CN113042682A - Ceramic core wax blank correction tool and correction method for aviation blade - Google Patents
Ceramic core wax blank correction tool and correction method for aviation blade Download PDFInfo
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- CN113042682A CN113042682A CN202110279864.1A CN202110279864A CN113042682A CN 113042682 A CN113042682 A CN 113042682A CN 202110279864 A CN202110279864 A CN 202110279864A CN 113042682 A CN113042682 A CN 113042682A
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- correcting
- ceramic core
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- correction
- core wax
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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
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/18—Finishing
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- 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
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- Mechanical Engineering (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
The invention discloses a ceramic core wax blank correcting tool for aviation blades and a correcting method, wherein the correcting tool comprises a supporting plate, the lower end of the supporting plate is fixedly connected with an adjusting supporting leg, a correcting mould is arranged on the upper end surface of the supporting plate and comprises a correcting lower mould and a correcting upper mould, a correcting cavity matched with the shape of a ceramic core wax blank of a blade is formed between the correcting lower mould and the correcting upper mould, the correcting lower mould and the correcting upper mould are connected through a locking mechanism, the locking mechanism is arranged on two symmetrical side walls of the correcting mould, handles are fixedly connected with two ends of the supporting plate, the ceramic core wax blank which is just pressed and formed is placed on the correcting lower mould, the correcting upper mould is closed, the correcting upper mould and the correcting lower mould are tightly connected through the locking mechanism, and the correcting upper mould and; the method can accurately control the dimensional precision of the wax blank to reach the theoretical requirement, and greatly improves the dimensional precision and the qualification rate of the ceramic core finished product; and a warm water preheating shape-righting size control method is adopted, so that conditions are created for geometric shape recovery and thermal stress elimination.
Description
Technical Field
The invention relates to the technical field of wax mold correction, in particular to a ceramic core wax blank correction tool and correction method for an aviation blade.
Background
With the continuous improvement of the performance of the aero-engine, turbine blades located at key parts of the aero-engine are mostly of a hollow structure in order to bear higher temperature and more severe use environments; the ceramic core is an indispensable link for forming the complex cavity of the hollow blade, so that the ceramic core is mostly a complex blade structure with a thin wall or a large wall thickness difference. The stress generated by the ceramic core in the processes of forming, demolding and cooling can cause the deformation of the wax blank, and the deformation is more serious for the flange position with large wall thickness difference and thin cross section because the cooling speed is faster. In the production process of the existing ceramic core, the size of a ceramic core blade is generally ensured by the size of a mould, the size of the blade is ensured by increasing the wax blank injection time and the shape-keeping time, and the blade is only controlled by trimming the mould if the blade deforms in the later period. However, the deformation of the ceramic core blade is influenced by a plurality of factors, the randomness is high, the deformation is difficult to determine, the difficulty in adjusting the mold is high, and the mold is easy to scrap; and the size of the ceramic core blade is ensured by increasing the wax blank injection time and the shape maintaining time, the production efficiency is low, and the control of the depression size is unstable. Aiming at the defects of the existing ceramic core blade shape correction and size control technology, the invention aims to provide a ceramic core wax blank correction tool and correction method for an aviation blade, which ensure that the ceramic core blade completely meets the requirements of drawing size and theoretical three-dimensional size at the wax blank stage, and thus an aviation blade cavity formed by the ceramic core blade completely meets the requirement of casting size precision.
Disclosure of Invention
The invention mainly aims to provide a ceramic core wax blank correcting tool and a correcting method for aviation blades, which can effectively solve the problems in the background technology.
In order to achieve the purpose, the invention adopts the technical scheme that: the utility model provides a frock is corrected with ceramic core wax base to aviation blade, includes the layer board, the lower extreme fixed connection of layer board adjusts the landing leg, the mould is corrected in the up end installation of layer board, correct the mould including correcting the lower mould and correcting the mould, correct the lower mould and correct between the mould form with the anastomotic school type chamber of blade ceramic core wax base shape, correct the lower mould and correct to go up and be connected through locking mechanism between the mould, locking mechanism locates the bisymmetry lateral wall of correcting the mould, the both ends fixed connection handle of layer board.
Preferably, the correcting mould is a plurality of and is installed on the supporting plate in parallel at equal intervals.
Preferably, the four corners of the upper end surface of the lower correcting die are provided with positioning die grooves, and the four corners of the lower end surface of the upper correcting die are provided with positioning lugs corresponding to the positioning die grooves.
Preferably, the upper end of the lower correction die is provided with a reference hole groove, and the upper correction die is provided with a reference hole communicated with the reference hole groove and used for three-coordinate size detection of the correction tool.
Preferably, the upper end surface of the lower correcting die and the lower end surface of the upper correcting die are provided with ceramic core wax blank injection nozzle clearance grooves at opposite positions.
Preferably, the adjusting support leg is in threaded connection with the lower end face of the supporting plate.
Preferably, locking mechanism includes hook plate, fixing base and upset piece, the lateral wall fixed connection of mould on hook plate and the correction, the fixing base is with the lateral wall fixed connection who corrects the lower mould, the upset piece passes through the rotatory swing joint of axostylus axostyle with the fixing base, the branch of the both sides wall swing joint symmetry of upset piece, two slip grafting U type pole on the branch, the horizontal pole and the hook plate joint of U type pole, the montant surface of U type pole is equipped with the screw thread strip, the montant of U type pole is located the upper and lower both sides threaded connection lock nut of branch.
A method for correcting ceramic core wax blanks for aviation blades comprises the steps of placing ceramic core wax blanks which are just formed in a pressing mode on a correcting lower die, closing a correcting upper die, tightly connecting the correcting upper die with the correcting lower die through a locking mechanism, keeping for 5-7 minutes, and taking out.
Preferably, the ceramic core with the large wall thickness and the ceramic core which is easy to crack due to stress concentration caused by shape correction are preheated by warm water before the ceramic core wax blank is placed in the correction tool.
Preferably, the warm water preheating method comprises the steps of putting the ceramic core wax blank into water with the water temperature of 40-50 ℃, keeping the temperature for 20-40s and taking out the ceramic core wax blank.
Compared with the prior art, the invention has the following beneficial effects: according to the invention, the correcting cavity is formed by the correcting lower die and the correcting upper die of the correcting mould to correct the ceramic core wax blank of the blade, so that the dimensional accuracy of the wax blank can be accurately controlled to reach the theoretical requirement, meanwhile, the operation is simple, the dimensional control efficiency is high, and the dimensional accuracy and the qualification rate of the ceramic core finished product are greatly improved; the combination of a plurality of correction moulding beds improves the correction efficiency and the size control stability, and the warm water preheating correction size control method is adopted, so that the preheating of the ceramic core wax blank in hot water creates conditions for geometric shape recovery and thermal stress elimination.
Drawings
FIG. 1 is a perspective view of the overall structure of the present invention;
FIG. 2 is a perspective view of the corrective tire of the present invention;
FIG. 3 is a cross-sectional view of the corrective tire of the present invention;
FIG. 4 is a perspective view of the locking mechanism of the present invention;
FIG. 5 is a perspective view of a lower corrective mold of the present invention;
fig. 6 is a perspective view of the correcting upper die of the present invention.
In the figure: 1. a support plate; 2. adjusting the support legs; 3. correcting the mould; 31. correcting the lower die; 32. correcting the upper die; 33. correcting the cavity; 34. positioning a die cavity; 35. positioning the bump; 36. a ceramic core wax blank injection nozzle clearance groove; 37. a reference hole groove; 38. a reference hole; 4. a locking mechanism; 41. a hook plate; 42. a fixed seat; 43. a turnover piece; 44. a strut; 45. a U-shaped rod; 46. locking the nut; 5. a handle.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
Example 1
As shown in fig. 1-6, a frock is corrected with ceramic core wax base to aviation blade, includes layer board 1, the lower extreme fixed connection regulation landing leg 2 of layer board 1, the upper end face installation of layer board 1 corrects mould 3, correct mould 3 including correcting lower mould 31 and correcting last mould 32, correct and form the type correction chamber 33 that coincide with blade ceramic core wax base shape between lower mould 31 and the correcting last mould 32, correct and be connected through locking mechanism 4 between lower mould 31 and the correcting last mould 32, locking mechanism 4 locates the bilateral symmetry lateral wall of correcting mould 3, both ends fixed connection handle 5 of layer board 1.
In this embodiment, correct mould 3 for a plurality of and equidistant parallel mount on layer board 1, specifically can set up to four, can carry out the size correction to a plurality of wax blanks simultaneously.
In this embodiment, the four corners of the upper end surface of the lower correction die 31 are provided with positioning die cavities 34, and the four corners of the lower end surface of the upper correction die 32 are provided with positioning bumps 35 corresponding to the positioning die cavities 34, so that the lower correction die 31 and the upper correction die 32 can be better theoretically attached.
In this embodiment, the upper end of the correction lower die 31 is provided with a reference hole groove 37, and the correction upper die 32 is provided with a reference hole 38 communicated with the reference hole groove 37, so as to perform size detection on the correction tool by using three coordinates.
In this embodiment, a ceramic core wax blank injection nozzle clearance groove 36 is formed at a position opposite to the upper end surface of the correcting lower die 31 and the lower end surface of the correcting upper die 32.
In this embodiment, adjust landing leg 2 and layer board 1's lower terminal surface threaded connection, the convenience is gone up and down to adjusting landing leg 2.
In this embodiment, locking mechanism 4 includes hook plate 41, fixing base 42 and upset 43, the lateral wall fixed connection of mould 32 is gone up with correcting in hook plate 41, fixing base 42 and the lateral wall fixed connection of correcting lower mould 31, upset 43 and fixing base 42 pass through the rotatory swing joint of axostylus axostyle, the branch 44 of the both sides wall swing joint symmetry of upset 43, two slip grafting U type pole 45 on the branch 44, the horizontal pole and the hook plate 41 joint of U type pole 45, the montant surface of U type pole 45 is equipped with the screw thread strip, the montant of U type pole 45 is located the upper and lower both sides threaded connection lock nut 46 of branch 44, adopts adjustable device, through the adjustment locking dynamics of preset lock nut 46 to the deformation is corrected in the adjustment.
Example 2
A method for correcting ceramic core wax blanks for aviation blades comprises the steps of placing ceramic core wax blanks which are just formed in a pressing mode on a correcting lower die 31, closing a correcting upper die 32, tightly connecting the correcting upper die 32 and the correcting lower die 31 through a locking mechanism 4, keeping for 5-7 minutes, and taking out.
In the embodiment, the ceramic core with the larger wall thickness and the ceramic core which is easy to crack due to stress concentration caused by shape correction are preheated by warm water before the ceramic core wax blank is placed in the correction tool, so that conditions are created for geometric shape recovery and thermal stress elimination.
In the embodiment, the warm water preheating method comprises the steps of putting the ceramic core wax blank into water with the water temperature of 40-50 ℃, keeping the temperature for 20-40s and taking out the ceramic core wax blank.
While certain exemplary embodiments of the present invention have been described above by way of illustration only, it will be apparent to those of ordinary skill in the art that the described embodiments may be modified in various different ways without departing from the spirit and scope of the invention. Accordingly, the drawings and description are illustrative in nature and should not be construed as limiting the scope of the invention.
Claims (10)
1. The utility model provides a frock is corrected with ceramic core wax base to aviation blade, includes the layer board, its characterized in that: the lower extreme fixed connection of layer board adjusts the landing leg, the mould is corrected in the up end installation of layer board, correct the mould including correcting the lower mould and correcting the mould, correct and form the mould correction chamber identical with blade ceramic core wax base shape between lower mould and the mould of correcting, correct and be connected through locking mechanism between the mould on lower mould and the correction, locking mechanism locates the two symmetrical lateral walls of correcting the mould, the both ends fixed connection handle of layer board.
2. The ceramic core wax blank correcting tool for the aviation blade as claimed in claim 1, wherein: the correcting mould is a plurality of and is installed on the supporting plate in parallel at equal intervals.
3. The ceramic core wax blank correcting tool for the aviation blade as claimed in claim 1, wherein: the upper end surface four corners of the correction lower die are provided with positioning die grooves, and the lower end surface four corners of the correction upper die are provided with positioning lugs corresponding to the positioning die grooves.
4. The ceramic core wax blank correcting tool for the aviation blade as claimed in claim 1, wherein: the upper end of the correction lower die is provided with a reference hole groove, and the correction upper die is provided with a reference hole communicated with the reference hole groove.
5. The ceramic core wax blank correcting tool for the aviation blade as claimed in claim 1, wherein: and a ceramic core wax blank injection nozzle clearance groove is formed in the opposite position of the upper end surface of the correcting lower die and the lower end surface of the correcting upper die.
6. The ceramic core wax blank correcting tool for the aviation blade as claimed in claim 1, wherein: the adjusting supporting legs are in threaded connection with the lower end face of the supporting plate.
7. The ceramic core wax blank correcting tool for the aviation blade as claimed in claim 1, wherein: locking mechanism includes hook plate, fixing base and upset piece, the lateral wall fixed connection of mould on hook plate and the correction, the fixing base is with the lateral wall fixed connection who corrects the lower mould, the upset piece passes through the rotatory swing joint of axostylus axostyle with the fixing base, the branch of the both sides wall swing joint symmetry of upset piece, two slip grafting U type pole on the branch, the horizontal pole and the hook plate joint of U type pole, the montant surface of U type pole is equipped with the screw thread strip, the montant of U type pole is located the upper and lower both sides threaded connection lock nut of branch.
8. The method for straightening the ceramic core wax blank for the aviation blade as claimed in any one of claims 1 to 7, wherein the method comprises the following steps: the method comprises the steps of placing a ceramic core wax blank which is just formed by pressing on a correction lower die, closing a correction upper die, tightly connecting the correction upper die with the correction lower die by a locking mechanism, keeping for 5-7 minutes, and taking out.
9. The method for straightening the ceramic core wax blank for the aviation blade according to claim 8, wherein the method comprises the following steps: the ceramic core with the large wall thickness and the ceramic core which is easy to crack due to stress concentration caused by shape correction are preheated by warm water before the ceramic core wax blank is placed in the correction tool.
10. The method for straightening the ceramic core wax blank for the aviation blade according to claim 8, wherein the method comprises the following steps: the warm water preheating method comprises the steps of putting the ceramic core wax blank into water with the water temperature of 40-50 ℃, keeping the temperature for 20-40s and taking out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110279864.1A CN113042682A (en) | 2021-03-16 | 2021-03-16 | Ceramic core wax blank correction tool and correction method for aviation blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110279864.1A CN113042682A (en) | 2021-03-16 | 2021-03-16 | Ceramic core wax blank correction tool and correction method for aviation blade |
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| CN113042682A true CN113042682A (en) | 2021-06-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110279864.1A Pending CN113042682A (en) | 2021-03-16 | 2021-03-16 | Ceramic core wax blank correction tool and correction method for aviation blade |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113857430A (en) * | 2021-08-23 | 2021-12-31 | 中国科学院金属研究所 | Blade deformation control method and application |
| CN115041630A (en) * | 2022-06-29 | 2022-09-13 | 中国航发动力股份有限公司 | Method for correcting wax mold of turbine blade with adjustable sectioning surface |
| CN115385674A (en) * | 2022-09-22 | 2022-11-25 | 中国航发北京航空材料研究院 | Preparation method of high-precision ceramic core |
| CN115945541A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | Orthopedic mould of heat-insulating tile foundry goods |
| CN117259664A (en) * | 2023-11-23 | 2023-12-22 | 江苏永瀚特种合金技术股份有限公司 | Turbine rotor blade precision casting wax matrix orthopedic device |
-
2021
- 2021-03-16 CN CN202110279864.1A patent/CN113042682A/en active Pending
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113857430A (en) * | 2021-08-23 | 2021-12-31 | 中国科学院金属研究所 | Blade deformation control method and application |
| CN113857430B (en) * | 2021-08-23 | 2023-10-13 | 中国科学院金属研究所 | Blade deformation control method and application |
| CN115041630A (en) * | 2022-06-29 | 2022-09-13 | 中国航发动力股份有限公司 | Method for correcting wax mold of turbine blade with adjustable sectioning surface |
| CN115041630B (en) * | 2022-06-29 | 2023-10-20 | 中国航发动力股份有限公司 | Wax mould correction method for turbine blade with adjustable sub-section |
| CN115385674A (en) * | 2022-09-22 | 2022-11-25 | 中国航发北京航空材料研究院 | Preparation method of high-precision ceramic core |
| CN115945541A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | Orthopedic mould of heat-insulating tile foundry goods |
| CN117259664A (en) * | 2023-11-23 | 2023-12-22 | 江苏永瀚特种合金技术股份有限公司 | Turbine rotor blade precision casting wax matrix orthopedic device |
| CN117259664B (en) * | 2023-11-23 | 2024-04-23 | 江苏永瀚特种合金技术股份有限公司 | Turbine rotor blade precision casting wax matrix orthopedic device |
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