CN105269824A - Rapid formation method of X-ray detecting device for blade of aviation engine - Google Patents
Rapid formation method of X-ray detecting device for blade of aviation engine Download PDFInfo
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- CN105269824A CN105269824A CN201510708284.4A CN201510708284A CN105269824A CN 105269824 A CN105269824 A CN 105269824A CN 201510708284 A CN201510708284 A CN 201510708284A CN 105269824 A CN105269824 A CN 105269824A
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- blade
- ray detector
- aviation engine
- drip molding
- forming method
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Abstract
The invention provides a rapid formation method of an X-ray detecting device for a blade of an aviation engine. The rapid formation method comprises the following steps: I, establishing a three-dimensional entity model of the X-ray detecting device according to the blade structure; II, slicing the model of the detecting device, and planning the laser scanning path of each layer; III, inputting the model on selective laser sintering equipment, setting the technological parameters of selective laser sintering, and adopting laser beams to scan powder material on each layer according to the planned scan path; IV, performing finishing treatment on the surface of a part after machining; V, enhancing the strength of a formed part; VI, after curing the part, removing the redundancy on the surface to obtain the X-ray detecting device. According to the rapid formation method, the technology is simple and easy to control, the operation is reliable, the production period is short, and the repeatability is high; the X-ray detecting device manufactured by adopting the rapid formation method is reliable in mechanical property, meets the operating requirements, and can realize rapid response manufacture according to different blade structures.
Description
Technical field
The present invention relates to the RP technique field of nonmetallic materials, specifically a kind of quick forming method of blade of aviation engine x-ray detector.
Background technology
Machining mode is mainly adopted to complete for blade x-ray detector at present, because blade profile mostly is complicated curved surface, and it is of a great variety, machining mode is difficult to manufacture the apparatus structure that even cannot manufacture and can coordinate blade profile completely, and the traditional approach process-cycle is long, stock utilization is low.
Tradition adopts selective laser sintering (SLS) technology, first threedimensional model is converted into certain thickness two-dimentional lamella information, then plans the laser beam scan path of every one deck, control laser beam and scanning pattern is scanned, make dusty material and adhered to one another, obtain the entity of this layer.After completing one deck scanning, forming cavity declines one deck paving powder height, carries out paving powder and the sintering of lower one deck, finally forms 3D solid part.Selectivity laser sintering forming element surface pore is more, and roughness is about Ra12.5, and intensity is low, can not meet the actual operation requirements of device.
Summary of the invention
The present invention is directed to above shortcomings in prior art, provide the quick forming method of the blade of aviation engine x-ray detector that a kind of technique is simply controlled, properties of product meet instructions for use.The present invention is achieved by the following technical solutions.
According to the quick forming method of a kind of blade of aviation engine x-ray detector provided by the invention, comprise the steps:
Step 1, set up the three-dimensional entity model of blade x-ray detector according to blade construction;
Step 2, slicing treatment is carried out to described three-dimensional entity model, plan the laser beam scan path that every layer of section is corresponding;
Step 3, dusty material is put into the hopper of Selective Laser Sintering, three-dimensional entity model is input in Selective Laser Sintering, the technological parameter of setting selective laser sintering, each layer dusty material that difference that the laser beam of Selective Laser Sintering scans according to described laser beam scan path and each layer is cut into slices is corresponding, until selective laser sintering process finishing, obtain drip molding;
Step 4, use explosion-proof dust catcher draw selective laser sintering process unnecessary powder, take out drip molding, polishing process is carried out to drip molding surface.
Preferably, also comprise the steps:
Step 5, by epoxy resin, bisphenol-A E51 epoxy resin modification amine hardener according to even coated molded surface after the ratio mixing of 3:1, strengthen the intensity of drip molding;
Step 6, the drip molding of dipped resin is put into electric heating constant-temperature blowing drying box, take out after to be formed solidification, Material removal part excess surface thing, obtains blade x-ray detector.
Preferably, the material of described blade x-ray detector is polystyrene.
Preferably, described dusty material adopts granularity to be 100 object Polystyrene powders.
Preferably, the laser power shaping the laser beam of part entity part is 12W, and the laser power shaping the laser beam of part support section is 10W.
Preferably, described technological parameter is: sweep span 0.15mm, sweep speed 1800mm/s, slice thickness 0.20mm, preheat temperature 110 DEG C.
Preferably, the method for described polishing process is: use file to remove excess surface thing, then uses No. 1500 sand paper to remove the floating powder on surface.
Preferably, described coated molded surperficial method is:
Drip molding is put into the mixing material of well-mixed epoxy resin, bisphenol-A E51 epoxy resin modification amine hardener, leave standstill 5-10 minute and take out, leave standstill in atmosphere, after 1 minute, drip molding is put into described mixing material again, leave standstill 2 minutes and take out.
Preferably, the method for described drip molding solidification is:
Drip molding is put into the electric heating constant-temperature blowing drying box that temperature is 45 DEG C, leave standstill 4 hours and take out.
Preferably, set up the three-dimensional entity model of blade x-ray detector by 3 d modeling software, wherein, described 3 d modeling software is Pro/E software or Magics software; Carry out slicing treatment by Slice Software to described three-dimensional entity model, wherein, described Slice Software is Magics software.
Compared with prior art, the present invention has following beneficial effect:
1, the Selective Laser Sintering that the present invention adopts can manufacture the blade x-ray detector of curved surface complexity, and can realize the rapid response manufacturing with blade construction change, and treated drip molding any surface finish, mechanical property meets the demands.
2, instant invention overcomes the deficiency that classical production process manufactures x-ray detector, selective laser sintering (SLS) method is adopted to manufacture blade x-ray detector structure, and carry out polishing process for the shaggy shortcoming of drip molding, then adopt resin to strengthen drip molding mechanical property.
3, the present invention can overcome the processing of traditional approach manufacture blade x-ray detector difficulty, macrocyclic shortcoming, and the change that can adapt to blade design realizes rapid response manufacturing, has many excellent characteristics such as short period.
4, the blade x-ray detector utilizing the present invention to be shaped, smooth surface, forming accuracy meets the demands; Not only solve and adopt conventional machine processing mode to manufacture the problem that the checkout gear cycle is long, qualification rate is low, and improve the utilization rate of material, reduce manufacturing cost.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the selective laser sintering (SLS) process chart of blade x-ray detector of the present invention.
Fig. 2 is the selective laser sintering (SLS) equipment drawing that blade x-ray detector of the present invention adopts.
Fig. 3 is blade x-ray detector of the present invention and blade scheme of installation when using.
In figure: 1 is lifting workbench; 2 is hopper; 3 is Pu Fen mechanism; 4 is laser instrument; 5 is dusty material; 6 is blade; 7 is blade x-ray detector.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some changes and improvements can also be made.These all belong to protection scope of the present invention.
As shown in Figure 1, according to the quick forming method of a kind of blade of aviation engine x-ray detector provided by the invention, comprise the steps:
Step 1, set up the three-dimensional entity model of blade x-ray detector according to blade construction; Preferably, set up the three-dimensional entity model of blade x-ray detector by 3 d modeling software, wherein, described 3 d modeling software is Pro/E software or Magics software;
Step 2, slicing treatment is carried out to described three-dimensional entity model, plan the laser beam scan path that every layer of section is corresponding;
Step 3, dusty material is put into the hopper of Selective Laser Sintering, three-dimensional entity model is input in Selective Laser Sintering, the technological parameter of setting selective laser sintering, each layer dusty material that difference that the laser beam of Selective Laser Sintering scans according to described laser beam scan path and each layer is cut into slices is corresponding, until selective laser sintering process finishing, obtain drip molding; Preferably, carry out slicing treatment by Slice Software to described three-dimensional entity model, wherein, described Slice Software is Magics software;
Step 4, use explosion-proof dust catcher draw selective laser sintering process unnecessary powder, take out drip molding, polishing process is carried out to drip molding surface;
Step 5, by epoxy resin, bisphenol-A E51 epoxy resin modification amine hardener according to even coated molded surface after the ratio mixing of 3:1, strengthen the intensity of drip molding; Described coated molded surperficial method is: mixing material drip molding being put into well-mixed epoxy resin, bisphenol-A E51 epoxy resin modification amine hardener, leave standstill 5-10 minute and take out, leave standstill in atmosphere, after 1 minute, drip molding is put into described mixing material again, leave standstill 2 minutes and take out;
Step 6, the drip molding of dipped resin is put into electric heating constant-temperature blowing drying box, take out after to be formed solidification, Material removal part excess surface thing, obtains blade x-ray detector.The method of described drip molding solidification is: drip molding is put into the electric heating constant-temperature blowing drying box that temperature is 45 DEG C, leave standstill 4 hours and take out.
Preferably, the material of described blade x-ray detector is polystyrene.
Preferably, described dusty material adopts granularity to be 100 object Polystyrene powders.
Preferably, the laser power shaping the laser beam of part entity part is 12W, and the laser power shaping the laser beam of part support section is 10W.
Preferably, described technological parameter is: sweep span 0.15mm, sweep speed 1800mm/s, slice thickness 0.20mm, preheat temperature 110 DEG C.
Preferably, the method for described polishing process is: use file to remove excess surface thing, then uses No. 1500 sand paper to remove the floating powder on surface.
As shown in Figure 2, the computer of described Selective Laser Sintering is built with 3 d modeling software and Slice Software.Described 3 d modeling software can adopt Pro/E software or Magics software, and Slice Software can adopt Magics software.
As shown in Figure 3, the concrete specification of the present embodiment blade x-ray detector is: material is polystyrene, is of a size of 120mm × 65mm × 40mm.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make a variety of changes within the scope of the claims or revise, and this does not affect flesh and blood of the present invention.When not conflicting, the feature in the embodiment of the application and embodiment can combine arbitrarily mutually.
Claims (10)
1. a quick forming method for blade of aviation engine x-ray detector, is characterized in that, comprises the steps:
Step 1, set up the three-dimensional entity model of blade x-ray detector according to blade construction;
Step 2, slicing treatment is carried out to described three-dimensional entity model, plan the laser beam scan path that every layer of section is corresponding;
Step 3, dusty material is put into the hopper of Selective Laser Sintering, three-dimensional entity model is input in Selective Laser Sintering, the technological parameter of setting selective laser sintering, each layer dusty material that difference that the laser beam of Selective Laser Sintering scans according to described laser beam scan path and each layer is cut into slices is corresponding, until selective laser sintering process finishing, obtain drip molding;
Step 4, use explosion-proof dust catcher draw selective laser sintering process unnecessary powder, take out drip molding, polishing process is carried out to drip molding surface.
2. the quick forming method of blade of aviation engine x-ray detector according to claim 1, is characterized in that, also comprise the steps:
Step 5, by epoxy resin, bisphenol-A E51 epoxy resin modification amine hardener according to even coated molded surface after the ratio mixing of 3:1, strengthen the intensity of drip molding;
Step 6, the drip molding of dipped resin is put into electric heating constant-temperature blowing drying box, take out after to be formed solidification, Material removal part excess surface thing, obtains blade x-ray detector.
3. the quick forming method of blade of aviation engine x-ray detector according to claim 1, is characterized in that, the material of described blade x-ray detector is polystyrene.
4. the quick forming method of blade of aviation engine x-ray detector according to claim 1, is characterized in that, described dusty material adopts granularity to be 100 object Polystyrene powders.
5. the quick forming method of blade of aviation engine x-ray detector according to claim 1, is characterized in that, the laser power shaping the laser beam of part entity part is 12W, and the laser power shaping the laser beam of part support section is 10W.
6. the quick forming method of blade of aviation engine x-ray detector according to claim 1, is characterized in that, described technological parameter is: sweep span 0.15mm, sweep speed 1800mm/s, slice thickness 0.20mm, preheat temperature 110 DEG C.
7. the quick forming method of blade of aviation engine x-ray detector according to claim 1, is characterized in that, the method for described polishing process is: use file to remove excess surface thing, then uses No. 1500 sand paper to remove the floating powder on surface.
8. the quick forming method of blade of aviation engine x-ray detector according to claim 2, is characterized in that, described coated molded surperficial method is:
Drip molding is put into the mixing material of well-mixed epoxy resin, bisphenol-A E51 epoxy resin modification amine hardener, leave standstill 5-10 minute and take out, leave standstill in atmosphere, after 1 minute, drip molding is put into described mixing material again, leave standstill 2 minutes and take out.
9. the quick forming method of blade of aviation engine x-ray detector according to claim 2, is characterized in that, the method for described drip molding solidification is:
Drip molding is put into the electric heating constant-temperature blowing drying box that temperature is 45 DEG C, leave standstill 4 hours and take out.
10. the quick forming method of blade of aviation engine x-ray detector according to claim 1, it is characterized in that, set up the three-dimensional entity model of blade x-ray detector by 3 d modeling software, wherein, described 3 d modeling software is Pro/E software or Magics software; Carry out slicing treatment by Slice Software to described three-dimensional entity model, wherein, described Slice Software is Magics software.
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| CN201510708284.4A CN105269824A (en) | 2015-10-27 | 2015-10-27 | Rapid formation method of X-ray detecting device for blade of aviation engine |
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| CN201510708284.4A CN105269824A (en) | 2015-10-27 | 2015-10-27 | Rapid formation method of X-ray detecting device for blade of aviation engine |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105880467A (en) * | 2016-06-01 | 2016-08-24 | 洛阳双瑞精铸钛业有限公司 | Method for producing high-accuracy PS powder model precision castings |
| CN108021770A (en) * | 2017-12-04 | 2018-05-11 | 北京理工大学 | Leaf longevity evaluation method based on CT scan |
| CN108115938A (en) * | 2017-11-16 | 2018-06-05 | 芜湖林电子科技有限公司 | A kind of 3D printing raw material automatic recovery system |
| CN108115937A (en) * | 2017-11-16 | 2018-06-05 | 芜湖林电子科技有限公司 | A kind of 3D printing impurity method for cleaning based on Image Acquisition |
| CN114309642A (en) * | 2020-09-29 | 2022-04-12 | 中国航发商用航空发动机有限责任公司 | Method for additive manufacturing of an aircraft engine component and readable storage medium |
| CN114378309A (en) * | 2021-12-29 | 2022-04-22 | 天翼物联科技有限公司 | Flexible manufacturing system and flexible manufacturing method for complex component |
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| CN1970202A (en) * | 2006-12-08 | 2007-05-30 | 华中科技大学 | Method for selective laser sintering for quick and direct production of injection die |
| CN101401746A (en) * | 2008-10-30 | 2009-04-08 | 华中科技大学 | Method for quickly producing removalbe partial denture bracket |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105880467A (en) * | 2016-06-01 | 2016-08-24 | 洛阳双瑞精铸钛业有限公司 | Method for producing high-accuracy PS powder model precision castings |
| CN105880467B (en) * | 2016-06-01 | 2018-04-24 | 洛阳双瑞精铸钛业有限公司 | A kind of method for producing high-precision PS powder model precision castings |
| CN108115938A (en) * | 2017-11-16 | 2018-06-05 | 芜湖林电子科技有限公司 | A kind of 3D printing raw material automatic recovery system |
| CN108115937A (en) * | 2017-11-16 | 2018-06-05 | 芜湖林电子科技有限公司 | A kind of 3D printing impurity method for cleaning based on Image Acquisition |
| CN108021770A (en) * | 2017-12-04 | 2018-05-11 | 北京理工大学 | Leaf longevity evaluation method based on CT scan |
| CN114309642A (en) * | 2020-09-29 | 2022-04-12 | 中国航发商用航空发动机有限责任公司 | Method for additive manufacturing of an aircraft engine component and readable storage medium |
| CN114309642B (en) * | 2020-09-29 | 2024-01-12 | 中国航发商用航空发动机有限责任公司 | Additive manufacturing method of aeroengine component and readable storage medium |
| CN114378309A (en) * | 2021-12-29 | 2022-04-22 | 天翼物联科技有限公司 | Flexible manufacturing system and flexible manufacturing method for complex component |
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