CN105149582B - Laser engineered net shaping method for ternary impeller blade - Google Patents
Laser engineered net shaping method for ternary impeller blade Download PDFInfo
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- CN105149582B CN105149582B CN201510481989.7A CN201510481989A CN105149582B CN 105149582 B CN105149582 B CN 105149582B CN 201510481989 A CN201510481989 A CN 201510481989A CN 105149582 B CN105149582 B CN 105149582B
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Abstract
The invention discloses a laser engineered net shaping method for a ternary impeller blade, and belongs to the technical field of laser 3D printing. A whole impeller blade is segmented according to the inclination angle and torsion angle of the impeller blade, a reasonable preset included angle is set between a laser beam and the perpendicular direction for the segmented impeller blade, and then impeller blade shaping is performed. The ternary impeller blade with the inclination angle of 0-75 degrees and the torsion angle of 0-90 degrees can be shaped on the three-axis open-loop condition. The hardware requirement of the laser engineered net shaping method for a laser engineered net shaping system is low, the equipment complexity and the part machining cost are reduced, no support needs to be added for a three-dimensional model in a three-dimensional modeling process, the technological process is simple, machining efficiency is high, and materials are saved.
Description
Technical field
The invention belongs to laser 3D printing technical field, it is related to a kind of 3 d impeller blade laser near-net-shape method.
Background technology
3 d impeller blade is the main composition of the modern times such as aircraft engine, steam turbine and turbocompressor power set
Part, it is that thin-wall part is reversed in a kind of complicated space, is inclined and the big architectural feature reversed with big, mechanical processing difficulty compared with
Greatly.Traditional 3 d impeller blade machining process mainly includes：Precision forging, five-shaft numerical control milling and numerical control Electrolyzed Processing.Adopt
When processing 3 d impeller blade with above-mentioned processing mode, cause a large amount of expensive in the forging mold or process that generally require complexity
The waste of heavy material, the process-cycle is more long, and processing cost is higher.
Laser near-net-shape technology is a kind of new quick 3D printing (increasing material manufacturing) technology, can realize various property high
Can, labyrinth it is quick, without mould, full densification near-net-shape.It is that shaping 3 d impeller blade etc. is big using 5 Shaft and NC Machining Test systems
Inclination, a kind of common method of big torsion structure, but 5 Shaft and NC Machining Test systems are high to the hardware requirement of laser near-net-shape system, increase
Add equipment complexity and part processing cost, therefore, how to shape with form accuracy high three under 3 axle open loop conditions
First impeller blade has realistic meaning.
At present, laser near-net-shape 3 d impeller blade is mainly by blade under the conditions of 3 axle opened loop controls
Cantilever design is realized with the mode of pendency position addition Auxiliary support.
Zhang Hang, middle areas in Shandong Province is good, Yang Qiang, Li Dichen, a kind of metal laser direct-forming closely related alloy turbine engine thermal end high
The method of part, Chinese invention patent, publication number CN104368814A discloses a kind of metal laser direct-forming closely related alloy whirlpool high
The method of turbine hot-end component, the method utilizes metal laser direct-forming technology, under 3 Shaft and NC Machining Test running conditionses,
By way of cantilever design and pendency position in turbo blade add Auxiliary support, closely related alloy powder high is directly processed
Shaping, has obtained the turbogenerator hot-end component such as turbine stator vane, turbine moving blade.Needed in three-dimensional modeling using the method
During to threedimensional model add support, then needed during following process by unnecessary supporting construction remove, technological process
Complexity, waste of material is serious.
The content of the invention
To solve under 3 axle open loop conditions, need to add Auxiliary support during 3 d impeller blade laser near-net-shape
Problem, the present invention proposes a kind of 3 d impeller blade laser near-net-shape method.
A kind of 3 d impeller blade laser near-net-shape method, step is as follows：
A, three-dimensional entity model is set up to 3 d impeller blade to be formed, then threedimensional model is carried out by certain thickness
Slicing delamination, obtains the outline data in each section, 0 °~75 ° of described 3 d impeller blade pitch angle, 0 ° of windup-degree
~90 °；The described thickness that slicing delamination is carried out to three-dimensional entity model is 0.1-0.5mm；
B, whole blade is divided into by low-angle section, middle angular segments and big angle according to impeller blade angle of inclination and windup-degree
Degree section, described low-angle 0 °~30 ° of maximum tilt angle of section, 0 °~0.2 ° of interlayer windup-degree；Described middle angular segments are most
Big 30 °~45 ° of angle of inclination, 0 °~0.35 ° of interlayer windup-degree；Described wide-angle 45 °~75 ° of maximum tilt angle of section,
0 °~1.28 ° of interlayer windup-degree；
C, for described impeller blade low-angle section, laser head and vertical direction are deflected into certain angle, as laser
Beam presets angle with vertical direction, and described default angle is 0 °~30 °；It is sharp for angular segments in described impeller blade
Light beam presets angle with vertical direction, and described default angle is 15 °~30 °；For described impeller blade wide-angle section, it is
Laser beam presets angle with vertical direction, and described default angle is 40 °~45 °；
D, the outline data that will be obtained and default angle information import laser near-net-shape equipment, start laser near net into
Shape system, starts to shape 3 d impeller blade.
A kind of 3 d impeller blade laser near-net-shape method proposed by the present invention has advantages below：
1st, a kind of described 3 d impeller blade laser near-net-shape method, can shape under 3 axle open loop conditions and incline
0 °~75 ° of rake angle, the 3 d impeller blade that 0 °~90 ° of windup-degree, the hardware requirement to laser near-net-shape system is relatively low,
Reduce equipment complexity and part processing cost；
2nd, a kind of described 3 d impeller blade laser near-net-shape method, it is not necessary to three-dimensional during three-dimensional modeling
Model addition support, it is to avoid supporting construction is removed during following process, technological process is simple, high in machining efficiency, saves
Material.
Brief description of the drawings
Accompanying drawing is 3 d impeller blade laser near-net-shape method schematic diagram of the present invention.
In figure：1 impeller blade angle of inclination；2 impeller blade windup-degrees；3 impeller blade low-angles section；4 impeller blades
Middle angular segments；5 impeller blade wide-angles section；6 laser heads；7 laser beams preset angle with vertical direction.
Specific embodiment
The present invention is further described with reference to the accompanying drawings and examples.In embodiment, selected laser near net into
Shape parameter is：Laser power 1000W, sweep speed 360mm/min, powder sending quantity is 3.6g/min；Powder used is 316 stainless steels
Powder, is fitted into the powder feeding cylinder of powder feeder after drying；Stainless steel substrate sand papering used simultaneously uses alcohol wipe.
Comprise the following steps that：
A, three-dimensional entity model is set up to 3 d impeller blade to be formed, then threedimensional model is entered by thickness 0.2mm
Row slicing delamination, obtains the outline data in each section, described 0 ° of 3 d impeller blade pitch angle~65 °, windup-degree
0 °~90 °；
B, whole blade is divided into by the low-angle section 3, and of middle angular segments 4 according to impeller blade angle of inclination 1 and windup-degree 2
Wide-angle section 5, described low-angle 30 ° of 3 maximum tilt angle of section, 0.2 ° of interlayer windup-degree；Described middle angular segments 4 are maximum
45 ° of angle of inclination, 0.13 ° of interlayer windup-degree；Described wide-angle 65 ° of maximum tilt angle of section, interlayer windup-degree
0.29°；
C, for described impeller blade low-angle section 3, laser head 6 and vertical direction are deflected into certain angle, as swash
Light beam presets angle with vertical direction, and described default angle 7 is 15 °；It is laser for angular segments in described impeller blade
Beam presets angle with vertical direction, and described default angle 7 is 20 °；It is laser beam for described impeller blade wide-angle section
Angle is preset with vertical direction, described default angle 7 is 40 °；
D, the outline data that will be obtained and default angle information import laser near-net-shape equipment, start laser near net into
Shape system, starts to shape 3 d impeller blade.
Example described above is only the present invention preferably specific embodiment, but protection scope of the present invention is not limited to
This, any one skilled in the art the invention discloses technical scope in, technology according to the present invention scheme
And its inventive concept is subject to equivalent or change, should all be included within the scope of the present invention.
Claims (2)
1. a kind of 3 d impeller blade laser near-net-shape method, it is characterised in that step is as follows：
A, three-dimensional entity model is set up to 3 d impeller blade to be formed, section point is then carried out to the three-dimensional entity model
Layer, obtains the outline data in each layering section, and described 0 °~75 ° of 3 d impeller blade pitch angle to be formed is reversed
0 °~90 ° of angle；
B, whole blade is divided into by low-angle section, middle angular segments and big angle according to 3 d impeller blade pitch angle and windup-degree
Degree section, described low-angle 0 °~30 ° of maximum tilt angle of section, 0 °~0.2 ° of interlayer windup-degree；Described middle angular segments are most
Big 30 °~45 ° of angle of inclination, 0 °~0.35 ° of interlayer windup-degree；Described wide-angle 45 °~75 ° of maximum tilt angle of section,
0 °~1.28 ° of interlayer windup-degree；
C, for described 3 d impeller blade low-angle section, laser head and vertical direction are deflected into certain angle, as laser
Beam presets angle with vertical direction, and described default angle is 0 °~30 °；It is sharp for angular segments in described impeller blade
Light beam presets angle with vertical direction, and described default angle is 15 °~30 °；For described impeller blade wide-angle section, it is
Laser beam presets angle with vertical direction, and described default angle is 40 °~45 °；
D, the outline data in each layering section that will be obtained in step A and the default angle information of obtain each section of step C
Laser near-net-shape equipment is imported, starts laser near-net-shape system, start to shape 3 d impeller blade.
2. 3 d impeller blade laser near-net-shape method according to claim 1, it is characterised in that described in step A
The thickness that slicing delamination is carried out to three-dimensional entity model be 0.1-0.5mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510481989.7A CN105149582B (en) | 2015-08-09 | 2015-08-09 | Laser engineered net shaping method for ternary impeller blade |
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| CN201510481989.7A CN105149582B (en) | 2015-08-09 | 2015-08-09 | Laser engineered net shaping method for ternary impeller blade |
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| CN105149582B true CN105149582B (en) | 2017-05-24 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106077643B (en) * | 2016-07-26 | 2018-06-01 | 西安航天发动机厂 | A kind of integral manufacturing method of S-04 high strength stainless steels or S-08 high strength stainless steel three-dimensional closed impellers |
| EP3421157A1 (en) * | 2017-06-30 | 2019-01-02 | Sulzer Management AG | Method for producing an impeller of a rotary machine and impeller produced according to such a method |
| CN107999932B (en) * | 2017-11-29 | 2020-03-31 | 西南交通大学 | Arc length feedforward detection and open-loop control method for GTA filler wire additive manufacturing |
| CN109514075B (en) * | 2018-10-23 | 2021-05-18 | 上海航天设备制造总厂有限公司 | Laser near-net forming method for stirring head of functionally graded friction stir welding |
| JP7263838B2 (en) * | 2019-02-27 | 2023-04-25 | セイコーエプソン株式会社 | Modeling method of three-dimensional object |
| CN113714513A (en) * | 2021-08-04 | 2021-11-30 | 上海航天设备制造总厂有限公司 | Method for manufacturing spherical storage tank of spacecraft based on laser near-net-shape forming technology |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011127195A (en) * | 2009-12-18 | 2011-06-30 | Amada Co Ltd | Apparatus for producing 3-dimensional shaped article |
| CN103624258A (en) * | 2013-11-11 | 2014-03-12 | 西安交通大学 | System and method for forming laser metal manufacturing part with large inclination angle |
| CN104308153A (en) * | 2014-10-27 | 2015-01-28 | 西安交通大学 | High-entropy alloy hot-end part manufacturing method of turbine engine on basis of selective laser melting |
| CN104368814A (en) * | 2014-11-11 | 2015-02-25 | 西安交通大学 | Method for directly molding high-entropy alloy turbine engine hot end component through laser metal |
| CN104625059A (en) * | 2015-01-21 | 2015-05-20 | 大连理工大学 | Laser engineered net shaping method of supporting-free inclined structure |
-
2015
- 2015-08-09 CN CN201510481989.7A patent/CN105149582B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011127195A (en) * | 2009-12-18 | 2011-06-30 | Amada Co Ltd | Apparatus for producing 3-dimensional shaped article |
| CN103624258A (en) * | 2013-11-11 | 2014-03-12 | 西安交通大学 | System and method for forming laser metal manufacturing part with large inclination angle |
| CN104308153A (en) * | 2014-10-27 | 2015-01-28 | 西安交通大学 | High-entropy alloy hot-end part manufacturing method of turbine engine on basis of selective laser melting |
| CN104368814A (en) * | 2014-11-11 | 2015-02-25 | 西安交通大学 | Method for directly molding high-entropy alloy turbine engine hot end component through laser metal |
| CN104625059A (en) * | 2015-01-21 | 2015-05-20 | 大连理工大学 | Laser engineered net shaping method of supporting-free inclined structure |
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