CN101480761B - Method for preparing blank of turbine disc with gradient function of aerial engine - Google Patents
Method for preparing blank of turbine disc with gradient function of aerial engine Download PDFInfo
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- CN101480761B CN101480761B CN 200910010308 CN200910010308A CN101480761B CN 101480761 B CN101480761 B CN 101480761B CN 200910010308 CN200910010308 CN 200910010308 CN 200910010308 A CN200910010308 A CN 200910010308A CN 101480761 B CN101480761 B CN 101480761B
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Abstract
The invention relates to a preparation method for blank of a graded functional turbine disc of an aero-engine, which is characterized in that presetting congruent and coating-suitable high-temperature alloy powder A with the same components by a high-power (above 5000W) CO2 laser with stable coating performance based on the design of a high-temperature alloy mandrel, coating, surfacing and forming the high-temperature alloy powder A into the needed core blank size, then presetting high-temperature alloy powder B on the edge of the blank, and continuously coating, surfacing and forming the high-temperature alloy powder B into the needed blank size of the whole turbine disc, wherein the high-temperature alloy powder A is added with at least three of the following elements: Al, Ti, Si, Y2O3 and Hf besides the component of the high-temperature alloy mandrel, and the high-temperature alloy powder B is added with at least three of the following elements: Ni, Nb, Si, Y2O3 and Hf, besides the component of the high-temperature alloy mandrel. The invention improves the prior laser cladding forming process to be suitable for the preparation of blank for functionally graded turbine disk of aero-engines.
Description
Technical field
The present invention relates to a kind of preparation method of blank of turbine disc with gradient function of aerial engine; Particularly relate to a kind of preparation method who adopts laser fusing-covering forming technique to make blank of turbine disc with gradient function of aerial engine, belong to preparation blank of turbine disc with gradient function of aerial engine and laser fusing-covering forming technique field.
Background technology
The turbine disk of aero-engine 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; The turbine disk middle part of aero-engine requires to have high pi of strength; And edge part requires at high temperature to have good creep rupture strength and fatigue strength index, existing manufacturing approach to use single high-temperature alloy material to be difficult to realize this characteristic.
Existing manufacturing approach is through vacuum metling and electroslag remelting, prepares steel ingot, then through the method for free forging and die forging, is processed into the cake blank, manufactures the turbine disk through 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 is high with the alloying level of high temperature alloy; The high-melting-point alloy element is many, also contains the element of many generation hardening constituents, and alloying component is complicated; 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, edge stress is concentrated; Creep rupture strength and fatigue behaviour descend, and directly influence the serviceability of the turbine disk that produces.
In addition, no matter iron-based or nickel base superalloy, alloying level is higher, and hot processing temperature is high, the deformation temperature narrow range, and resistance of deformation is big, and it is big than other steel grade to cause forging difficulty.Quality differs, component distributing uneven 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 at all.
Therefore; Select suitable manufacturing approach; The serviceability at each position of the turbine disk of eliminate the lower phenomenon of blank of turbine disc component segregation and blank lumber recovery, reduce production costs, guaranteeing to process; 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 forms 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 the re-manufacturing technology of piling up repeatedly that obtains in the metal surface 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 the patent that equipment component repairs a lot of with report; For example; " a kind of Ni-base alloy powder laser melt-cladding sinter forming method " that the Chinese invention patent application that " self-shield superfine active carbide alloy laser melting coating production technology " that the Chinese invention patent application that publication number is " based on the method for preparing novel gradient functional material fine blanking die of laser fusing-covering forming technique " that provides of the Chinese invention patent application of CN101176950, publication number is CN1483856 provides 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 the application on medium and small parts; Through preparing suitable cladding material; Overcome the problem of crackle, pore and the microstructure inhomogeneities (layering) of the existence of laser crucible zone; 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; Carry out flawless and gas hole defect, have the blank of turbine disc manufacturing of gradient function, 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; Through research improvement repeatedly; Provided a kind of preparation method of new blank of turbine disc with gradient function of aerial engine; This production method is improved existing laser cladding forming technology, removes high-power (more than the 5000W) CO that adopts the cladding stable performance
2Outside the laser instrument, also combine to select the gradient function alloy powder material for use, carry out the blank of turbine disc with gradient function manufacturing, solve the many drawbacks that occur easily in the conventional production methods, realized the characteristic requirements that turbine disk high temperature uses down fruitfully.
The technical scheme that the present invention provides is: the preparation method of this blank of turbine disc with gradient function of aerial engine includes following steps:
1. with high-power (more than the 5000W) CO of cladding stable performance
2Laser instrument; On the high temperature alloy plug basis of design; Preset the superalloy powder A of congruent and suitable cladding earlier; The cladding built-up welding is molded into needed heart portion blank dimension, presets superalloy powder B at the blank edge again, continues the cladding built-up welding and is molded into needed whole turbine disk blank dimension.
2. said at least three kinds of elements that in the component of the superalloy powder A that blank heart portion presets, except that the component of high temperature alloy plug, add again in the following alloying element: Al, Ti, Si, Y
2O
3And Hf; Except that the component of high temperature alloy plug, add at least three kinds of elements in the following alloying element in the component of the superalloy powder B that presets at the blank edge again: Ni, Nb, Si, Y
2O
3And Hf.
3. said alloying element ratio of in the component of the superalloy powder A that blank heart portion presets, except that the component of high temperature alloy plug, adding again is:
Al?0.2～2.0％、Ti?0.5～3.0％、Si?0.1～0.5％、
Y
2O
3?0.01～0.05％、Hf?0.01～0.05％；
The alloying element ratio of except that the component of high temperature alloy plug, adding again in the component of the said superalloy powder B that presets at the blank edge is:
Ni?0.5～2.0％、Nb?0.2～1.0％、Si?0.2～0.6％、
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, its 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. brand-new preparation method is provided for the production of blank of turbine disc with gradient function of aerial engine.
2. adopt the blank of this method preparation to solve many drawbacks such as the component segregation in the conventional production methods, cost is high, rate of charge is big.
3. in the preparation of blank of turbine disc with gradient function of aerial engine, realized the design and the application of functionally gradient material (FGM), can guarantee of the requirement of each position of the turbine disk 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 several kinds of superalloy powder A that increase the elevated temperature strength alloying elements seemingly, again on the GH4169 high temperature alloy plug basis of design, and the component of alloying element is (mass percent): Si0.15%, Ni 1.2%, Y
2O
30.02%, Hf 0.01%, and the cladding built-up welding is molded into needed turbine core portion blank dimension; Cladding built-up welding and GH738 constituent class have added several kinds of superalloy powder B that increase creep rupture strength and fatigue strength alloying element seemingly, again at the blank edge again, and the component of alloying element is (mass percent): Ni 2.0%, Nb 0.6%, Si 0.2%, Y
2O
30.01%, Hf 0.01%, continues cladding built-up welding moulding and constitutes turbine disk cylindrical portion blank.Through section flaw detection zero defect, send the commentaries on classics precision forging as blank of turbine disc.
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 several kinds of superalloy powder A that increase the elevated temperature strength alloying elements seemingly, again on the GH4033 high temperature alloy plug basis of design, and the component of alloying element is (mass percent): B0.005%, Si0.2%, Y
2O
30.02%, Hf 0.01%, and the cladding built-up welding is molded into needed turbine core portion blank dimension; Cladding built-up welding and GH738 constituent class have added several kinds of superalloy powder B that increase creep rupture strength and fatigue strength alloying element seemingly, again at the blank edge again, and the component of alloying element is (mass percent): Ni 2.0%, Nb 0.6%, Si 0.2%, Y
2O
30.01%, Hf 0.01%, continues cladding built-up welding moulding and constitutes turbine disk cylindrical portion blank.Through section flaw detection zero defect, send the commentaries on classics precision forging as blank of turbine disc.
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 several kinds of superalloy powder A that increase the elevated temperature strength alloying elements seemingly, again on the GH4698 high temperature alloy plug basis of design, and the component of alloying element is (mass percent): Si0.2%, Ni 1.6%, Y
2O
30.01%, Hf 0.01%, and the cladding built-up welding is molded into needed turbine core portion blank dimension; Cladding built-up welding and GH738 constituent class have added several kinds of superalloy powder B that increase creep rupture strength and fatigue strength alloying element seemingly, again at the blank edge again, and the component of alloying element is (mass percent): Ni 2.0%, Nb 0.6%, Si 0.2%, Y
2O
30.01%, Hf 0.01%, continues cladding built-up welding moulding and constitutes turbine disk cylindrical portion blank.Through section flaw detection zero defect, send the commentaries on classics precision forging as blank of turbine disc.
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 blank of turbine disc with gradient function of aerial engine adopts 5000～10000W continuous CO that flows in the cladding operation
2Laser instrument, its 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, it is characterized in that:
With the high-power CO of the 10000W of cladding stable performance
2Laser instrument; Laser melting coating built-up welding and this high temperature alloy plug constituent class have added several kinds of superalloy powder A that increase elevated temperature strength alloying element and rare earth oxide seemingly, again on the GH4169 high temperature alloy plug basis of design, and the component of except that the component of high temperature alloy plug, adding again in the component of superalloy powder A is counted with mass percent: Si0.15%, Ni 1.2%, Y
2O
30.02%, Hf 0.01%, and the cladding built-up welding is molded into needed turbine core portion blank dimension;
Again at the blank edge cladding built-up welding and GH738 constituent class like, added several kinds of superalloy powder B that increase creep rupture strength and fatigue strength alloying element again, in the component of the superalloy powder B that presets at the blank edge except that the component of high temperature alloy plug again the component of interpolation count with mass percent: Ni 2.0%, Nb 0.6%, Si 0.2%, Y
2O
30.01%, Hf 0.01%, continues cladding built-up welding moulding and constitutes turbine disk cylindrical portion blank, through section flaw detection zero defect, send the commentaries on classics precision forging as blank of turbine disc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200910010308 CN101480761B (en) | 2009-02-06 | 2009-02-06 | Method for preparing blank of turbine disc with gradient function of aerial engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200910010308 CN101480761B (en) | 2009-02-06 | 2009-02-06 | Method for preparing blank of turbine disc with gradient function of aerial engine |
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| CN101480761A CN101480761A (en) | 2009-07-15 |
| CN101480761B true CN101480761B (en) | 2012-03-28 |
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| CN 200910010308 Expired - Fee Related CN101480761B (en) | 2009-02-06 | 2009-02-06 | Method for preparing blank of turbine disc with gradient function of aerial engine |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103128498B (en) * | 2011-12-05 | 2015-05-20 | 沈阳黎明航空发动机(集团)有限责任公司 | High-deformation-resistance high-temperature alloy baffle forming process |
| CN104152895B (en) * | 2014-08-15 | 2016-04-13 | 山东大学 | A kind of preparation technology of titanium alloy surface intermetallic compound base ceramic composite coating |
| US11059132B2 (en) | 2015-09-11 | 2021-07-13 | Siemens Energy, Inc. | Structural braze tape |
| CN113416953A (en) * | 2021-06-23 | 2021-09-21 | 沈阳稀有金属研究所 | Alloy powder and application thereof in laser cladding |
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2009
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Effective date of registration: 20161202 Address after: 610202 Sichuan city of Chengdu Province Southwest Airport Economic Development Zone Shuangliu District Patentee after: SICHUAN DACHENG TURBINE EQUIPMENT REMANUFACTURING TECHNOLOGY 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: 20120328 Termination date: 20220206 |