of wax pattern for hollow turbine blade | |
| CN109614698B (en) | Geometric shape fitting method, device and medium for front edge of engine blade | |
| CN111806720A (en) | Rectification skin construction method based on measured data of wing body butt joint | |
| CN103413019A (en) | Discrete method of irregular outline double-curvature outer profile integral wallboard | |
| CN109409020B (en) | Modeling method of hollow fan blade | |
| CN106123725A (en) | The reverse implementation method of the compressor blade of correction various dimensions mismachining tolerance |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150204 |
|
| WD01 | Invention patent application deemed withdrawn after publication |