CN101474676A - Preparation method of high-temperature alloy turbine disc blank for aerial engine - Google Patents
Preparation method of high-temperature alloy turbine disc blank for aerial engine Download PDFInfo
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- CN101474676A CN101474676A CN 200910010310 CN200910010310A CN101474676A CN 101474676 A CN101474676 A CN 101474676A CN 200910010310 CN200910010310 CN 200910010310 CN 200910010310 A CN200910010310 A CN 200910010310A CN 101474676 A CN101474676 A CN 101474676A
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- cladding
- temperature alloy
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- turbine disc
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Abstract
A preparation method of a high temperature alloy turbine disk billet of an aeroengine is characterized by presetting high temperature alloy powder which has similar components and is suitable for cladding on a designed high temperature alloy mandrel by a high power (above (above 5000W) CO2 laser with stable cladding property and cladding, building up by welding and forming the powder to the dimension required by a turbine disk billet, and adding at least three elements from alloy elements Ni, B, Si, Y2O3 and Hf to the preset high temperature alloy powder. The preparation method improves the existing laser cladding forming technology, and realizes a breakthrough of preparing a large homogeneous billet of the turbine disk which is a core component of the aeroengine without cracks and pore defect by the laser cladding forming technology.
Description
Technical field
The present invention relates to a kind of preparation method of high-temperature alloy turbine disc blank for aerial engine, particularly relate to a kind of method that adopts laser fusing-covering forming technique to make high-temperature alloy turbine disc blank for aerial engine, belong to high-temperature alloy turbine disc blank for aerial engine and the laser fusing-covering forming technique field of making, the present invention is applicable to the production preparation of aerial motor spare part.
Background technology
High-temperature alloy turbine disc is a heart of aero engine, is the precise part that at high temperature rotates at a high speed with the speed of per minute commentaries on classics up to ten thousand, and is very high to the specification requirement of material, all is with special, high-quality high-temperature alloy material manufacturing.According to the operating characteristic requirement, turbine disk middle part requires to have high pi of strength, and tenon tooth portion in edge requires at high temperature to have good creep rupture strength and fatigue strength index.
Existing manufacture method is to prepare steel ingot by vacuum metling and electroslag remelting, then by the method for free forging and die forging, is processed into the cake blank, manufactures the turbine disk by a series of machine adding methods again.And the metallurgical quality level of China's high-temperature alloy material is lower, shows that mainly the degree of purity of material is low, and the alloy fluctuation is big, and is strict inadequately to the requirement of raw material and high-temperature material impurity and gas content, has influence on alloy property and stable.
Because the turbine disk alloying level height of high temperature alloy, the high-melting-point alloy element is many, also contains the element of many generation hardening constituents, the alloying component complexity, control difficulty to composition, surface and the inherent quality of steel ingot in the smelting is very big, component segregation very easily occurs.Because it is substance is bigger, also necessary integrated poured again, in cooling procedure, certainly will cause the skewness of high low melting point element, heart portion and surface quality occur and differ, cause ingot blank material heart portion intensity to reduce or deficiency, directly influence the serviceability of the turbine disk that produces.
In addition, no matter iron-based or nickel base superalloy, alloying level is higher, the hot processing temperature height, and the deformation temperature narrow range, resistance of deformation is big, and it is big than other steel grade to cause forging difficulty.Quality differs, the component distributing inequality if having during preceding working procedure is smelted again, and will further increase the forging difficulty, will occur various forging defects inevitably.Owing to be single alloying component, can't realize the specific (special) requirements of turbine core portion and edge simultaneously to material property.
Therefore, select suitable manufacture method, eliminate the lower phenomenon of blank of turbine disc component segregation and blank lumber recovery, reduce production costs, guarantee the serviceability at each position of the turbine disk of processing, to realize that the turbine disk made in one piece significantly reduces vibration, improves rotary speed, increases service life, be the current problem that needs to be resolved hurrily.
Laser fusing-covering forming technique has obtained rapid popularization and extensive use in recent years as a kind of advanced person's re-manufacturing technology.
Laser fusing-covering forming technique utilizes the high characteristics of high energy laser beam focused energy, moment will be preset or send the alloy powder of putting, have specific physical, chemistry or mechanical property to melt fully synchronously automatically with laser at substrate surface, base material part fusing simultaneously, form a kind of new compound material, rapid solidification after the laser beam flying, the fine and close coating of acquisition and matrix metallurgical binding is to reach the purpose of recovering physical dimension and surface peening.
Laser formation is exactly the built-up welding repeatedly of laser melting coating, is at the re-manufacturing technology repeatedly piled up of metal surface acquisition with the high-performance surface coating of the firm metallurgical binding of matrix.
At present about utilize laser melting coating or laser again manufacturing process to carry out patent and report that equipment component repairs a lot; for example; publication number is " based on the method for preparing novel gradient functional material fine blanking die of laser fusing-covering forming technique " that the Chinese invention patent application of CN101176950 provides; publication number is " a kind of Ni-base alloy powder laser melt-cladding sinter forming method " that Chinese invention patent application that the Chinese invention patent application of CN1483856 " the self-shield superfine active carbide alloy laser melting coating production technology " that provide and publication number are CN1883852 provides; but existing utilize laser melting coating or laser again the manufacturing process technology of carrying out the equipment component reparation all are application on medium and small parts; by preparing suitable cladding material; overcome the crackle that the laser crucible zone exists; the problem of pore and microstructure inhomogeneities (layering); obtain certain technique effect; and real core key part in aero-engine; especially on the large-scale blank of this key components and parts of the picture turbine disk; can adopt conventional laser cladding forming technology to carry out flawless and gas hole defect; the blank of turbine disc manufacturing of homogeneous; retrieve verification through the applicant: domestic beyond example still, do not see relevant report abroad yet.
Summary of the invention
The objective of the invention is to solve the problems referred to above that prior art exists, by research improvement repeatedly, provided a kind of preparation method of new high-temperature alloy turbine disc blank for aerial engine, this preparation method improves existing laser cladding forming technology, adopts high-power (more than the 5000W) CO of cladding stable performance first
2Laser instrument on the high temperature alloy plug basis of design, presets to the superalloy powder of the approaching and suitable cladding of branchs, and the cladding built-up welding is molded into the needed size of blank of turbine disc.
The technical scheme that the present invention provides is: the preparation method of this high-temperature alloy turbine disc blank for aerial engine includes following steps:
1. use high-power (more than the 5000W) CO of cladding stable performance
2Laser instrument on the high temperature alloy plug basis of design, presets to the superalloy powder of the approaching and suitable cladding of branchs, and the cladding built-up welding is molded into the needed size of blank of turbine disc.
The superalloy powder that presets, be on the high temperature alloy composition basis of design, suitably add again and reduce fusing point, improve wellability, increase the toughness phase, reduce cracking sensitivity, improve the alloying element of cladding performance, guarantee that the cladding of large tracts of land multilayer do not have mass defect.
2. add at least three kinds of elements in the following alloying element in the superalloy powder that presets again: Ni, B, Si, Y
2O
3And Hf.
3. the alloying element ratio of adding again in the superalloy powder that presets is:
Ni?0.5～2.0％，B?0.1～0.5％，Si?0.1～0.5％，
Y
2O
3?0.01～0.05％，Hf?0.01～0.05％。
4. in cladding operation, adopt 5000～10000W continuous CO that flows over
2Laser instrument, the melting and coating process parameter is: power: 4800～8000W, focal length: 300～400mm, spot size: 1.5 * 10mm, sweep speed: 240～400mm/min puts powder thickness: 0.5～1.0mm.In the cladding process inert gas shielding is adopted in the molten bath.
Compared with prior art, the invention has the beneficial effects as follows:
1. the production for the large-scale blank of aero-engine high-temperature alloy turbine disc provides brand-new manufacture method.
2. adopt the large-scale blank of the turbine disk of laser cladding forming technology manufacturing to solve many drawbacks such as the component segregation in the conventional production methods, cost height, rate of charge are big.
3. in the production of high-temperature alloy turbine disc blank for aerial engine, can realize the design of homogeneous or functionally gradient material (FGM), guarantee the requirement of each position of the turbine disk of processing to serviceability.
The specific embodiment
Embodiment 1:
With the high-power CO of the 10000W of cladding stable performance
2Laser instrument, laser melting coating built-up welding and GH4169 constituent class have added the superalloy powder of several increase elevated temperature strength alloying elements seemingly, again on the GH4169 high temperature alloy plug basis of design, and the component of several alloying elements of interpolation is (mass percent): Si 0.15%, Ni 1.2%, Y
2O
30.02%, Hf 0.01%, and cladding built-up welding moulding constitutes blank of turbine disc, through section flaw detection zero defect, send the commentaries on classics precision forging as turbine disk blank material.
Its melting and coating process parameter is: power: 8000W, and focal length: 300～360mm, spot size: 1.5 * 10mm, sweep speed: 320～400mm/min puts powder thickness: 0.5～1.0mm.In the cladding process inert gas shielding is adopted in the molten bath.
Embodiment 2:
With the high-power CO of the 5000W of cladding stable performance
2Laser instrument, laser melting coating built-up welding and GH4033 constituent class have added the superalloy powder of several increase elevated temperature strength alloying elements seemingly, again on the GH4033 high temperature alloy plug basis of design, and the component of several alloying elements of interpolation is (mass percent): B 0.005%, Si 0.2%, Y
2O
30.02%, Hf 0.01%, and cladding built-up welding moulding constitutes blank of turbine disc, through section flaw detection zero defect, send the commentaries on classics precision forging as turbine disk blank material.
Its melting and coating process parameter is: power: 4800W, and focal length: 320～380mm, spot size: 1.5 * 10mm, sweep speed: 240～360mm/min puts powder thickness: 0.5～1.0mm.In the cladding process inert gas shielding is adopted in the molten bath.
Embodiment 3:
With the high-power CO of the 5000W of cladding stable performance
2Laser instrument, laser melting coating built-up welding and GH4698 constituent class have added the superalloy powder of several increase elevated temperature strength alloying elements seemingly, again on the GH4698 high temperature alloy plug basis of design, and the component of several alloying elements of interpolation is (mass percent): Si 0.2%, Ni 1.6%, Y
2O
30.01%, Hf 0.01%.Cladding built-up welding moulding constitutes blank of turbine disc, through section flaw detection zero defect, send the commentaries on classics precision forging as turbine disk blank material.
Its melting and coating process parameter is: power: 4800W, and focal length: 320～380mm, spot size: 1.5 * 10mm, sweep speed: 240～360mm/min puts powder thickness: 0.5～1.0mm.In the cladding process inert gas shielding is adopted in the molten bath.
Claims (1)
1. the preparation method of a high-temperature alloy turbine disc blank for aerial engine is characterized in that including following steps:
(1) high-power (more than the 5000W) CO of usefulness cladding stable performance
2Laser instrument on the high temperature alloy plug basis of design, presets to the superalloy powder of the approaching and suitable cladding of branchs, and the cladding built-up welding is molded into the needed size of blank of turbine disc.
(2) add at least three kinds of elements in the following alloying element in the superalloy powder that presets again: Ni, B, Si, Y
2O
3And Hf;
The alloying element ratio of adding again in the superalloy powder that (3) presets is:
Ni?0.5～2.0％，B?0.1～0.5％，Si?0.1～0.5％，
Y
2O
3?0.01～0.05％，Hf?0.01～0.05％；
(4) in cladding operation, adopt 5000～10000W continuous CO that flows over
2Laser instrument, the melting and coating process parameter of the superalloy powder material of production is: power: 4800～8000W, focal length: 300～400mm, spot size: 1.5 * 10mm, sweep speed: 240～400mm/min puts powder thickness: 0.5～1.0mm.In the cladding process inert gas shielding is adopted in the molten bath.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200910010310 CN101474676B (en) | 2009-02-06 | 2009-02-06 | Preparation method of high-temperature alloy turbine disc blank for aerial engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200910010310 CN101474676B (en) | 2009-02-06 | 2009-02-06 | Preparation method of high-temperature alloy turbine disc blank for aerial engine |
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| Publication Number | Publication Date |
|---|---|
| CN101474676A true CN101474676A (en) | 2009-07-08 |
| CN101474676B CN101474676B (en) | 2012-01-18 |
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ID=40835497
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|---|---|---|---|
| CN 200910010310 Expired - Fee Related CN101474676B (en) | 2009-02-06 | 2009-02-06 | Preparation method of high-temperature alloy turbine disc blank for aerial engine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103707016A (en) * | 2013-12-10 | 2014-04-09 | 中国南方航空工业(集团)有限公司 | Broaching machining method for mortise of powder metallurgy superalloy turbine disc |
| CN106637198A (en) * | 2016-12-26 | 2017-05-10 | 江苏亚威创科源激光装备有限公司 | Manufacturing method for mould based on laser additive manufacturing and provided with gradient wear-resisting coating |
| CN107073584A (en) * | 2014-11-21 | 2017-08-18 | 西门子公司 | Manufacture the method and the part of part |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100439521C (en) * | 2005-04-19 | 2008-12-03 | 沈阳大陆激光技术有限公司 | Powdery alloy processing material in site by movable laser smelt-coating process |
-
2009
- 2009-02-06 CN CN 200910010310 patent/CN101474676B/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103707016A (en) * | 2013-12-10 | 2014-04-09 | 中国南方航空工业(集团)有限公司 | Broaching machining method for mortise of powder metallurgy superalloy turbine disc |
| CN103707016B (en) * | 2013-12-10 | 2016-09-21 | 中国南方航空工业(集团)有限公司 | The wire pulling method method of powder metallurgy superalloy turbine disc tongue-and-groove |
| CN107073584A (en) * | 2014-11-21 | 2017-08-18 | 西门子公司 | Manufacture the method and the part of part |
| CN107073584B (en) * | 2014-11-21 | 2019-01-08 | 西门子公司 | Manufacture the method and the component of component |
| US10518361B2 (en) | 2014-11-21 | 2019-12-31 | Siemens Aktiengesellschaft | Method of manufacturing a component and component |
| CN106637198A (en) * | 2016-12-26 | 2017-05-10 | 江苏亚威创科源激光装备有限公司 | Manufacturing method for mould based on laser additive manufacturing and provided with gradient wear-resisting coating |
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| Publication number | Publication date |
|---|---|
| CN101474676B (en) | 2012-01-18 |
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Effective date of registration: 20160831 Address after: 200941, A-171, room 1, 1758 Hong Kong Road, Nanhui new town, Shanghai, Pudong New Area Patentee after: SHANGHAI DALU TIANRUI LASER SURFACE ENGINEERING CO.,LTD. Address before: 110136 Shenyang, Shenbei New Area Province Economic Development Zone, justice, Shen North Road, No. 29, No. Patentee before: Shenyang Dalu Laser Technology Co.,Ltd. |
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Granted publication date: 20120118 Termination date: 20220206 |
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