CN110181001A - A kind of precision casting process of superalloy turbine - Google Patents
A kind of precision casting process of superalloy turbine Download PDFInfo
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- CN110181001A CN110181001A CN201910610236.XA CN201910610236A CN110181001A CN 110181001 A CN110181001 A CN 110181001A CN 201910610236 A CN201910610236 A CN 201910610236A CN 110181001 A CN110181001 A CN 110181001A
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- shell
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- precision casting
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C3/00—Selection of compositions for coating the surfaces of moulds, cores, or patterns
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
- B22C7/02—Lost patterns
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/12—Treating moulds or cores, e.g. drying, hardening
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
- B22C9/28—Moulds for peculiarly-shaped castings for wheels, rolls, or rollers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D27/00—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting
- B22D27/15—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting by using vacuum
Abstract
The invention belongs to aviation precision casting technology fields, and in particular to a kind of precision casting process of superalloy turbine.The precision casting process of superalloy turbine of the invention the following steps are included: component die design and manufacture, ceramic core preparation, the preparation of shell slurry, the preparation of part shell, the dewaxing of shell, the preroast of shell and part casting, wherein, the component die is designed using bottom filling to guarantee wax-pattern entirety stamp.Inner cavity of component of the present invention is filled using ceramic core, ceramic core is the Al-base ceramic that surface is coated with cobalt aluminate, cobalt aluminate, which is coated in core surface, can efficiently reduce the shrinkage porosite on inner cavity of component surface, the existing oxidation of conventional casting techniques core cavity and shrinkage porosite problem are successfully solved, while high porosity can guarantee be removed with giant after ceramic core is poured.
Description
Technical field
The invention belongs to aviation precision casting technology fields, and in particular to a kind of hot investment casting work of superalloy turbine
Skill.
Background technique
With the gradually development of Civil Aviation Industry, aero-engine is as part requirement the most key on civil aircraft
It is higher and higher.Nickel base superalloy is the main material of aero-engine, because of its complicated harsh use environment, high temperature alloy zero
Part generally has more complicated inner-cavity structure.The part of prior art production easily generates shrinkage porosite in inner cavity of component.
Summary of the invention
Technical problem to be solved by the present invention lies in view of the above shortcomings of the prior art, provide a kind of high temperature alloy
The precision casting process of turbine.Ceramic core used in preparation process of the present invention is a kind of aluminium oxide, magnesia, cobalt aluminate composite wood
Material can be effectively reduced the shrinkage porosite on inner cavity of component surface, and formwork slurry is using mixing slurries such as silica solution, refractory powder, cobalt aluminates
Material is conducive to the rapid cooling of piece surface, guarantees piece surface flatness.
In order to solve the above technical problems, the technical solution adopted by the present invention is that: a kind of hot investment casting of superalloy turbine
Technique, comprising the following steps:
(1) component die manufactures and designs: making part Wax mold according to part to be processed；
(2) prepared by ceramic core: making ceramic core according to part to be processed；
(3) preparation of shell slurry: surface layer slurry is with (2 ~ 2.5): (10 ~ 10.5): the weight ratio of (0.8 ~ 1) is molten by quick-drying silicon
Glue, zirconium English powder, aluminic acid cobalt powder are uniformly mixed；Backing layer slurry is with 1:(1.4 ~ 1.5) ratio silica solution, mullite powder are mixed it is equal
It is even；
(4) preparation of part shell: ceramic core is put into part Wax mold, is filled with filling wax, is pressed into part wax-pattern, will
Part wax-pattern takes out after immersing step (3) described surface layer slurry and the rotation of backing layer slurry, and part wax-pattern is made to obtain uniform coating；
It is uniformly drenched on wax-pattern, is repeated above operation several times using the molding sand of different-grain diameter, until obtaining part shell；
(5) dewaxing of shell: part shell is put into dewaxing kettle, at 170 ~ 180 DEG C of temperature and the pressure of 0.8 ~ 1.0Mpa
Wax-pattern is sloughed；
(6) preroast of shell: being put into roaster for part shell, roasts at 950 ~ 1000 DEG C, by residual wax and part shell
Moisture remove；
(7) casting of part: part shell is preheated to 1150 ± 15 DEG C, keeps the temperature 4 ~ 8h or more；Alloy is refined, is refined
Afterwards by alloy 1540 ± 15 DEG C at a temperature of vacuum pouring part shell in, obtain the part with running channel, finally cutting polishing,
Obtain the workpiece of required shape.
The viscosity of surface layer slurry described in step (3) is 45 ~ 70s-1, pH value is 8.5 ~ 10；The viscosity of backing layer slurry be 15 ~
25s-1, pH value is 8.5 ~ 10.
The mass fraction of aluminium oxide meets 99%≤w in step (2) described ceramic coreAluminium oxide< 100%, while the hole of ceramic core
Gap rate is 50% or more.
The partial size of step (4) the wax-pattern surface layer sand is 120 mesh, and the 2nd ~ 8 layer is backing layer, and the 2nd layer of partial size is 60 ~ 80
Mesh；3rd layer of partial size is 30 ~ 60 mesh, remaining 5 layers partial size is 16 ~ 30 mesh.
The ceramic core can be removed using giant, solve the problems, such as traditional aluminium base ceramic core difficulty cleaning.
Compared with prior art, the invention has the following advantages:
Due to the inner-cavity structure of superalloy turbine class casting complexity, inner cavity of component of the invention is filled using ceramic core, pottery
Porcelain core is the Al-base ceramic that surface is coated with cobalt aluminate, and cobalt aluminate, which is coated in core surface, can efficiently reduce inner cavity of component table
The shrinkage porosite in face successfully solves the existing oxidation of conventional casting techniques core cavity and shrinkage porosite problem, while high porosity energy
It can be removed with giant after enough guaranteeing ceramic core casting.
Shell slurry of the invention is conducive to the fast of piece surface using mixed slurries such as silica solution, refractory powder, cobalt aluminates
Quickly cooling but, guarantees that piece surface flatness, preparation process of the invention can be applied to the casting of other high temperature alloy parts.
Detailed description of the invention
Fig. 1 is the overlooking structure diagram of turbine components prepared by the embodiment of the present invention 1.
Fig. 2 is the left view structural representation of turbine components prepared by the embodiment of the present invention 1.
Fig. 3 is the A-A view of turbine components prepared by the embodiment of the present invention 1.
Fig. 4 is the schematic view of the front view of 1 component die of the embodiment of the present invention.
Fig. 5 is the left view structural representation of 1 component die of the embodiment of the present invention.
Fig. 6 is the overlooking structure diagram of 1 component die of the embodiment of the present invention.
Fig. 7 is the schematic view of the front view of the water-soluble core mold of the embodiment of the present invention 1.
Fig. 8 is the left view structural representation of the water-soluble core mold of the embodiment of the present invention 1.
Fig. 9 is the overlooking structure diagram of the water-soluble core mold of the embodiment of the present invention 1.
Figure 10 is the schematic view of the front view of the ceramic core mold of the embodiment of the present invention 1.
Figure 11 is the left view structural representation of the ceramic core mold of the embodiment of the present invention 1.
Figure 12 is the overlooking structure diagram of the ceramic core mold of the embodiment of the present invention 1.
Technical solution of the present invention is described in further detail below by specific embodiment and attached drawing.
Specific embodiment
Embodiment 1
A kind of precision casting process of superalloy turbine, comprising the following steps:
(1) component die manufactures and designs: part Wax mold designs to guarantee that wax-pattern integrally fills type, mold materials using bottom filling
For wrought aluminium 6061, mold generally body structure is composed of 40 loose pieces, mold shown in Fig. 1 ~ 3 is prepared；
(2) prepared by ceramic core: due to the labyrinth of inner cavity of component, inner cavity of component is filled using ceramic core, and ceramic core is aluminium
Base ceramics, surface coat cobalt aluminate to reduce piece surface shrinkage porosite, and wherein the mass fraction of aluminium oxide is 99.5%, cobalt aluminate
0.5%, mold shown in Figure 10 ~ 12 is prepared；
(3) preparation of shell slurry: surface layer slurry is mixed rapidly-dried silica sol, zirconium English powder, aluminic acid cobalt powder with the weight ratio of 2:10:1
It closes, and stirs for 24 hours until slurry is uniformly mixed；Silica solution, mullite powder are mixed with the weight ratio of 1:1.5, and stirred by backing layer slurry
It mixes 8 hours；Wherein, the viscosity of surface layer slurry is 46s-1, pH value 9.5；The viscosity of backing layer slurry is 18s-1, pH value 9.5；
(4) preparation of part shell: being put into part Wax mold for ceramic core, is filled with filling wax compression moulding part wax-pattern, will
Part wax-pattern successively immerses in step (3) the backing layer slurry and surface layer slurry, takes out after rotating 5s, obtains uniform coating, makes
It is uniformly drenched on wax-pattern with the molding sand of different-grain diameter, surface layer makes two layers, and backing layer makes six layers, obtains part shell；Surface layer sand
For 120 mesh, transition zone (the 2nd layer) 60 mesh；3rd layer of 30 mesh, remaining 5 layers are entirely 30 mesh sand；
(5) dewaxing of shell: being put into dewaxing kettle for shell, sloughs wax-pattern under conditions of 175 DEG C and 0.85Mpa；
(6) preroast of shell: being put into roaster for shell, in 1000 DEG C of roasting 1h, residual wax is burning-out, while by shell water
Divide burning-off, increases formwork elevated temperature strength；
(7) casting of part: part shell is preheated to 1150 DEG C, 5h is kept the temperature, alloy is refined, alloy exists after refining
Vacuum pouring obtains band running channel part at a temperature of 1540 DEG C, finally cutting polishing, obtains turbine as shown in Fig. 1, and part is whole
Wall thickness is 1.4mm.
Embodiment 2
A kind of precision casting process of superalloy turbine, comprising the following steps:
(1) component die manufactures and designs: part Wax mold designs to guarantee that wax-pattern integrally fills type, mold materials using bottom filling
For wrought aluminium 6061, mold generally body structure is composed of 40 loose pieces；
(2) prepared by ceramic core: due to the labyrinth of inner cavity of component, inner cavity of component is filled using ceramic core, and ceramic core is aluminium
Base ceramics, surface coat cobalt aluminate to reduce piece surface shrinkage porosite, and wherein the mass fraction of aluminium oxide is 99%, cobalt aluminate 1%, system
It is standby to obtain mold；
(3) preparation of shell slurry: surface layer slurry is with the weight ratio of 2.5:10.5:0.8 by rapidly-dried silica sol, zirconium English powder, aluminic acid
Cobalt powder mixing, and stir for 24 hours until slurry is uniformly mixed；Backing layer slurry is mixed silica solution, mullite powder with the weight ratio of 1:1.4
It closes, and stirs 8 hours；Wherein, the viscosity of surface layer slurry is 70s-1, pH value 8.5；The viscosity of backing layer slurry is 25s-1, pH value
It is 8.5；
(4) preparation of part shell: being put into part Wax mold for ceramic core, is filled with filling wax compression moulding part wax-pattern, will
Part wax-pattern successively immerses in step (3) the backing layer slurry and surface layer slurry, takes out after rotating 5s, obtains uniform coating, makes
It is uniformly drenched on wax-pattern with the molding sand of different-grain diameter, surface layer makes two layers, and backing layer makes six layers, obtains part shell；Surface layer sand
For 120 mesh, transition zone (the 2nd layer) 80 mesh；3rd layer of 60 mesh, remaining 5 layers are entirely 16 mesh sand；
(5) dewaxing of shell: being put into dewaxing kettle for shell, sloughs wax-pattern under conditions of 180 DEG C and 1.0Mpa；
(6) preroast of shell: being put into roaster for shell, in 950 DEG C of roasting 1h, residual wax is burning-out, while by shell water
Divide burning-off, increases formwork elevated temperature strength；
(7) casting of part: part shell is preheated to 1165 DEG C, 4h is kept the temperature, alloy is refined, alloy exists after refining
Vacuum pouring obtains band running channel part at a temperature of 1555 DEG C, finally cutting polishing, obtains turbine, and part entirety wall thickness is 1.4mm.
Embodiment 3
A kind of precision casting process of superalloy turbine, comprising the following steps:
(1) component die manufactures and designs: part Wax mold designs to guarantee that wax-pattern integrally fills type, mold materials using bottom filling
For wrought aluminium 6061, mold generally body structure is composed of 40 loose pieces；
(2) prepared by ceramic core: due to the labyrinth of inner cavity of component, inner cavity of component is filled using ceramic core, and ceramic core is aluminium
Base ceramics, surface coat cobalt aluminate to reduce piece surface shrinkage porosite, and wherein the mass fraction of aluminium oxide is 99%, cobalt aluminate 1%, system
It is standby to obtain mold；
(3) preparation of shell slurry: surface layer slurry is with the weight ratio of 2.5:10:1 by rapidly-dried silica sol, zirconium English powder, aluminic acid cobalt powder
Mixing, and stir for 24 hours until slurry is uniformly mixed；Backing layer slurry is mixed silica solution, mullite powder with the weight ratio of 1:1.5, and
Stirring 8 hours；Wherein, the viscosity of surface layer slurry is 60s-1, pH value 10；The viscosity of backing layer slurry is 20s-1, pH value 10；
(4) preparation of part shell: being put into part Wax mold for ceramic core, is filled with filling wax compression moulding part wax-pattern, will
Part wax-pattern successively immerses in step (3) the backing layer slurry and surface layer slurry, takes out after rotating 5s, obtains uniform coating, makes
It is uniformly drenched on wax-pattern with the molding sand of different-grain diameter, surface layer makes two layers, and backing layer makes six layers, obtains part shell；Surface layer sand
For 120 mesh, transition zone (the 2nd layer) 70 mesh；3rd layer of 45 mesh, remaining 5 layers are entirely 25 mesh sand；
(5) dewaxing of shell: being put into dewaxing kettle for shell, sloughs wax-pattern under conditions of 180 DEG C and 0.8Mpa；
(6) preroast of shell: being put into roaster for shell, in 975 DEG C of roasting 1h, residual wax is burning-out, while by shell water
Divide burning-off, increases formwork elevated temperature strength；
(7) casting of part: part shell is preheated to 1135 DEG C, 8h is kept the temperature, alloy is refined, alloy exists after refining
Vacuum pouring obtains band running channel part at a temperature of 1525 DEG C, finally cutting polishing, obtains turbine, and part entirety wall thickness is 1.4mm.
The above description is only a preferred embodiment of the present invention, is not intended to limit the scope of the invention, all at this
Under the inventive concept of invention, using equivalent structure transformation made by present specification, or directly/it is used in other indirectly
Relevant technical field is included in scope of patent protection of the invention.
Claims (5)
1. a kind of precision casting process of superalloy turbine, which comprises the following steps:
(1) component die manufactures and designs: making part Wax mold according to part to be processed；
(2) prepared by ceramic core: making ceramic core according to part to be processed；
(3) preparation of shell slurry: surface layer slurry is with (2 ~ 2.5): (10 ~ 10.5): the weight ratio of (0.8 ~ 1) is molten by quick-drying silicon
Glue, zirconium English powder, aluminic acid cobalt powder are uniformly mixed；Backing layer slurry is with 1:(1.4 ~ 1.5) ratio silica solution, mullite powder are mixed it is equal
It is even；
(4) preparation of part shell: ceramic core is put into part Wax mold, is filled with filling wax, is pressed into part wax-pattern, will
Part wax-pattern takes out after immersing step (3) described surface layer slurry and the rotation of backing layer slurry, and part wax-pattern is made to obtain uniform coating；
It is uniformly drenched on wax-pattern, is repeated above operation several times using the molding sand of different-grain diameter, until obtaining part shell；
(5) dewaxing of shell: part shell is put into dewaxing kettle, at 170 ~ 180 DEG C of temperature and the pressure of 0.8 ~ 1.0Mpa
Wax-pattern is sloughed；
(6) preroast of shell: being put into roaster for part shell, roasts at 950 ~ 1000 DEG C, by residual wax and part shell
Moisture remove；
(7) casting of part: part shell is preheated to 1150 ± 15 DEG C, keeps the temperature 4 ~ 8h or more；Alloy is refined, is refined
Afterwards by alloy 1540 ± 15 DEG C at a temperature of vacuum pouring part shell in, obtain the part with running channel, finally cutting polishing,
Obtain the workpiece of required shape.
2. the precision casting process of superalloy turbine according to claim 1, which is characterized in that described in step (3)
The viscosity of surface layer slurry is 45 ~ 70s-1, pH value is 8.5 ~ 10；The viscosity of backing layer slurry is 15 ~ 25s-1, pH value is 8.5 ~ 10.
3. the precision casting process of superalloy turbine according to claim 1, which is characterized in that step (2) described pottery
The mass fraction of aluminium oxide meets 99%≤w in porcelain coreAluminium oxide< 100%, while the porosity of ceramic core is 50% or more.
4. the precision casting process of superalloy turbine according to claim 1, which is characterized in that step (4) described wax
The partial size of die face layer sand is 120 mesh, and the 2nd ~ 8 layer is backing layer, and the 2nd layer of partial size is 60 ~ 80 mesh；3rd layer of partial size is 30 ~ 60
Mesh, remaining 5 layers partial size are 16 ~ 30 mesh.
5. the precision casting process of superalloy turbine according to claim 3, which is characterized in that the ceramic core can
It is removed using giant, solves the problems, such as traditional aluminium base ceramic core difficulty cleaning.
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| CN201910610236.XA CN110181001A (en) | 2019-07-08 | 2019-07-08 | A kind of precision casting process of superalloy turbine |
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| CN201910610236.XA CN110181001A (en) | 2019-07-08 | 2019-07-08 | A kind of precision casting process of superalloy turbine |
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| CN110722104A (en) * | 2019-11-26 | 2020-01-24 | 温州万虹阀门有限公司 | Precision casting process of small-diameter deep-hole valve joint |
| CN112091173A (en) * | 2020-07-29 | 2020-12-18 | 江阴鑫联金属制品有限公司 | Precision investment casting mold and casting method for spiral pump stator |
| CN112157218A (en) * | 2020-10-09 | 2021-01-01 | 马鞍山方圆动力科技有限公司 | Special narrow groove precision casting method for blade |
| CN112207234A (en) * | 2020-10-14 | 2021-01-12 | 鹰普航空科技有限公司 | Precise casting process of complex high-temperature alloy nozzle ring |
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Cited By (16)
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| CN110722104A (en) * | 2019-11-26 | 2020-01-24 | 温州万虹阀门有限公司 | Precision casting process of small-diameter deep-hole valve joint |
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Address after: 214191 Furong five road, Xishan Economic Development Zone, Wuxi, Jiangsu Province, No. 18 Applicant after: Yingpu Aviation Technology Co.,Ltd. Address before: 214191 Furong five road, Xishan Economic Development Zone, Wuxi, Jiangsu Province, No. 18 Applicant before: IMPRO AVIATION COMPONENTS (WUXI) Co.,Ltd. |
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Application publication date: 20190830 |