CN112517854A - Ceramic core positioning method for manufacturing hollow turbine blade - Google Patents
Ceramic core positioning method for manufacturing hollow turbine blade Download PDFInfo
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- CN112517854A CN112517854A CN202011520801.2A CN202011520801A CN112517854A CN 112517854 A CN112517854 A CN 112517854A CN 202011520801 A CN202011520801 A CN 202011520801A CN 112517854 A CN112517854 A CN 112517854A
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- 239000000919 ceramic Substances 0.000 title claims abstract description 85
- 238000000034 method Methods 0.000 title claims abstract description 32
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 26
- 230000008093 supporting effect Effects 0.000 claims abstract description 19
- 230000005484 gravity Effects 0.000 claims abstract description 18
- 238000012545 processing Methods 0.000 claims abstract description 14
- 230000008602 contraction Effects 0.000 claims description 16
- 125000006850 spacer group Chemical group 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 6
- 230000013011 mating Effects 0.000 claims description 3
- 238000004513 sizing Methods 0.000 claims 1
- 238000003825 pressing Methods 0.000 abstract description 8
- 230000009286 beneficial effect Effects 0.000 description 10
- 239000000956 alloy Substances 0.000 description 5
- 229910045601 alloy Inorganic materials 0.000 description 5
- 230000000694 effects Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000005266 casting Methods 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
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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
- B22C9/10—Cores; Manufacture or installation of cores
- B22C9/108—Installation of cores
-
- 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
- B22C9/24—Moulds for peculiarly-shaped castings for hollow articles
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
The invention relates to a ceramic core positioning method for manufacturing a hollow turbine blade, and belongs to the technical field of turbine blade processing. The method comprises the following steps: determining a limit distance according to a manufacturing process; determining a gravity center point for supporting the ceramic core according to the structures of the ceramic core and the mold, wherein the gravity center point is set as a limiting point; designing the size of a limiting pin for supporting the ceramic core according to the limiting distance; designing the hole opening position and the hole opening direction on the die according to the sizes of the limiting point and the limiting pin; processing and manufacturing the limiting pin according to the size of the limiting pin to obtain the limiting pin; opening holes on the die according to the hole opening positions and the hole opening directions; and inserting the limiting pin into the hole and abutting against the ceramic core. The ceramic core positioning method solves the problems of core deviation and wall thickness caused by unstable placement of the core in the die in the pressing process of the hollow turbine blade.
Description
Technical Field
The invention belongs to the technical field of turbine blade processing, and particularly relates to a ceramic core positioning method for manufacturing a hollow turbine blade.
Background
At present, a hollow turbine blade for an aeroengine and a gas turbine is generally prepared by adopting a ceramic core, wherein the ceramic core is fixed in an outer die when the hollow turbine blade is molded, and then the hollow turbine blade is finally obtained through pressing, coating shell making, casting and core removing.
The hollow turbine blade has strict requirements on the size precision, the wall thickness and the like of the inner cavity, and the requirement on the performance of the core is higher, so that the positioning of the core in the outer die is also very important. When the hollow turbine blade is molded, the mold core is placed unstably in the mold, the mold core slides easily in the mold, core deviation and wall thickness problems are caused, and the produced hollow turbine blade is scrapped.
In addition, in the development process of the turbine blade, the structural characteristics, process requirements, raw material performance and the like of a product need to be considered in the design of a mold, the hollow turbine blade relates to the accurate positioning of a ceramic core in an outer mold, the mold structure is more complex, and the problems of low mold taking efficiency, high mold processing difficulty, low precision and the like are inevitably caused by the increase of the parting surface of the mold or excessive use of mold blocks.
Disclosure of Invention
The invention provides a ceramic core positioning method for manufacturing a hollow turbine blade, aiming at solving the technical problems of core deviation and wall thickness caused by unstable placement of a core in a mould in the pressing process of the hollow turbine blade.
The technical scheme for solving the technical problems is as follows: a method of positioning a ceramic core for the manufacture of a hollow turbine blade, comprising the steps of:
determining a limit distance according to a manufacturing process;
determining a gravity center point for supporting the ceramic core according to the structures of the ceramic core and the mold, wherein the gravity center point is set as a limiting point;
designing the size of a limiting pin for supporting the ceramic core according to the limiting distance;
designing the hole opening position and the hole opening direction on the die according to the sizes of the limiting point and the limiting pin;
processing and manufacturing the limiting pin according to the size of the limiting pin to obtain the limiting pin;
forming corresponding holes on the die according to the hole forming position and the hole forming direction;
and inserting the limiting pin into the hole and abutting against the ceramic core.
The invention has the beneficial effects that: (1) the core is accurately limited through the limiting pin, so that the integrity of the wax mould and the complex structure of the free end of the wax mould are guaranteed, and the rapidness of taking the wax mould is guaranteed;
(2) other parting structures or other auxiliary structures of the ceramic core are not required to be added, the structural complexity of the mold is not required to be increased, and the mold taking efficiency is ensured;
(3) through simple spacer pin, solve hollow turbine blade and slide core deflection and the wall thickness problem that leads to because of the core in the pressing process, simplify the mould structure, promoted production efficiency, guaranteed product quality simultaneously.
On the basis of the technical scheme, the invention can be further improved as follows.
Further, according to the manufacturing process, the step of determining the limiting distance comprises the following steps:
determining the shrinkage rate of a material for manufacturing the hollow turbine blade and the size of the ceramic core;
obtaining a shrinkage distance according to the shrinkage rate and the size;
and determining a limiting distance according to the contraction distance, wherein the limiting distance is greater than the contraction distance.
The beneficial effect of adopting the further scheme is that: do benefit to and confirm to obtain spacing distance, because spacing distance is greater than the shrink distance to the problem that the material shrink influences the support effect can not appear.
Further, obtaining the shrinkage distance according to the shrinkage rate and the size is to multiply the shrinkage rate by the width of the ceramic core to obtain the shrinkage distance.
The beneficial effect of adopting the further scheme is that: the contraction distance can be calculated conveniently.
Further, according to the contraction distance, the limit distance is determined and calculated by adopting the following formula:
A=B*(1+C);
wherein A is a limit distance, B is a contraction distance, and C is 0.5-1.
The beneficial effect of adopting the further scheme is that: the limiting distance is conveniently calculated.
Further, the shrinkage is 1.8% -2%.
The beneficial effect of adopting the further scheme is that: the shrinkage rate is low, and the manufactured turbine blade has better effect.
Furthermore, the limiting distance is 3-5 mm.
The beneficial effect of adopting the further scheme is that: the ceramic core is supported in a limiting manner.
Further, the center of gravity point for supporting the ceramic core is determined according to the structures of the ceramic core and the mold, and the center point is the center point of the contact surface of the inclined lower end of the ceramic core and the inner cavity of the mold.
The beneficial effect of adopting the further scheme is that: the center of gravity point is very convenient to determine, and the limiting supporting effect is better.
Further, according to the limiting distance, the size of the limiting pin for supporting the ceramic core is determined according to the limiting distance and the thickness of the mold, and the length of the limiting pin is larger than the sum of the limiting distance and the thickness of the mold.
The beneficial effect of adopting the further scheme is that: the size of the limiting pin is determined conveniently.
Further, the spacer pin includes front end and screw thread end, the one end of front end with the one end integrated into one piece of screw thread end, the front end be used for with ceramic core butt, the screw thread end be used for with the mould is connected, the hole including be used for the through-hole that the front end passed with be used for with screw thread end complex screw hole.
The beneficial effect of adopting the further scheme is that: can conveniently be to the spacing support of ceramic core through the front end, can not influence the suppression of wax matrix again simultaneously.
Furthermore, the diameter of the front end is 0.5mm-1.5mm, and the diameter of the threaded end is 2mm-5 mm.
The beneficial effect of adopting the further scheme is that: the influence on the wax mould pressing is better.
Drawings
FIG. 1 is a schematic view of the connection between a stopper pin and a mold according to the present invention.
In the drawings, the components represented by the respective reference numerals are listed below:
1. the die comprises a die 2, a limiting pin 3 and a ceramic core.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
Examples
The present embodiment provides a ceramic core positioning method for manufacturing a hollow turbine blade, comprising the steps of:
step 1: determining a limit distance according to a manufacturing process, and specifically adopting the following steps:
step 11: determining the shrinkage rate of the material for manufacturing the hollow turbine blade and the size of the ceramic core.
Step 12: and obtaining a shrinkage distance according to the shrinkage rate and the size, specifically, multiplying the shrinkage rate by the width of the ceramic core to obtain the shrinkage distance.
Step 13: and determining a limiting distance according to the contraction distance, wherein the limiting distance is greater than the contraction distance. The method specifically comprises the following steps:
the formula is as follows:
A=B*(1+C);
wherein A is a limit distance, B is a contraction distance, and C is 0.5-1.
Wherein, spacing distance is the distance that is used for supporting ceramic core for ceramic core is supported.
Wherein, the material of the common hollow turbine blade is alloy, and the shrinkage rate of the common alloy is 1.8-2%. The spacing distance calculated according to the shrinkage rate of the alloy is 3-5 mm.
Step 2: and determining a gravity point for supporting the ceramic core according to the structures of the ceramic core and the mould, wherein the gravity point is set as a limiting point. Specifically, the central point of the contact surface of the inclined lower end of the ceramic core and the inner cavity of the mold is determined, and the central point is the gravity center point.
The ceramic core is placed in the mould in an inclined state during processing, the edge of the ceramic core is arc-shaped or linear, and the central points of the contact surfaces of the arc-shaped or linear ceramic core and the inner cavity of the mould are gravity points.
And step 3: and designing the size of a limiting pin for supporting the ceramic core according to the limiting distance. Specifically, the length of the limiting pin is determined according to the limiting distance and the thickness of the die, and the length of the limiting pin is greater than the sum of the limiting distance and the thickness of the die. Wherein the spacer pin is used for passing through the mould and abutting against the ceramic core, supporting and fixing the ceramic core and positioning the ceramic core.
The limiting pin comprises a front end and a threaded end, one end of the front end and one end of the threaded end are integrally formed, the front end is used for being abutted against the ceramic core, and the threaded end is used for being connected with the mold. Wherein the other end of the threaded end can be provided with a rotating nut for conveniently rotating the bolt end.
Wherein, according to the above-mentioned spacing distance, the diameter of the front end of the general spacing pin is 0.5mm-1.5mm, and the diameter of the threaded end is 2mm-5 mm.
And 4, step 4: and designing the hole opening position and the hole opening direction on the die according to the sizes of the limiting point and the limiting pin. Specifically, according to the structure of the die, a hole which is communicated with the inner cavity of the die and penetrates through the die is designed, so that the limiting pin can be inserted into the hole. The position of the hole is determined by the position of the limiting point, the length of the size of the limiting pin in the hole opening direction and the thickness of the die are determined, and therefore the shortest hole is formed to enable the limiting pin to be abutted against the ceramic core.
And 5: and processing and manufacturing the limiting pin according to the size of the limiting pin to obtain the limiting pin.
The limiting pin is manufactured through a metal processing technology according to the size of the limiting pin, and when the limiting pin is processed, the processing precision and the coaxiality are guaranteed, the limiting pin is guaranteed to be flexibly adjusted, and the limiting pin is not deformed in the using process.
Step 6: and opening corresponding holes on the die according to the hole opening position and the hole opening direction.
Wherein the hole comprises a through hole for the front end to pass through and a threaded hole for mating with the threaded end.
And 7: the limiting pin is inserted into the hole, so that the threaded end is in threaded fit with the threaded hole, the front end enters the inner cavity of the mold through the through hole, the front end is driven to enter or exit the inner cavity of the mold by rotating the threaded end, and the front end is abutted against the ceramic core after entering the inner cavity of the mold, so that the ceramic core is positioned. Other parting structures or other auxiliary structures of the ceramic core do not need to be added, the structural complexity of the mold does not need to be increased, and the mold taking efficiency cannot be reduced.
Specifically, as shown in fig. 1, the positioning process for a ceramic core is enhanced using this embodiment.
In the process of wax mold pressing, a free end wax cap with a complex structure is designed on a core head of a ceramic core, and the positioning surface of the ceramic core in an external mold is an inclined surface. Therefore, the following method is adopted for positioning.
Step 1: determining a limit distance according to a manufacturing process, and specifically adopting the following steps:
step 11: determining the shrinkage rate of the material for manufacturing the hollow turbine blade and the size of the ceramic core. The hollow turbine blade is made of high-temperature alloy, and the shrinkage rate of the high-temperature alloy is 2%. The width of the ceramic core is 100 mm.
Step 12: and obtaining a shrinkage distance according to the shrinkage rate and the size, specifically, multiplying the shrinkage rate by the width of the ceramic core to obtain the shrinkage distance. The contraction distance is thus 100mm 2% =2 mm.
Step 13: and determining a limiting distance according to the contraction distance, wherein the limiting distance is greater than the contraction distance. The method specifically comprises the following steps:
the formula is as follows:
A=B*(1+C);
in the formula, A is a limit distance, B is a contraction distance, and C is 0.5.
Thereby calculating the spacing distance A to be 3 mm.
Wherein, spacing distance is the distance that is used for supporting ceramic core for ceramic core is supported.
Step 2: and determining a gravity point for supporting the ceramic core according to the structures of the ceramic core and the mould, wherein the gravity point is set as a limiting point. Specifically, the central point of the contact surface of the inclined lower end of the ceramic core and the inner cavity of the mold is determined, and the central point is the gravity center point.
The ceramic core is placed in the mould in an inclined state during processing, the edge of the ceramic core is arc-shaped or linear, and the central points of the contact surfaces of the arc-shaped or linear ceramic core and the inner cavity of the mould are gravity points.
And step 3: and designing the size of a limiting pin for supporting the ceramic core according to the limiting distance. Specifically, the length of the limiting pin is determined according to the limiting distance and the thickness of the die, and the length of the limiting pin is greater than the sum of the limiting distance and the thickness of the die. Wherein the spacer pin is used for passing through the mould and abutting against the ceramic core, supporting and fixing the ceramic core and positioning the ceramic core.
The limiting pin comprises a front end and a threaded end, one end of the front end and one end of the threaded end are integrally formed, the front end is used for being abutted against the ceramic core, and the threaded end is used for being connected with the mold. Wherein the other end of the threaded end can be provided with a rotating nut for conveniently rotating the bolt end.
According to the limiting distance, the diameter of the front end of the limiting pin is 1mm, and the diameter of the threaded end is 4 mm. The diameter of the spin nut was 20 mm.
And 4, step 4: and designing the hole opening position and the hole opening direction on the die according to the sizes of the limiting point and the limiting pin. Specifically, according to the structure of the die, a hole which is communicated with the inner cavity of the die and penetrates through the die is designed, so that the limiting pin can be inserted into the hole. The position of the hole is determined by the position of the limiting point, the length of the size of the limiting pin in the hole opening direction and the thickness of the die are determined, and therefore the shortest hole is formed to enable the limiting pin to be abutted against the ceramic core.
And 5: and processing and manufacturing the limiting pin according to the size of the limiting pin to obtain the limiting pin.
The limiting pin is manufactured through a metal processing technology according to the size of the limiting pin, and when the limiting pin is processed, the processing precision and the coaxiality are guaranteed, the limiting pin is guaranteed to be flexibly adjusted, and the limiting pin is not deformed in the using process.
Step 6: and opening holes on the die according to the hole opening positions and the hole opening directions.
Wherein the hole comprises a through hole for the front end to pass through and a threaded hole for mating with the threaded end.
And 7: the limiting pin is inserted into the hole, so that the threaded end is in threaded fit with the threaded hole, the front end enters the inner cavity of the mold through the through hole, the front end is driven to enter or exit the inner cavity of the mold by rotating the threaded end, and the front end is abutted against the ceramic core after entering the inner cavity of the mold, so that the ceramic core is positioned. Other parting structures or other auxiliary structures of the ceramic core do not need to be added, the structural complexity of the mold does not need to be increased, and the mold taking efficiency cannot be reduced.
Specifically, in the process of manufacturing the hollow turbine blade, when a wax mold is pressed, a ceramic core is placed in an outer mold, then a limiting pin is screwed, the mold is closed and pressed, and after pressing is completed, the limiting pin is screwed out quickly before mold taking until mold taking operation is not influenced. The operation flow is simple, convenient and quick, the pressing efficiency is improved, and the integrity of the wax mould and the free end structure is ensured.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings, which are merely for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be construed as limiting the invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
In the description of the invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted", "connected" and "connected" are to be construed broadly, e.g. as being fixed or detachable or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
It is to be noted that "comprising" in the present invention means that it may include other components in addition to the components described, and the "comprising" may be replaced with "being" or "consisting of … …" in a closed manner.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. A method of positioning a ceramic core for use in the manufacture of a hollow turbine blade, comprising the steps of:
determining a limit distance according to a manufacturing process;
determining a gravity center point for supporting the ceramic core according to the structures of the ceramic core and the mold, wherein the gravity center point is set as a limiting point;
designing the size of a limiting pin for supporting the ceramic core according to the limiting distance;
designing the hole opening position and the hole opening direction on the die according to the sizes of the limiting point and the limiting pin;
processing and manufacturing the limiting pin according to the size of the limiting pin to obtain the limiting pin;
forming corresponding holes on the die according to the hole forming position and the hole forming direction;
and inserting the limiting pin into the hole and abutting against the ceramic core.
2. The method of claim 1, wherein determining a stopping distance comprises the steps of, according to a manufacturing process:
determining the shrinkage rate of a material for manufacturing the hollow turbine blade and the size of the ceramic core;
obtaining a shrinkage distance according to the shrinkage rate and the size;
and determining a limiting distance according to the contraction distance, wherein the limiting distance is greater than the contraction distance.
3. The method of claim 2, wherein the obtaining a shrinkage distance based on the shrinkage rate and the size is multiplying the shrinkage rate by a width of the ceramic core to obtain the shrinkage distance.
4. The method of claim 3, wherein said determining a spacing distance based on said contraction distance is calculated using the formula:
A=B*(1+C);
wherein A is a limit distance, B is a contraction distance, and C is 0.5-1.
5. The method of claim 2, wherein the shrinkage is 1.8% -2%.
6. The method of claim 5, wherein the spacing distance is 3-5 mm.
7. The method of claim 1, wherein the determining the center of gravity point for supporting the ceramic core based on the structure of the ceramic core and the mold is the determining the center point of the contact surface of the inclined lower end of the ceramic core and the inner cavity of the mold, and the center point is the center of gravity point.
8. The method of claim 1, wherein the sizing of the spacer pin for supporting the ceramic core according to the spacing distance is such that a length of the spacer pin is determined according to the spacing distance and a thickness of the mold, the length of the spacer pin being greater than a sum of the spacing distance and the thickness of the mold.
9. The method of claim 8, wherein the spacer pin comprises a front end and a threaded end, one end of the front end being integrally formed with one end of the threaded end, the front end being adapted to abut the ceramic core, the threaded end being adapted to be coupled to the mold, the bore comprising a through-hole for the front end to pass through and a threaded bore for mating with the threaded end.
10. The method of claim 9, wherein the nose has a diameter of 0.5mm to 1.5mm and the threaded end has a diameter of 2mm to 5 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011520801.2A CN112517854A (en) | 2020-12-21 | 2020-12-21 | Ceramic core positioning method for manufacturing hollow turbine blade |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011520801.2A CN112517854A (en) | 2020-12-21 | 2020-12-21 | Ceramic core positioning method for manufacturing hollow turbine blade |
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| CN102125998A (en) * | 2010-12-31 | 2011-07-20 | 大同北方天力增压技术有限公司 | Method for manufacturing impeller mould for gas compressor of turbocharger |
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| CN210412407U (en) * | 2019-08-18 | 2020-04-28 | 山西大学 | Hollow turbine blade precision casting wax mold for realizing automatic ceramic core clamping |
| CN109351912B (en) * | 2018-11-20 | 2020-11-27 | 安徽应流航源动力科技有限公司 | Positioning die and positioning method for adjusting ceramic core of engine blade |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA1190020A (en) * | 1980-04-02 | 1985-07-09 | Frank T. Obrochta | Cambered core positioning for injection molding |
| CN1183328A (en) * | 1997-10-22 | 1998-06-03 | 冶金工业部钢铁研究总院 | Method for mfg. wax pattern |
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