CN105772633B - A kind of turbo blade hot investment casting directional freeze method - Google Patents
A kind of turbo blade hot investment casting directional freeze method Download PDFInfo
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- CN105772633B CN105772633B CN201511000487.4A CN201511000487A CN105772633B CN 105772633 B CN105772633 B CN 105772633B CN 201511000487 A CN201511000487 A CN 201511000487A CN 105772633 B CN105772633 B CN 105772633B
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- turbo blade
- wax
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- 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
- B22C9/08—Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
- B22C9/082—Sprues, pouring cups
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
The invention belongs to model casting directional solidification field, refers in particular to a kind of turbo blade directional solidification and fills type device and preparation method.The structure includes spherical die head wax-pattern, turbo blade wax-pattern.The dispersed assembling on spherical die head of turbo blade wax-pattern, after the completion of making shell processed, still keeps being kept completely separate outside each turbo blade cavity.During shell processed, by controlling formwork thickness, make inside each turbo blade cavity to form temperature gradient radially after pouring metal melt fills type, metallic crystal is radially directed growth, form column crystal.
Description
Technical field
The invention belongs to model casting directional solidification field, refers in particular to a kind of turbo blade hot investment casting directional freeze method.
Background technology
Turbocharger is widely used in internal combustion engine, wherein turbo blade rotation under the pushing directly on of high temperature and high speed tail gas
And drive coaxial compressor to work, higher radial direction thermal stress is born, is typical heat-resistant part.
Prepared by turbo blade generally use high temperature alloy precision casting method, form equiax crystal；The transverse grain boundaries drop of equiax crystal
The low radial mechanical performance of turbocharger turbine blade, especially high-temerature creep and thermal fatigue property；Therefore, reduction is passed through
Transverse grain boundaries are even eliminated, the radial mechanical performance of turbocharger turbine blade can be improved, so that its service life is improved,
Reduce cost.
Hot investment casting directional solidification is that ad hoc approach is used in casting solidification process, is established inside formwork cavity specific
The temperature gradient in direction, so that metallic crystal is grown along the direction opposite with hot-fluid, finally makes casting obtain specific orientation
Columnar grain, eliminate transverse grain boundaries, so as to improve mechanical property of the casting in column crystal differently- oriented directivity；The present invention passes through essence
The principle of close casting directional solidification, eliminates the transverse grain boundaries of turbo blade radially, so as to improve its radial direction high-temerature creep and heat
Fatigue behaviour.
The content of the invention：
Turbo blade is produced using precision casting process, to eliminate the transverse grain boundaries formed in process of setting, the present invention
A kind of turbo blade hot investment casting directional freeze method is provided, by being internally formed edge in each independent turbo blade cavity
The temperature gradient of radial direction, makes metallic crystal from turbo blade leaf margin radially to central shaft oriented growth, so as to eliminate transverse direction
Crystal boundary, substantially increases the mechanical property of turbo blade diametrically.
A kind of turbo blade hot investment casting directional freeze method, it is characterised in that prepare with the following method：
(1) apply hot investment casting wax-pattern assemble method, by each turbo blade wax-pattern uniformly, be dispersedly assembled in spherical mold
On the sphere of head wax-pattern, the distance between each turbo blade wax-pattern is sufficiently large, to ensure each turbo blade after shell processed
Still keep being kept completely separate outside cavity.
It is described by each turbo blade wax-pattern uniformly, be dispersedly assembled on the sphere of spherical die head wax-pattern and refer to：By number
A turbo blade wax-pattern is assembled on the sphere of spherical die head by the substantially symmetrical about its central axis of cylindrical running channel, according to turbo blade size
Determine assembling quantity.
Between the turbo blade wax-pattern and spherical die head wax-pattern, it is connected using sprue, the both ends of sprue are welded respectively
It is connected on the sphere of spherical die head wax-pattern and the central shaft of turbo blade wax-pattern.
The spherical die head wax-pattern appearance is spherical in shape, and top is equipped with cylindric running channel；Spherical die head can improve die head and exist
The quantity of unit volume over-assemble turbo blade wax-pattern, improves recovery rate (i.e. rate of metal)；Meanwhile spherical mold capitiform into
Spherical cavity small volume, can when pouring metal melt fills type, for each turbo blade cavity provide similar in mold filling pressure；
In addition, production turbo blade generally uses vacuum melting, spherical die head can improve space availability ratio, reduce smelting equipment vacuum
The volume of room, reduces cost.
(2) the formwork preparation method, refers to the control by formwork thickness during shell processed, closes each turbo blade
Blade and the heat dissipation channel at central shaft position, while quick heat radiating passage is established at turbo blade leaf margin position, make heat only
Blade can be directed radially through from central shaft to flow to leaf margin, and is radiated outside by leaf margin, so as to force metallic crystal along heat
Reverse direction growth is flowed, forms columnar grain, eliminates transverse grain boundaries.
The control of formwork thickness during the shell processed, refers to be coated with conventional slurry, drenches in sand program, addition includes guarantor
The special procedure including floating sand, intermediate layer grouting thickening is stayed, increases the formwork thickness of turbo blade blade and root surface, most
Central shaft and the formwork at blade position is set to respectively reach 9mm and 6.5mm eventually；By eliminating floating sand, the method for striking off backing layer formwork,
Turbo blade leaf margin position formwork thickness is reduced, leaf margin position formwork thickness is reduced to 2mm, expands blade and blade edge position
With blade blade and the thickness difference of the formwork of root surface；Die casing material generally selects the refractory materials such as corundum, mullite, high
The lower thickness of temperature is maximum effect factor of formwork heat-sinking capability.
The shell process processed, refers to that conventional fine casts formwork preparation process：
1. slurry is coated with：Module is immersed in size barrel, slurry is soaked with module；
2. drench sand：The module that painting is hung up properly is drenched into sand in sand sprinkling machine；
3. repeat 1., 2., until the formwork of module reaches respective thickness.
(3) after formwork reaches respective thickness, dewaxing, roasting are implemented, wherein, dewaxing, roasting are all conventional hot investment casting
Technique.
Compared with prior art, the present invention it is advantageous that：
1st, the type device that fills uses spherical die head, its recovery rate (rate of metal) is higher than traditional die head, and space is tied
Structure is compacter, beneficial to the vacuum-chamber dimensions for reducing vacuum melting furnace, reduces the pumpdown time, improves productivity, reduce into
This.
2nd, for the type device that fills when pouring metal melt fills type, liquid high temperature alloy enters spherical die-type from cylindricality running channel
Chamber, spherical die-type chamber are rapidly filled with, and subsequent each turbo blade cavity, which almost starts simultaneously at, fills type, and mold filling pressure differs
It is smaller, so the turbo blade stay in grade prepared, uniformity are higher.
3rd, stable temperature gradient radially is formed in each turbo blade cavity, makes metallic crystal from turbo blade
Leaf margin is grown along blade to central shaft, is formed column crystal, is eliminated transverse grain boundaries, substantially increase turbocharger turbine blade
High-temerature creep and thermal fatigue property.
Brief description of the drawings：
Fig. 1 fills type device wax-pattern assembling schematic diagram for turbo blade directional solidification of the present invention, wherein, 1, cylinder pours
Road wax-pattern, 2, sprue wax-pattern, 3, turbo blade wax-pattern, 4, spherical die head wax-pattern.
Fig. 2 fills type device formwork cavity schematic diagram for turbo blade directional solidification of the present invention, wherein, 5, cylinder pours
Road, 6, sprue, 7, turbo blade, 8, formwork, 9, spherical die head；As seen from the figure, divide mutually outside each 7 cavity of turbo blade
From that is, after type is filled in cast, its temperature field is independent mutually；During cast, the cavity of spherical die head 9 is due to small volume, prior to each
A 7 cavity of turbo blade fills type, then fills type to each 7 cavity of turbo blade by sprue 6 from spherical 9 cavity of die head, and
Mold filling pressure is close.
Fig. 3 a are profile (vertical section) of the turbo blade cavity parallel to central shaft, and Fig. 3 b are that turbo blade cavity is vertical
In the profile (cross section) of central shaft, wherein, 10, turbo blade leaf margin, 11, blade, 12, central shaft；By Fig. 3 a and Fig. 3 b
As it can be seen that by the optimization of formwork preparation method of the present invention, the formwork thickness value at 10 position of turbo blade leaf margin is approximately equal to leaf
Body 11 and the 30% of the thickness value at the grade of central shaft 12 position.
Fig. 4 fills type device using turbo blade hot investment casting directional solidification of the present invention and preparation method is obtained
The macrograph of turbo blade, can observe turbo blade diametrically be organized as typical column crystal.
Embodiment
Type device is filled using turbo blade hot investment casting directional solidification of the present invention and implements wax-pattern assembling, in spherical die head
8 pieces of turbo blade wax-patterns 3 of the sphere over-assemble of wax-pattern 4, each turbo blade wax-pattern 3 press cylindrical 1 central shaft of running channel wax-pattern
Symmetrically, it is and in larger distance between each turbo blade wax-pattern 3, then implement slurry and be coated with, drench sand and carry out shell processed, every two layers it
Between, retain the floating sand at 12 position of blade 11 and jackshaft, and implement thickening processing of being in the milk for several times in intermediate layer, finally make blade 11
Part thickness reaches 6.5mm, and 12 part thickness of central shaft reaches 9mm；Meanwhile in 10 position of leaf margin, 3 layers of a reservation, thick 2mm
Formwork, backing layer formwork afterwards all strikes off before the drying.Formwork implements cast after dewaxing, roasting, and type is filled in cast
Afterwards, the heat of liquid metal can only be delivered in furnace body by the formwork at 10 position of turbo blade leaf margin in 7 cavity of turbo blade,
The liquid metal at 10 position of leaf margin obtains degree of supercooling first, i.e., metallic crystal is first in 10 position forming core of turbo blade leaf margin, together
When, 7 cavity of turbo blade is interior to form stable temperature gradient on the direction of hot-fluid, its direction is radially led to by central shaft 12
Blade 11 is crossed, is directed toward leaf margin 10, so that induce the crystal grain of 10 position forming core of leaf margin to be grown along the reverse direction of temperature gradient, i.e., it is solid
Liquid interface is promoted with supercooling region to the movement of high-temperature area along blade 11 to central shaft 12, forms column crystal；Should
Illustrate, the formwork thickness at 10 position of leaf margin is thinner, more uniform, and the primary grain that its whole edge obtains is just more uniform, thin
Small, so that finally formed column crystal is just more low small, fine and close, the mechanical behavior under high temperature of turbo blade also accordingly improves；Metal is cold
But after, through shaking shell, cutting, removes turbo blade.
Turbo blade is prepared using the present invention, recovery rate (rate of metal) is 80%, and traditional hot investment casting recovery rate
About 50%, and the turbo blade quality homogeneity higher prepared using the present invention.
After corrosion, its grain shape is observed, diametrically observes typical columanar structure, as shown in Figure 4.
Through on probation, the more traditional equiax crystal turbo blade of turbo blade service life prepared using the present invention improves
30%, and operating temperature improves about 15 DEG C.
Finally illustrating, the present invention can also have other embodiment, for example substitute spherical die head 9 with column die head,
The conversion of 3 assembling position of turbo blade wax-pattern, quantity increase and decrease etc..All technical sides formed using equivalent substitution or equivalent transformation
Case, within the scope of the present invention.
Claims (5)
1. a kind of turbo blade hot investment casting directional freeze method, it is characterised in that prepare with the following method：
(1) apply hot investment casting wax-pattern assemble method, by each turbo blade wax-pattern uniformly, be dispersedly assembled in spherical die head wax
On the sphere of mould, the distance between each turbo blade wax-pattern is sufficiently large, to ensure each turbo blade cavity after shell processed
Outside still keeps being kept completely separate；
(2) formwork is prepared, by the control of formwork thickness during shell processed, closes each turbo blade blade and central axle portion
The heat dissipation channel of position, while quick heat radiating passage is established at turbo blade leaf margin position, make heat can only be by central shaft radially
Flowed to leaf margin by blade, and be radiated outside by leaf margin, so as to force metallic crystal to be grown along hot-fluid reverse direction, formed
Columnar grain, eliminates transverse grain boundaries；
(3) after formwork reaches respective thickness, dewaxing, roasting are implemented；
The control of formwork thickness during the shell processed, refers to be coated with conventional slurry, drenches in sand program, and addition, which includes retaining, floats
Special procedure including sand, intermediate layer grouting thickening, increases the formwork thickness of turbo blade blade and root surface, finally makes
Central shaft and the formwork at blade position respectively reach 9mm and 6.5mm；By eliminating floating sand, the method for striking off backing layer formwork, reduces
Turbo blade leaf margin position formwork thickness, finally makes leaf margin position formwork thickness be reduced to 2mm, expands blade and blade edge position and leaf
The thickness difference of the formwork of piece blade and root surface；Die casing material selects corundum, and mullite refractory, thickness is under high temperature
Maximum effect factor of formwork heat-sinking capability.
2. a kind of turbo blade hot investment casting directional freeze method as claimed in claim 1, it is characterised in that described will be each
A turbo blade wax-pattern uniformly, be dispersedly assembled on the sphere of spherical die head wax-pattern and refer to：By several turbo blade wax-patterns by circle
The substantially symmetrical about its central axis of cylindricality running channel is assembled on the sphere of spherical die head, and assembling quantity is determined according to turbo blade size.
A kind of 3. turbo blade hot investment casting directional freeze method as claimed in claim 1, it is characterised in that：The turbine leaf
Between piece wax-pattern and spherical die head wax-pattern, it is connected using sprue, the both ends of sprue are respectively welded at spherical die head wax-pattern
On the central shaft of sphere and turbo blade wax-pattern.
A kind of 4. turbo blade hot investment casting directional freeze method as claimed in claim 1, it is characterised in that：The spherical mold
Head wax-pattern appearance is spherical in shape, and top is equipped with cylindric running channel；Spherical die head can improve die head in unit volume over-assemble turbine
The quantity of blade wax mould, improves recovery rate (i.e. rate of metal)；Meanwhile spherical mold capitiform into spherical cavity small volume,
Can when pouring metal melt fills type, for each turbo blade cavity provide similar in mold filling pressure；In addition, production turbo blade
General to use vacuum melting, spherical die head can improve space availability ratio, reduce the volume of smelting equipment vacuum chamber, reduce into
This.
A kind of 5. turbo blade hot investment casting directional freeze method as claimed in claim 1, it is characterised in that：The shell mistake processed
Journey, refers to that conventional fine casts formwork preparation process：
1. slurry is coated with：Module is immersed in size barrel, slurry is soaked with module；
2. drench sand：The module that painting is hung up properly is drenched into sand in sand sprinkling machine；
3. repeat 1., 2., until the formwork of module reaches respective thickness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511000487.4A CN105772633B (en) | 2015-12-28 | 2015-12-28 | A kind of turbo blade hot investment casting directional freeze method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511000487.4A CN105772633B (en) | 2015-12-28 | 2015-12-28 | A kind of turbo blade hot investment casting directional freeze method |
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| Publication Number | Publication Date |
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| CN105772633A CN105772633A (en) | 2016-07-20 |
| CN105772633B true CN105772633B (en) | 2018-05-11 |
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| CN109807284A (en) * | 2019-03-05 | 2019-05-28 | 南通海泰科特精密材料有限公司 | A kind of disjunctor crucible formwork manufacture craft and disjunctor crucible formwork for casting |
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| KR101350431B1 (en) * | 2013-07-30 | 2014-01-15 | 한국차폐기술주식회사 | A precision casting mold for comprehensive turbine housing by using a shell mold |
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| CN104384449A (en) * | 2014-10-29 | 2015-03-04 | 西安航空动力股份有限公司 | Method of controlling grain size of precisely cast turbine blade |
| CN104439076A (en) * | 2014-12-08 | 2015-03-25 | 中国南方航空工业(集团)有限公司 | Method for controlling grain size of casting |
| CN104999032A (en) * | 2015-06-15 | 2015-10-28 | 上海交通大学 | Casting and method for evaluating hot crack tendency of high temperature alloy investment casting process |
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2015
- 2015-12-28 CN CN201511000487.4A patent/CN105772633B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101537484A (en) * | 2009-03-17 | 2009-09-23 | 江苏大学 | Method for improving temperature distribution in process of single crystal casting solidification |
| CN101629272A (en) * | 2009-08-12 | 2010-01-20 | 江苏大学 | Method for preparing continuous-fiber partially-reinforced aluminum alloy parts |
| CN103252448A (en) * | 2013-04-19 | 2013-08-21 | 江苏大学 | Preparation method of thin-wall high-strength mold shell for single crystal blade manufacturing |
| KR101350431B1 (en) * | 2013-07-30 | 2014-01-15 | 한국차폐기술주식회사 | A precision casting mold for comprehensive turbine housing by using a shell mold |
| CN104259442A (en) * | 2014-09-29 | 2015-01-07 | 江苏大学 | Method for preventing single crystal blade from generating miscellaneous crystal defect |
| CN104308082A (en) * | 2014-10-29 | 2015-01-28 | 西安航空动力股份有限公司 | Pouring method of hollow turbine guide vane |
| CN104384449A (en) * | 2014-10-29 | 2015-03-04 | 西安航空动力股份有限公司 | Method of controlling grain size of precisely cast turbine blade |
| CN104439076A (en) * | 2014-12-08 | 2015-03-25 | 中国南方航空工业(集团)有限公司 | Method for controlling grain size of casting |
| CN104999032A (en) * | 2015-06-15 | 2015-10-28 | 上海交通大学 | Casting and method for evaluating hot crack tendency of high temperature alloy investment casting process |
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| CN105772633A (en) | 2016-07-20 |
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