CN107755636A - A kind of quick method for solving the casting deformation of combustion engine blade - Google Patents
A kind of quick method for solving the casting deformation of combustion engine blade Download PDFInfo
- Publication number
- CN107755636A CN107755636A CN201710817840.0A CN201710817840A CN107755636A CN 107755636 A CN107755636 A CN 107755636A CN 201710817840 A CN201710817840 A CN 201710817840A CN 107755636 A CN107755636 A CN 107755636A
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- China
- Prior art keywords
- combustion engine
- engine blade
- formwork
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- gate system
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Classifications
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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
- 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
- B22D27/04—Influencing the temperature of the metal, e.g. by heating or cooling the mould
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of quick method for solving the casting deformation of combustion engine blade, it is characterised in that comprises the following steps：（1）Combustion engine blade running gate system is designed using 3D sculpting software, and is imported in finite element software, simulation calculates combustion engine blade running gate system Temperature Distribution, is accurately positioned combustion engine blade prior to periphery cooling solidification region at first；（2）Wax-pattern module corresponding with combustion engine blade is taken, coating is coated with the surface of the wax-pattern module, and is dewaxed, is calcined successively, after cooling treatment, obtains formwork；（3）In combustion engine blade certain thickness ceramic thermal insulation cotton is wrapped up corresponding to cooling solidification region on formwork at first prior to periphery；（4）The formwork wrapped is calcined, and roasting formwork is taken out and poured into a mould.The present invention is accurately positioned combustion engine deformable blade region, improves the qualification rate of combustion engine Blade roughcast, and easy to operation, is to solve a kind of effective ways that combustion engine blade is deformed by shrinkage stress.
Description
Technical field
The present invention relates to hot investment casting field, specifically a kind of quick method for solving the casting deformation of combustion engine blade.
Background technology
Heavy combustion engine core component turbine blade mainly uses investment pattern precision casting technique monoblock cast at present.Such as certain combustion engine the 4th
Level movable vane piece, total length about 380mm, most thin section position only 0.7mm, is easily deformed after essence casting.To meet blade design drawing size
Requirement, traditional way be according to casting structure and experience, using trial-and-error method wrap up ceramic thermal insulation cotton, repetition test, to
Obtain the casting that size meets design requirement.Though the method can solve casting deformation, compare blindly, without specific aim, and
Test period is grown, and spends cost high.
The content of the invention
The invention aims to solve above-mentioned technical problem, there is provided a kind of quick combustion engine blade that solves casts deformation
Method, casting deformation region can be accurately positioned using the present invention, save research and development and experimental manufacturing cost, increase substantially casting dimension conjunction
Lattice rate, there is significant economic benefit and social benefit.
Realize the technical scheme is that：A kind of quick method for solving the casting deformation of combustion engine blade, it is characterised in that
Comprise the following steps：
（1）Combustion engine blade running gate system is designed using 3D sculpting software, and is imported in finite element software, simulation calculates combustion engine leaf
Piece running gate system Temperature Distribution, combustion engine blade is accurately positioned prior to periphery cooling solidification region at first；
（2）Wax-pattern module corresponding with combustion engine blade is taken, is coated with coating on the surface of the wax-pattern module, and taken off successively
After wax, roasting, cooling treatment, formwork is obtained；
（3）In combustion engine blade certain thickness ceramic thermal insulation is wrapped up corresponding to cooling solidification region on formwork at first prior to periphery
Cotton；
（4）The formwork wrapped is calcined, and roasting formwork is taken out and poured into a mould.
The step（1）In, design combustion engine blade running gate system, export using 3D sculpting software UG or SolidWorks
For IGS formatted files；IGS files are imported into HypeMesh softwares again, surface grids is divided automatically, exports as STL formatted files；Will
Stl file is imported in Mesh 3D files, is divided volume mesh automatically, is exported as mesh formatted files；Mesh files are imported
In ProCast files, arrange parameter, simulation calculate combustion engine blade running gate system Temperature Distribution, be accurately positioned combustion engine blade prior to
Periphery cooling solidification region at first.
The step（3）In, it is wound on outside ceramic thermal insulation cotton and is fixed with nickel filament, or in ceramic thermal insulation cotton interface
Position high-temperature agglomerant or high temperature clay bond.
The beneficial effects of the invention are as follows：
1st, the present invention uses computer numerical simulation, can be accurately positioned combustion engine blade prior to periphery cooling solidification area at first
Domain, this region take the lead in solidification shrinkage, cause casting deformation.By wrapping up certain thickness ceramic thermal insulation cotton in this region, can have
Effect reduces its freezing rate, makes it with neighboring area while solidifies, improvement casting deformation.
2nd, the present invention can be accurately positioned casting deformation region, save research and development and experimental manufacturing cost, increase substantially casting dimension
Qualification rate, there is significant economic benefit and social benefit.
Brief description of the drawings
Fig. 1 is corresponding process structure change schematic diagram of the embodiment of the present invention.
Label in figure：1-cooling solidification region at first, 2-formwork, 3-ceramic thermal insulation cotton.
Embodiment
As shown in figure 1, a kind of quick method for solving the casting deformation of combustion engine blade, comprises the following steps：
（1）Combustion engine blade running gate system is designed using 3D sculpting software UG or SolidWorks, exports as IGS formatted files；
IGS files are imported into HypeMesh softwares again, surface grids is divided automatically, exports as STL formatted files；Stl file is imported
In Mesh 3D files, volume mesh is divided automatically, exports as mesh formatted files；Mesh files are imported in ProCast files,
Arrange parameter, simulation calculate combustion engine blade running gate system Temperature Distribution, be accurately positioned combustion engine blade cool at first prior to periphery it is solidifying
Gu region 1；
（2）Wax-pattern module corresponding with combustion engine blade is taken, is coated with coating on the surface of the wax-pattern module, and taken off successively
After wax, roasting, cooling treatment, formwork 2 is obtained；
（3）In combustion engine blade certain thickness ceramic thermal insulation cotton is wrapped up corresponding to cooling solidification region on formwork at first prior to periphery
3；Be wound on outside ceramic thermal insulation cotton 3 and be fixed with nickel filament, or the interface of ceramic thermal insulation cotton 3 position high-temperature agglomerant or
High temperature clay bonds；
（4）The formwork 2 wrapped is calcined, and roasting formwork 2 is taken out and poured into a mould.
The present invention uses computer numerical simulation, can be accurately positioned combustion engine blade prior to periphery cooling solidification area at first
Domain, this region take the lead in solidification shrinkage, cause casting deformation.By wrapping up certain thickness ceramic thermal insulation cotton in this region, can have
Effect reduces its freezing rate, makes it with neighboring area while solidifies, improvement casting deformation.The present invention can be accurately positioned casting deformation
Region, research and development and experimental manufacturing cost are saved, increases substantially casting dimension qualification rate, there is significant economic benefit and society to imitate
Benefit.
Claims (3)
- A kind of 1. quick method for solving the casting deformation of combustion engine blade, it is characterised in that comprise the following steps：（1）Combustion engine blade running gate system is designed using 3D sculpting software, and is imported in finite element software, simulation calculates combustion engine leaf Piece running gate system Temperature Distribution, combustion engine blade is accurately positioned prior to periphery cooling solidification region at first；（2）Wax-pattern module corresponding with combustion engine blade is taken, is coated with coating on the surface of the wax-pattern module, and taken off successively After wax, roasting, cooling treatment, formwork is obtained；（3）In combustion engine blade certain thickness ceramic thermal insulation is wrapped up corresponding to cooling solidification region on formwork at first prior to periphery Cotton；（4）The formwork wrapped is calcined, and roasting formwork is taken out and poured into a mould.
- 2. quickly solve the method for combustion engine blade casting deformation according to claim 1, it is characterised in that：The step（1） In, combustion engine blade running gate system is designed using 3D sculpting software UG or SolidWorks, exports as IGS formatted files；Again will IGS files import HypeMesh softwares, divide surface grids automatically, export as STL formatted files；Stl file is imported into Mesh 3D In file, volume mesh is divided automatically, exports as mesh formatted files；Mesh files are imported in ProCast files, ginseng is set Number, simulation calculate combustion engine blade running gate system Temperature Distribution, are accurately positioned combustion engine blade prior to periphery cooling solidification region at first.
- 3. quickly solve the method for combustion engine blade casting deformation according to claim 1, it is characterised in that：The step（3） In, be wound on outside ceramic thermal insulation cotton and be fixed with nickel filament, or ceramic thermal insulation cotton interface position high-temperature agglomerant or High temperature clay bonds.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710817840.0A CN107755636A (en) | 2017-09-12 | 2017-09-12 | A kind of quick method for solving the casting deformation of combustion engine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710817840.0A CN107755636A (en) | 2017-09-12 | 2017-09-12 | A kind of quick method for solving the casting deformation of combustion engine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107755636A true CN107755636A (en) | 2018-03-06 |
Family
ID=61265405
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710817840.0A Withdrawn CN107755636A (en) | 2017-09-12 | 2017-09-12 | A kind of quick method for solving the casting deformation of combustion engine blade |
Country Status (1)
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| CN (1) | CN107755636A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109434025A (en) * | 2018-11-29 | 2019-03-08 | 沈阳航发精密铸造有限公司 | A kind of process for eliminating supramarginal plate crackle metallurgical imperfection |
| CN110238349A (en) * | 2019-07-16 | 2019-09-17 | 中国航发北京航空材料研究院 | Reduce the preparation method and its fusible pattern preparation method of titanium investment precision casting surface roughness |
| CN115255274A (en) * | 2022-07-29 | 2022-11-01 | 贵州安吉航空精密铸造有限责任公司 | Investment casting method of stainless steel casting with bracket structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109434025A (en) * | 2018-11-29 | 2019-03-08 | 沈阳航发精密铸造有限公司 | A kind of process for eliminating supramarginal plate crackle metallurgical imperfection |
| CN110238349A (en) * | 2019-07-16 | 2019-09-17 | 中国航发北京航空材料研究院 | Reduce the preparation method and its fusible pattern preparation method of titanium investment precision casting surface roughness |
| CN115255274A (en) * | 2022-07-29 | 2022-11-01 | 贵州安吉航空精密铸造有限责任公司 | Investment casting method of stainless steel casting with bracket structure |
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