CN111085661A - Investment mold and method for manufacturing blade with complex cavity - Google Patents
Investment mold and method for manufacturing blade with complex cavity Download PDFInfo
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- CN111085661A CN111085661A CN202010031737.5A CN202010031737A CN111085661A CN 111085661 A CN111085661 A CN 111085661A CN 202010031737 A CN202010031737 A CN 202010031737A CN 111085661 A CN111085661 A CN 111085661A
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- ceramic core
- module
- manufacturing
- fulcrums
- blade
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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
- 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
- B22C9/10—Cores; Manufacture or installation of cores
Abstract
The invention discloses a fired mold and a method for manufacturing a blade with a complex cavity, which belong to the technical field of aviation part manufacturing. The method combines rapid forming and investment casting, utilizes a rapid forming technology to prepare an external module, utilizes a ceramic core as a middle insert to prepare an investment, and then utilizes an investment casting method to cast parts, thereby solving the problem that the complex pore cavity blade cannot be manufactured by rapid forming, saving the cycle and cost of mold design and manufacture, and being very suitable for new product development and small-batch production.
Description
Technical Field
The invention relates to the technical field of aviation part manufacturing, in particular to an investment mold and a method for manufacturing a blade with a complex cavity by combining rapid prototyping and investment casting.
Background
The rapid prototyping technology is a high-tech technology which is developed in the 90 s of the 20 th century and quickly changes the design concept into a real object, and because the rapid prototyping technology does not need an investment pattern and technological equipment in the product development process, the trial production period of a sample piece and a new product is greatly shortened, and the rapid prototyping technology is started to be popularized and used by the production and manufacturing industry. Investment casting is widely used for manufacturing complex small and medium castings such as aviation engine blades, structural members, turbochargers and the like. The main processes from product design to product realization comprise the working procedures of mould design and manufacture, wax mould pressing, module combination, shell manufacturing, dewaxing and sintering, pouring, heat treatment, inspection and the like. The problems of high cost, long period, complex and fussy die repairing and the like of die design and manufacturing cannot meet the requirements of the product development stage or the production of small-batch castings. At present, the production and application of manufacturing a casting by adopting a mode of manufacturing an investment pattern without manufacturing a mould and by adopting a rapid forming technology are more, and the casting has better quality results, but the prior art can not realize the manufacturing of the investment pattern embedded with other materials because the rapid forming can only print the investment pattern made of the same material.
Disclosure of Invention
In order to overcome the defects of the existing investment casting, the invention aims to solve the technical problems that: the investment mold for manufacturing the blade with the complex cavity and the manufacturing method thereof are provided, wherein the investment mold combines a rapid prototyping technology with investment casting to improve efficiency and reduce cost.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the manufacturing method comprises the steps of manufacturing an investment pattern with a complex cavity blade, wherein the investment pattern comprises a model and a ceramic core positioned in the model, the model is divided into two-segment or multi-segment modules along a parting surface, a plurality of ceramic core fulcrums and positioning pin holes are arranged in the model, the ceramic core takes the ceramic core fulcrums as positioning points and is fixed in the model through multi-point adhesion of softened paraffin, and the plurality of modules of the model are also fixed through multi-point adhesion of the softened paraffin.
Further, the ceramic core fulcrums are distributed in three directions of the module, wherein the fulcrums in the direction X are located on the cutting surfaces at two ends of the module, the module at each end is provided with 2 fulcrums, the fulcrums in the direction Y are located on the surface of an inner cavity of the module, 2 fulcrums are arranged on the air inlet side of the module, 1 fulcrum is arranged in the middle of the air outlet side, and the fulcrum in the direction Z is located at the position of the cross section or the round hole of the ceramic core and is provided with 1 fulcrum.
Furthermore, reinforcing rib plates are arranged on the inner surface of the model, the reinforcing rib plates are of a diamond structure, and the thickness of each reinforcing rib plate is not more than the area of the position of the ceramic core.
A method of manufacturing a blade with a complex cavity, comprising the steps of:
a. manufacturing a module: dividing the model into two-segment or multi-segment modules along a parting surface, printing and manufacturing the modules by using a rapid prototyping technology, and then arranging a ceramic core fulcrum and a positioning pin hole in the modules;
b. manufacturing a ceramic core: manufacturing a ceramic core according to the shape of a cavity in the middle of the part;
c. assembling the module with the ceramic core: mounting the ceramic core on one of the lamella modules, taking the ceramic core fulcrum as a positioning point, then mounting the other modules, and bonding and fixing;
d. and (3) trimming a fired mold: brushing, repairing and polishing the joint surface gap of the mounted assembly to enable the surface to be smooth and flat, and completing investment pattern manufacturing;
e. casting parts: and (4) sequentially completing the production processes of combining a module, manufacturing a shell, dewaxing and sintering, casting, carrying out heat treatment and inspecting according to the general flow of investment casting to obtain the required part.
Furthermore, the module is a sheet body consistent with the appearance structure of the part, the size of the sheet body is controlled according to the compensation comprehensive shrinkage rate of 0.5-2%, and the thickness of the sheet body is 0.5-2 mm.
Furthermore, when the module is manufactured, a clamping hole is preset at the position where a ceramic core fulcrum needs to be placed, and the ceramic core fulcrum is clamped in the clamping hole to be fixed.
Further, the number of the ceramic core supporting points is at least three, and the plurality of the ceramic core supporting points ensure that the degree of freedom of the ceramic core in a three-dimensional space is zero when the ceramic core is installed on the module.
Further, the ceramic core fulcrums are distributed in three directions of the module, wherein the fulcrums in the direction X are located on two cutting surfaces at two ends of the module, the module at each end is provided with 2 fulcrums, the fulcrums in the direction Y are located on the surface of an inner cavity of the module, the air inlet side is provided with 2 fulcrums, the middle of the air outlet side is provided with 1 fulcrum, and the fulcrum in the direction Z is located at the position of the ceramic core cross section or the round hole and is provided with 1 fulcrum.
Further, when carrying out the equipment of module and ceramic core, arrange the ceramic core in on the module, respectively with 2 fulcrums of the last air inlet side of module, 1 fulcrum of direction of height, and 4 fulcrums of end cutting face lean on tightly, it is fixed to adopt softened paraffin to carry out the multiple spot adhesion to module and ceramic core edge, then close module and the module of fixed ceramic core, pass the reservation locating pin hole of module and module with the pin of at least 1 ~ 3mm of diameter, align the module well, it is fixed to carry out the multiple spot adhesion to the module edge after finally merging.
Further, after the assembly of the module and the ceramic core is completed, the pin in the locating pin hole is taken down, then the edge of the parting surface is bonded at multiple points by adopting softened paraffin, and the parting gap and the gap of the end head of the ceramic core are brushed and supplemented by adopting paraffin in the stage of investment dressing.
The invention has the beneficial effects that: the method is characterized in that a model is separated from a ceramic core, a method combining rapid forming and investment casting is adopted in a matching mode, an external module is prepared by utilizing a rapid forming technology, the ceramic core is used as a middle insert to prepare an investment, and then a part casting method is adopted to cast parts, so that the problem that the complex cavity blade cannot be manufactured by rapid forming is solved, the cycle and the cost of mold design and manufacturing are saved, and the method is very suitable for new product development and small-batch production.
Drawings
Fig. 1 is a schematic block diagram.
Fig. 2 is a schematic view of a module and a pottery core mounting preliminary structure.
Fig. 3 is a schematic view of the installation structure of the module and the ceramic core.
Fig. 4 is a side view of a module and ceramic core mounting structure.
Fig. 5 is a sectional view of a module and ceramic core mounting structure.
Marked in the figure as 1-model, 11-first module, 12-second module, 2-ceramic core, 3-ceramic core fulcrum, 4-positioning pin hole and 5-reinforcing rib plate.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1-5, the fired mold with the complex cavity blade is manufactured and comprises a mold 1 and a ceramic core 2 located in the mold 1, the mold 1 is divided into two or more sections of modules along a parting surface, a plurality of ceramic core fulcrums 3 and positioning pin holes 4 are arranged in the mold 1, the ceramic core 2 takes the ceramic core fulcrums 3 as positioning points and is fixed in the mold 1 through multi-point adhesion of softened paraffin, and the modules of the mold 1 are also fixed through multi-point adhesion of the softened paraffin. In the initial design stage and the new product development stage, a mold is generally required to be made first. The traditional mold making and mold opening process is complex, high in cost and long in time consumption. Particularly, for parts with cavities in the middle, ceramic cores need to be installed in the parts in the investment manufacturing stage, and the problems of difficult positioning control and the like exist. And this application separates model 1 and ceramic core 2, sets up ceramic core fulcrum 3 in model 1 and fixes a position and be used for installing ceramic core 2, just so can separately make both, and model 1 can adopt quick forming techniques such as 3D printing to make, and ceramic core 2 adopts conventional method preparation, then assembles the two, can reduce the manufacturing cycle of fired mold greatly, practices thrift manufacturing cost.
In order to further improve the positioning accuracy of the ceramic core 2, the ceramic core fulcrums 3 are distributed in three directions of the module, wherein the fulcrums in the direction X are located on two cutting surfaces at two ends of the module, the module at each end is provided with 2 fulcrums, the fulcrums in the direction Y are located on the surface of an inner cavity of the module, 2 fulcrums are arranged on the air inlet side of the module, 1 fulcrum is arranged in the middle of the air exhaust side, and the fulcrum in the direction Z is located at the position of the cross section or the round hole of the ceramic core and is provided with. The direction X, Y, Z is shown in the labels of fig. 2 and 4.
In order to improve the structural strength of the model 1, the inner surface of the model 1 is provided with reinforcing rib plates 5, the reinforcing rib plates 5 are of a diamond structure, and the thickness of the reinforcing rib plates 5 is not more than the area of the position of the ceramic core 2.
The method for manufacturing the blade with the complex cavity comprises the following steps:
a. manufacturing a module: dividing the model into two-segment or multi-segment modules along a parting surface, printing and manufacturing the modules by using a rapid prototyping technology, and then arranging a ceramic core fulcrum and a positioning pin hole in the modules;
b. manufacturing a ceramic core: manufacturing a ceramic core according to the shape of a cavity in the middle of the part;
c. assembling the module with the ceramic core: mounting the ceramic core on one of the lamella modules, taking the ceramic core fulcrum as a positioning point, then mounting the other modules, and bonding and fixing;
d. and (3) trimming a fired mold: brushing, repairing and polishing the joint surface gap of the mounted assembly to enable the surface to be smooth and flat, and completing investment pattern manufacturing;
e. casting parts: and (4) sequentially completing the production processes of combining a module, manufacturing a shell, dewaxing and sintering, casting, carrying out heat treatment and inspecting according to the general flow of investment casting to obtain the required part.
The invention mainly combines the rapid forming technology with the investment casting technology, utilizes the rapid forming technology to prepare the external module, utilizes the ceramic core as the middle insert to prepare the investment, and then adopts the investment casting method to cast the parts, thereby solving the problem that the complex cavity blade can not be manufactured by rapid forming, saving the cycle and the cost of mold design and manufacture, and being very suitable for new product development and small batch production.
As shown in figure 1, a model 1 to be manufactured is divided into two sections along a parting surface, namely a first module 11 and a second module 12, the two modules are of sheet body structures and can be spliced into a structure consistent with the appearance of a part, the size of each sheet body is controlled according to the compensation comprehensive shrinkage rate of 0.5% -2%, and the precision of the manufactured part is improved. Considering the processing cost and the actual demand of the rapid prototyping technology, the thickness of the first module 11 and the second module 12 is 0.5-2 mm, and in order to prevent the module from deforming, the reinforcing rib plate 5 can be manufactured in the module sheet body, the reinforcing rib plate 5 is vertical to the sheet body, the shape of the reinforcing rib plate is a diamond structure as shown in fig. 1, and the structural strength of the module sheet body can be improved. The thickness of the reinforcing rib plates 5 is not more than the position area of the ceramic core 2, so that the interference between the reinforcing rib plates 5 and the ceramic core 2 is prevented.
In order to ensure the relative position of the ceramic core 3 and the appearance in the module, at least three ceramic core fulcrums 3 are arranged at the inner cavity part of the module, and the plurality of ceramic core fulcrums 3 are required to ensure that the degree of freedom of the ceramic core 2 in a three-dimensional space is zero. The mounting mode of the ceramic core supporting point 3 can be that when a module is manufactured, a clamping hole is preset at the position where the ceramic core supporting point 3 needs to be placed, and the ceramic core supporting point 3 is clamped in the clamping hole to be fixed.
In order to improve the positioning accuracy of the ceramic core 2, the ceramic core fulcrums 3 are distributed in three directions of the module 1, wherein the fulcrums in the direction X are located on two cutting surfaces at two ends of the module, the module at each end is provided with 2 fulcrums, the fulcrums in the direction Y are located on the surface of an inner cavity of the module, the air inlet side is provided with 2 fulcrums, the middle part of the air exhaust side is provided with 1 fulcrum, and the fulcrum in the direction Z is located at the position of the ceramic core cross section or a round hole and is provided with 1. Wherein direction X, Y, Z is as indicated by the labels in fig. 2 and 4.
The specific assembling process of the module and the ceramic core is as follows: as shown in fig. 2-5, the first module 11 is fixed by plasticine to prevent shaking, then the ceramic core 2 is placed in the first module 11 and is close to the ceramic core fulcrum 3 without a gap to realize positioning, and finally softened paraffin is adopted to perform multi-point adhesion and fixation on the edges of the first module 11 and the ceramic core 2. And after the ceramic core 2 is installed, assembling the second module 12, after the assembly of the module and the ceramic core 2 is completed, performing multi-point bonding on the edge of a parting surface by adopting softened paraffin, and brushing and repairing the parting gap and the ceramic core end gap by adopting the paraffin in the phase of investment dressing so as to ensure that the surface of the investment is smooth and flat.
Further, in order to correspond with ceramic core fulcrum 3, when carrying out the equipment of module and ceramic core 2, arrange ceramic core 2 in first module 11 on the back, respectively with 2 fulcrums of the last air side of first module 11, 1 fulcrum of direction of height, and 4 fulcrums of end cutting plane lean on tightly, it is fixed to adopt softened paraffin to carry out the multiple spot adhesion first module 11 and 2 edges of ceramic core, then close second module 12 and the module of fixed ceramic core 2, reserve location pinhole 4 on passing the module with the pin of 3 at least diameters 1 ~ 3mm, align two modules well, it is fixed to carry out the multiple spot adhesion to the module edge after merging afterwards. And finally, before the investment is trimmed, the pins are taken down, and then the softened paraffin is used for brushing, repairing and polishing the investment.
The invention combines the rapid forming and the investment casting, solves the problem that the complex cavity blade can not be manufactured by the rapid forming, saves the cycle and the cost of the die design and the manufacture, is very suitable for new product development and small batch production, and has good practicability and application prospect.
Claims (10)
1. Manufacturing an investment pattern with a complex cavity blade, which is characterized in that: the ceramic core fixing device comprises a model (1) and a ceramic core (2) located in the model (1), wherein the model (1) is divided into two or more sections of modules along a parting surface, a plurality of ceramic core fulcrums (3) and positioning pin holes (4) are arranged in the model (1), the ceramic core (2) takes the ceramic core fulcrums (3) as positioning points and is fixed in the model (1) through softening paraffin in a multi-point adhesion mode, and the modules of the model (1) are also fixed through softening paraffin in a multi-point adhesion mode.
2. The pattern for making a blade with a complex cavity of claim 1 wherein: the ceramic core fulcrums (3) are distributed in three directions of the module, wherein the fulcrums in the direction X are located on the section planes at two ends of the module, the module at each end is provided with 2 fulcrums, the fulcrums in the direction Y are located on the surface of an inner cavity of the module, 2 fulcrums are arranged on the air inlet side of the module, 1 fulcrum is arranged in the middle of the air outlet side, and the fulcrum in the direction Z is located on the position of the cross section or the round hole of the ceramic core and is provided with 1 fulcrum.
3. The pattern for making a blade with a complex cavity of claim 1 wherein: and reinforcing rib plates are arranged on the inner surface of the model, are of a diamond structure, and have a thickness not exceeding the area of the position of the ceramic core.
4. The method for manufacturing the blade with the complex cavity is characterized by comprising the following steps:
a. manufacturing a module: dividing the model into two-segment or multi-segment modules along a parting surface, printing and manufacturing the modules by using a rapid prototyping technology, and then arranging a ceramic core fulcrum and a positioning pin hole in the modules;
b. manufacturing a ceramic core: manufacturing a ceramic core according to the shape of a cavity in the middle of the part;
c. assembling the module with the ceramic core: mounting the ceramic core on one of the lamella modules, taking the ceramic core fulcrum as a positioning point, then mounting the other modules, and bonding and fixing;
d. and (3) trimming a fired mold: brushing, repairing and polishing the joint surface gap of the mounted assembly to enable the surface to be smooth and flat, and completing investment pattern manufacturing;
e. casting parts: and (4) sequentially completing the production processes of combining a module, manufacturing a shell, dewaxing and sintering, casting, carrying out heat treatment and inspecting according to the general flow of investment casting to obtain the required part.
5. A method of manufacturing a blade with a complex cavity according to claim 1, characterised in that: the module is a sheet body consistent with the appearance structure of the part, the size of the sheet body is controlled according to the compensation comprehensive shrinkage rate of 0.5-2%, and the thickness of the sheet body is 0.5-2 mm.
6. A method of manufacturing a blade with a complex cavity according to claim 1, characterised in that: when the module is manufactured, a clamping hole is preset at the position where a ceramic core fulcrum needs to be placed, and the ceramic core fulcrum is clamped in the clamping hole to be fixed.
7. The method for manufacturing a blade with a complex cavity as claimed in any one of claims 4 to 6, wherein: the ceramic core supporting points at least comprise three, and the plurality of ceramic core supporting points ensure that the degree of freedom is zero in a three-dimensional space when the ceramic core is installed on the module.
8. The method of manufacturing a blade with a complex cavity according to claim 7, wherein: the ceramic core supporting points are distributed in three directions of the module, wherein the supporting points in the direction X are located on two cutting surfaces at the two ends of the module, the module at each end is provided with 2 supporting points, the supporting points in the direction Y are located on the surface of an inner cavity of the module, the air inlet side is provided with 2 supporting points, the middle part of the air exhaust side is provided with 1 supporting point, and the supporting points in the direction Z are located at the positions of the cross sections or the round holes of the ceramic core and are provided with 1 supporting point.
9. The method of manufacturing a blade with a complex cavity according to claim 8, wherein: when carrying out the equipment of module and ceramic core, arrange the ceramic core in on the module, respectively with 2 fulcrums in the last air inlet side of module, 1 fulcrum of direction of height, and 4 fulcrums in the end cutting plane lean on tightly, it is fixed to adopt softened paraffin to carry out the multiple spot adhesion to module and ceramic core edge, then close another module and the module of fixed good ceramic core, pass the location pinhole of reserving on the module with the 1 ~ 3 mm's of at least 3 diameters pin, align two modules well, it is fixed to carry out the multiple spot adhesion to the module edge after the final merger.
10. A method of manufacturing a blade with a complex cavity as claimed in claim 9, wherein: and after the assembly of the module and the ceramic core is finished, taking down the pin in the locating pin hole, then performing multi-point bonding on the edge of the parting surface by adopting softened paraffin, and performing brushing and repairing on the parting gap and the ceramic core end gap by adopting paraffin in the stage of investment dressing.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010031737.5A CN111085661A (en) | 2020-01-13 | 2020-01-13 | Investment mold and method for manufacturing blade with complex cavity |
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| CN202010031737.5A CN111085661A (en) | 2020-01-13 | 2020-01-13 | Investment mold and method for manufacturing blade with complex cavity |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111250704A (en) * | 2020-05-06 | 2020-06-09 | 中国航空制造技术研究院 | Clad type composite additive manufacturing method |
| CN113333670A (en) * | 2021-05-25 | 2021-09-03 | 贵州安吉航空精密铸造有限责任公司 | Preparation method of wax mould with built-in cavity |
| CN113414347A (en) * | 2021-07-01 | 2021-09-21 | 上海万泽精密铸造有限公司 | Method for controlling dimensional accuracy of hollow blade wax mold |
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Application publication date: 20200501 |