CN105312563B - A kind of manufacture method of Ni-based double-alloy blisk - Google Patents
A kind of manufacture method of Ni-based double-alloy blisk Download PDFInfo
- Publication number
- CN105312563B CN105312563B CN201510737582.6A CN201510737582A CN105312563B CN 105312563 B CN105312563 B CN 105312563B CN 201510737582 A CN201510737582 A CN 201510737582A CN 105312563 B CN105312563 B CN 105312563B
- Authority
- CN
- China
- Prior art keywords
- hub
- blade
- boss
- blisk
- powder
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 40
- 239000000956 alloy Substances 0.000 title claims abstract description 26
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 24
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 18
- 239000000463 material Substances 0.000 claims abstract description 16
- 239000000758 substrate Substances 0.000 claims abstract description 7
- 239000000843 powder Substances 0.000 claims description 22
- 238000003825 pressing Methods 0.000 claims description 13
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 8
- 238000010275 isothermal forging Methods 0.000 claims description 8
- 238000003754 machining Methods 0.000 claims description 8
- 238000005242 forging Methods 0.000 claims description 5
- 238000009825 accumulation Methods 0.000 claims description 4
- 229910052786 argon Inorganic materials 0.000 claims description 4
- 238000005253 cladding Methods 0.000 claims description 4
- 238000009689 gas atomisation Methods 0.000 claims description 4
- 238000009792 diffusion process Methods 0.000 abstract description 9
- 238000005266 casting Methods 0.000 abstract description 6
- 238000003466 welding Methods 0.000 abstract description 6
- 230000007547 defect Effects 0.000 abstract description 5
- 238000005516 engineering process Methods 0.000 abstract description 5
- 238000000465 moulding Methods 0.000 abstract description 3
- 238000002844 melting Methods 0.000 abstract description 2
- 230000008018 melting Effects 0.000 abstract description 2
- 238000005204 segregation Methods 0.000 abstract description 2
- 238000007711 solidification Methods 0.000 abstract description 2
- 230000008023 solidification Effects 0.000 abstract description 2
- 230000008030 elimination Effects 0.000 abstract 1
- 238000003379 elimination reaction Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 5
- 230000009977 dual effect Effects 0.000 description 3
- 238000005495 investment casting Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000001513 hot isostatic pressing Methods 0.000 description 1
- 238000009940 knitting Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 238000004663 powder metallurgy Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/02—Compacting only
- B22F3/04—Compacting only by applying fluid pressure, e.g. by cold isostatic pressing [CIP]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/10—Sintering only
- B22F3/105—Sintering only by using electric current other than for infrared radiant energy, laser radiation or plasma ; by ultrasonic bonding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/17—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by forging
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
- B22F2998/10—Processes characterised by the sequence of their steps
Abstract
The invention belongs to nickel-bass alloy material and its manufacturing technology field, specially a kind of manufacture method of Ni-based double-alloy blisk.Manufacturing cost is low, without blade casting mould, eliminates the shortcoming that conventional casting techniques are complicated, process is various, subsequent mechanical allowance is small, expects that the whole manufacturing cycle of part is short from former material；Metallurgical interface is well combined, and laser forming can be realized spreads uneven, insufficient, existing defects shortcomings between rapid melting and the solidification of hub and blade material, elimination conventional diffusion Welding different materials；Drip molding internal soundness is high, and laser fast forming can obtain tiny, uniform, fine and close tissue, eliminate casting technique shrinkage cavity and porosity, be mingled with, component segregation, the shortcomings of organize thick, comprehensive mechanical property is superior.Design boss provides substrate for the laser fast forming of blade, and laser forming interface weak area can be made to avoid the high stress concentration zone of blade and hub junction.
Description
Technical field
The invention belongs to nickel-bass alloy material and its manufacturing technology field, specially a kind of Ni-based double-alloy blisk
Manufacture method.
Background technology
Ni-based double-alloy blisk is the hot forging critical component of aircraft auxiliary power plant, is engine rotor manufacture skill
One of developing direction of art.The structure can not only mitigate turbine weight, exempt high accuracy processing and matching requirements, can also send out
The performance advantage of hub and two kinds of materials of blade is waved, working life and reliability is improved.
The preparation of Ni-based double-alloy blisk is realized using high temperature insostatic pressing (HIP) diffusion connecting process method at present, specifically
It is that powder metallurgy superalloy turbine disc is prepared using high temperature insostatic pressing (HIP) and isothermal forging process first, is cast using precision casting process
Go out blade ring, then by once heat iso-hydrostatic diffusion welding after the turbine disk and blade ring are fitted close, realize hub and blade
Metallurgical binding.The major defect of this process is that one is that cast blade ring needs to prepare mould, and development cost is high, week
Phase is long.Two be that heat iso-hydrostatic diffusion welding technique is unstable, and the diffusion between hub and blade material is uneven, insufficient, exists
Defect, it is impossible to realize good metallurgical binding.
Laser Rapid Prototyping Technique directly can be carried out three-dimensional using computer and set in the case of without any die hard
Meter, produces entity component or prototype, can realize the direct forming of high-performance labyrinth, densified metal component.But light
Spot size is limited, low for large volume simple structure shaping accumulation required time length, efficiency, is unfavorable for playing the excellent of the technology
Gesture.
The content of the invention
The purpose of the present invention is to propose to a kind of combination manufacturing method of Ni-based double-alloy blisk, traditional handicraft is made up
Deficiency, while it meets long-life, the use requirement of high reliability.
The particular content of technical solution of the present invention is：
The step of this method is：
(1) two kinds of nickel-base alloys of hub and blade of Ni-based double-alloy blisk are prepared respectively by argon gas atomization method
Powder, hub powder is used for high temperature insostatic pressing (HIP), and blade powder is used for laser fast forming；
(2) hub powder is prepared into out ingot blank by high temperature insostatic pressing (HIP), hub forging stock is then prepared using isothermal forging；
(3) machining process is used, boss is processed at hub edge, it is other during machining hub in addition to boss
Allowance is not stayed in part, and the outer rim and hub of boss are concentric, and land length and width are suitable with same position blade dimensions,
Boss height is 2~3mm；
(4) laser fast forming technique is used, using hub boss as substrate, blade powder is subjected to successively cladding accumulation,
Obtain the formed body of approximate blade shape；
(5) molded blisk is heat-treated；
(6) final delicate mechanical processing is carried out to blisk by detail drawing, removes blade and the unnecessary material of boss.
The present invention has the advantage that and beneficial effect
The present invention is whole using high temperature insostatic pressing (HIP), isothermal forging technology and the Ni-based dual alloy of Laser Rapid Prototyping Technique combination manufacture
Body leaf dish, compared with prior art with advantages below：(1) cost is low, the cycle is short, without blade casting mould, eliminates tradition
The shortcoming that casting technique is complicated, process is various, subsequent mechanical allowance is small, and the whole manufacturing cycle of part is expected from former material
It is short；(2) high flexibility, easy to operate, laser forming equipment integrated automation level height, whole computer control, manufacture is intelligent, number
Word；(3) metallurgical interface is well combined, and laser forming can realize rapid melting and the solidification of hub and blade material, is eliminated and is passed
Uneven, insufficient, existing defects shortcomings are spread between system diffusion welding craft different materials；(4) drip molding internal soundness is high,
Laser fast forming can obtain tiny, uniform, fine and close tissue, eliminate casting technique shrinkage cavity and porosity, be mingled with, component segregation, group
The shortcomings of knitting thick, comprehensive mechanical property is superior.(5) design boss provides substrate for the laser fast forming of blade, can make to swash
Avoid the high stress concentration zone of blade and hub junction in light formative interface weak area.Therefore, by hot isostatic pressing technique and laser
RP technique is applied in combination, and is a kind of reliable new way for manufacturing Ni-based double-alloy blisk.
Brief description of the drawings
Fig. 1 is a kind of schematic diagram of the Ni-based dual alloy turbine blisk structure of Typical Aircraft engine；
Fig. 2 is the schematic diagram that Ni-based double-alloy blisk hub is prepared using high temperature insostatic pressing (HIP) and isothermal forging process；
Fig. 3 is the blade ring schematic diagram that prior art uses precision casting process to cast；
Fig. 4 is the hub schematic diagram for processing boss at edge after over mechanical processing；Label in figure：1-land length；
2-projection width；3-boss height；
Fig. 5 is the blisk schematic diagram that near-net-shape is obtained using laser fast forming technique.Label in figure：4-disk
Hub, 5-blade.
Embodiment
Technical solution of the present invention is described in further detail below with reference to example：
The step of this method is：
(1) Ni-based double-alloy blisk hub, two kinds of Co-based alloy powders of blade, disk are prepared by argon gas atomization method
Hub powder is used for high temperature insostatic pressing (HIP), and blade powder is used for laser fast forming；
(2) hub powder is prepared into out ingot blank by high temperature insostatic pressing (HIP), hub forging stock is then prepared using isothermal forging；
(3) machining process is used, boss is processed at hub edge, base is provided for post laser Quick-forming blade
Bottom, except boss other parts do not stay allowance during machining hub, the outer rim and hub of boss are concentric, land length and width
Degree, suitable with same position blade dimensions, boss height is 2~3mm, laser forming interface is avoided blade and hub corner
High stress concentration zone；
(4) laser fast forming technique is used, using hub boss as substrate, blade powder is subjected to successively cladding accumulation,
Obtain the formed body of approximate blade shape；
(5) molded blisk is heat-treated；
(6) final delicate mechanical processing is carried out to blisk by detail drawing, removes blade and the unnecessary material of boss.
Embodiment
Fig. 1 is a kind of Ni-based dual alloy turbine blisk structure of Typical Aircraft engine, and hub material closes for FGH96
Gold, blade material is K418B alloys, if using traditional heat iso-hydrostatic diffusion welding process, it is necessary to using hot investment casting work
Skill, which is poured, casts out blade ring shown in Fig. 3, after then the turbine disk of hip moulding shown in Fig. 2 and blade ring are fitted close by
Heat iso-hydrostatic diffusion welding, forms blisk, and this various complexity of process process, manufacturing cycle length, cost are high, work
Skill stability is low, and the diffusion between hub and blade material is uneven, defect easily occurs.
(1) Ni-based double-alloy blisk hub FGH96 alloy powders and blade K418B are prepared by argon gas atomization method
Alloy powder, hub powder is used for high temperature insostatic pressing (HIP), and blade powder is used for laser fast forming, mesh~325 of powder size scope 100
Mesh；
(2) hub powder is prepared into out ingot blank by high temperature insostatic pressing (HIP), hub forging stock, disk is then prepared using isothermal forging
Hub size is 130 × 40mm of Φ；
(3) machining process is used, the boss shown in Fig. 4 is processed at hub edge, is post laser Quick-forming
Blade provides substrate, and except boss other parts do not stay allowance during machining hub, totally 32 boss are evenly distributed on disk
Hub outer rim, the outer rim and hub of boss is concentric, and land length 1 is 40mm, and width 2 is 10mm, with same position blade dimensions phase
When boss height 3 is 2mm, laser forming interface is avoided the high stress concentration zone of blade and hub corner；
(4) laser fast forming technique is used, using the boss of hub 4 as substrate, blade powder is subjected to successively cladding heap
Blade 5 is accumulated into, the formed body of the approximate blade shape shown in Fig. 5 is obtained；
(5) molded blisk is heat-treated；
(6) final delicate mechanical processing is carried out to blisk by detail drawing, removes blade and the unnecessary material of boss,
Obtain blisk shown in Fig. 1.
Compared with prior art, using high temperature insostatic pressing (HIP) of the present invention, isothermal forging and laser fast forming technique groups
Close metallurgical interface between the Ni-based double-alloy blisk of manufacture, two kinds of materials to be well combined, performance touches the mark requirements, process is grasped
Make simple, the manufacturing cycle shortens.
Claims (1)
1. a kind of manufacture method of Ni-based double-alloy blisk, it is characterised in that：The step of this method is：
(1) two kinds of nickel-base alloy powders of hub and blade of Ni-based double-alloy blisk are prepared respectively by argon gas atomization method
End, hub powder is used for high temperature insostatic pressing (HIP), and blade powder is used for laser fast forming；
(2) hub powder is prepared into out ingot blank by high temperature insostatic pressing (HIP), hub forging stock is then prepared using isothermal forging；
(3) machining process is used, boss is processed at hub edge, during machining hub in addition to boss, other parts
Allowance is not stayed, the outer rim and hub of boss are concentric, and land length and width are suitable with same position blade dimensions, boss
Highly it is 2~3mm；
(4) laser fast forming technique is used, using hub boss as substrate, blade powder is subjected to successively cladding accumulation, obtained
The formed body of approximate blade shape；
(5) molded blisk is heat-treated；
(6) final delicate mechanical processing is carried out to blisk by detail drawing, removes blade and the unnecessary material of boss.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510737582.6A CN105312563B (en) | 2015-11-03 | 2015-11-03 | A kind of manufacture method of Ni-based double-alloy blisk |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510737582.6A CN105312563B (en) | 2015-11-03 | 2015-11-03 | A kind of manufacture method of Ni-based double-alloy blisk |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105312563A CN105312563A (en) | 2016-02-10 |
| CN105312563B true CN105312563B (en) | 2017-10-03 |
Family
ID=55241441
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510737582.6A Active CN105312563B (en) | 2015-11-03 | 2015-11-03 | A kind of manufacture method of Ni-based double-alloy blisk |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105312563B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107520442B (en) * | 2016-06-20 | 2019-11-05 | 中国航发商用航空发动机有限责任公司 | Series connection integral blade disk manufacturing process |
| EP3281725A1 (en) * | 2016-08-09 | 2018-02-14 | Siemens Aktiengesellschaft | Method of additive manufacturing and computer readable medium |
| CN107116174A (en) * | 2017-06-21 | 2017-09-01 | 山东南山铝业股份有限公司 | The processing method and system of fan leaf dish |
| CN110788562B (en) * | 2019-08-02 | 2020-12-29 | 中国航发北京航空材料研究院 | Manufacturing method of nickel-based alloy dual-performance blisk |
| CN111187895B (en) * | 2020-02-17 | 2021-08-10 | 南昌航空大学 | Blisk with twinned structure and manufacturing method thereof |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5038014A (en) * | 1989-02-08 | 1991-08-06 | General Electric Company | Fabrication of components by layered deposition |
| US20060067830A1 (en) * | 2004-09-29 | 2006-03-30 | Wen Guo | Method to restore an airfoil leading edge |
| US8691329B2 (en) * | 2007-01-31 | 2014-04-08 | General Electric Company | Laser net shape manufacturing using an adaptive toolpath deposition method |
| US20080182017A1 (en) * | 2007-01-31 | 2008-07-31 | General Electric Company | Laser net shape manufacturing and repair using a medial axis toolpath deposition method |
| CN102052342B (en) * | 2009-10-29 | 2013-02-13 | 北京有色金属研究总院 | Titanium alloy integral bladed disc and manufacturing method thereof |
| CN102615284B (en) * | 2012-04-26 | 2013-11-27 | 西北工业大学 | Manufacturing method for double-structure turbine disk |
| CN104690517B (en) * | 2015-03-25 | 2017-02-22 | 西安交通大学 | Blisk manufacturing method based on 3D (three-dimensional) printing and electric spark finishing |
-
2015
- 2015-11-03 CN CN201510737582.6A patent/CN105312563B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN105312563A (en) | 2016-02-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105312563B (en) | A kind of manufacture method of Ni-based double-alloy blisk | |
| CN104493094B (en) | Rapid precise casting technology based on photocuring 3D printing technique | |
| CN104308153B (en) | A kind of manufacture method of high-entropy alloy turbogenerator hot-end component based on precinct laser fusion | |
| CN104368814B (en) | A kind of method of metal laser direct-forming high-entropy alloy turbogenerator hot-end component | |
| US10144062B2 (en) | Method and device for producing a component of a turbomachine | |
| CN102941343B (en) | Quick manufacturing method of titanium-aluminum alloy composite part | |
| CN108296715A (en) | A method of using forging and increasing material manufacturing combined shaping metal large-scale component | |
| CN106513685B (en) | A kind of nearly molten state hot isostatic pressing net-shape method of powder | |
| US20170284206A1 (en) | High porosity material and method of making thereof | |
| CN103949639A (en) | Method for preparing Nb-Si based superhigh-temperature alloy by SLM (selective laser melting) technology | |
| JP2003129862A (en) | Turbine blade production method | |
| CN101391302A (en) | Entirety quick manufacture method of hot isostatic pressing metal wrapps | |
| CN109365811A (en) | A kind of method of selective laser melting process forming Zinc-alloy | |
| CN102441642B (en) | Method for preventing blades of whole turbine impeller of high temperature alloy from under-casting | |
| CN103415365A (en) | Process for local repair of a damaged thermomechanical part and part thus produced, in particular a turbine part | |
| JP6342844B2 (en) | Turbine wheel manufacturing method | |
| CN103949646A (en) | Preparation method for Nb-Si base ultra-temperature alloy turbine vane | |
| CN109396434A (en) | A method of titanium alloy component is prepared based on selective laser melting process | |
| CN105772726A (en) | Hot isostatic pressure near-net forming method for semi-solid complex difficult-machining compact piece | |
| KR101473900B1 (en) | Metal core using direct metal rapid prototyping and manufacturing method of precision parts by hot isostatic press using the same and turbine blisk using the same | |
| CN105252001A (en) | Laser forming and manufacturing process for titanium alloy blisk blade | |
| CN108941511A (en) | A kind of moulding process based on 3D printing cast aluminium alloy gold cylinder cap | |
| CN104718035A (en) | Method for manufacturing at least one metal turbine engine part | |
| CN110328359A (en) | Narrow interval, distortion, multiple-blade dense distribution leaf grating class part manufacturing process | |
| CN107138727A (en) | A kind of sector with dot matrix cooling structure obturages block preparation method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |