CN111036852A - Method for positioning silicon-based ceramic core for single crystal/directional guide blade - Google Patents
Method for positioning silicon-based ceramic core for single crystal/directional guide blade Download PDFInfo
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- CN111036852A CN111036852A CN201911177491.6A CN201911177491A CN111036852A CN 111036852 A CN111036852 A CN 111036852A CN 201911177491 A CN201911177491 A CN 201911177491A CN 111036852 A CN111036852 A CN 111036852A
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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
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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
- B22C9/10—Cores; Manufacture or installation of cores
- B22C9/103—Multipart cores
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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
- B22C9/24—Moulds for peculiarly-shaped castings for hollow articles
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- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B11/00—Single-crystal growth by normal freezing or freezing under temperature gradient, e.g. Bridgman-Stockbarger method
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- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B29/00—Single crystals or homogeneous polycrystalline material with defined structure characterised by the material or by their shape
- C30B29/10—Inorganic compounds or compositions
- C30B29/52—Alloys
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Crystallography & Structural Chemistry (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention aims to provide a positioning method of a split ceramic core for forming an independent cavity so as to meet the preparation requirement of a single crystal/directional hollow turbine guide blade. The method specifically comprises the following steps: the ceramic positioning strip coated with the high-temperature adhesive is inserted between two split ceramic core heads for forming independent cavities, drying is carried out at room temperature, and the split ceramic core heads are bonded into a whole after the high-temperature adhesive is completely dried, so that the split ceramic core can be well fixed, and the positioning precision is improved. The same material is preferred for a good mating relationship between the ceramic core and the ceramic locating strip. Then wrapped and fixed inside the formwork in the subsequent shell making process.
Description
Technical Field
The invention belongs to the field of high-temperature alloy, and particularly provides a positioning method of a ceramic core for a single crystal/directional guide blade.
Background
The turbine blade is the most important hot end component of the gas turbine, and the temperature bearing capacity and the service life of the turbine blade directly influence the performance and the service cycle of a combustion engine. In recent years, with the development of engine industry, the inlet temperature of engines has been increasing, and the requirement for the temperature-bearing capability of turbine blades has been increasing. The conventional methods for improving the temperature bearing capacity of the blade mainly comprise the steps of improving the service temperature of materials, reducing the temperature of the blade by using an advanced coating and reducing the temperature of the blade by using an advanced cooling technology. Among them, the most effective method is to design a reasonable turbine blade structure (shape and inner cavity) to improve cooling efficiency. The silicon-based ceramic core has the characteristics of high temperature resistance, strong chemical stability, easy removal and the like, and is mainly used for forming the inner cavity of the hollow turbine blade. For a single crystal/directional turbine guide blade, especially for a large-size single crystal/directional turbine guide blade for a gas turbine with a plurality of independent inner cavities, the size is large, the directional solidification time is long, and a silicon-based ceramic core is in a high-temperature environment for a long time and inevitably deforms, so that the size of a spacer plate of two adjacent inner cavities of the turbine blade and the relative position of the inner cavities are changed, and the blade is scrapped. If the mold core is singly used for positioning, because the thermal expansion coefficients of the mold core material and the mold shell material are different, the thermal expansion coefficient of the mold core material and the mold shell material are not matched, a gap is generated between the mold shell and the mold core, and the positioning precision is difficult to ensure. Meanwhile, the ceramic core used for forming the inner cavity is also large in size, and the difficulty of preparing the integral core and controlling high-temperature deformation is greatly increased, so that the ceramic core used for forming each independent inner cavity is usually designed into a split core. How to select a positioning method suitable for forming a split ceramic core for an independent cavity is a difficult problem which is urgently needed to be solved in actual production.
Disclosure of Invention
The invention aims to provide a positioning method of a split ceramic core for forming an independent cavity so as to meet the preparation requirement of a single crystal/directional hollow turbine guide blade.
The technical scheme of the invention is as follows:
a method for positioning a silicon-based ceramic core for a single crystal/directional guide blade is characterized by comprising the following steps: firstly, the ceramic positioning strip coated with the high-temperature adhesive is inserted between two split ceramic core heads for forming independent cavities, drying is carried out at room temperature, and the split ceramic core heads are bonded into a whole after the high-temperature adhesive is completely dried, so that the split ceramic core can be well fixed, and the positioning precision is improved, as shown in figure 1. The same material is preferred for a good mating relationship between the ceramic core and the ceramic locating strip. Then wrapped and fixed inside the formwork in the subsequent shell making process.
As a preferred technical scheme:
width T of ceramic positioning strip inserted between two divided ceramic cores2The distance T between the two ceramic cores is 0.5-2mm smaller; width T of ceramic positioning strip not inserted between two divided ceramic cores1The distance T between the two ceramic cores is 4-10mm larger; height H of ceramic positioning strip inserted between two divided ceramic cores2Width W of core head of ceramic core1The size is 0.5-5 mm. The width W of the split ceramic core is 80-250mm, and the width W of the core head110-25mm, and the distance T between two adjacent split ceramic cores is 5-20 mm. Namely the size range of the ceramic positioning strip: t is not less than 9mm1≤30mm，3mm≤T2≤19.5mm，2mm≤H1≤10mm(H1The height of the ceramic positioning strip which is not inserted between the two split ceramic cores) is less than or equal to 5mm and less than or equal to H2≤24.5mm。
The split ceramic core and the ceramic positioning strip are made of silicon dioxide base materials, and the plasticizer is paraffin-based plasticizer.
The longitudinal section of the ceramic positioning strip inserted between the two split ceramic core heads for forming the independent cavity can be T-shaped or rectangular at the same time, or the section of one end can be T-shaped, and the section of the other end can be rectangular.
The high-temperature binder adopts a mixture of EC95 fused corundum powder and silica sol, the mesh number of the EC95 fused corundum powder is 600 meshes and 800 meshes, the average grain size of the silica sol is 8-15nm, the pH value is 8.5-10, and the SiO of the silica sol is2The content is 18-25 wt.%, Na2The content of O is less than or equal to 0.4 wt.%, and the mass ratio of powder to liquid is (3-3.5): 1.
The invention discloses a method for positioning a silicon-based ceramic core, which is characterized by comprising the following specific steps of:
firstly, preparing a split ceramic core and a ceramic positioning strip biscuit for forming an independent cavity; sintering the ceramic core and the ceramic positioning strip biscuit to prepare a finished ceramic core and a ceramic positioning strip (the sintering temperature is 1180-1200 ℃, and the sintering time is 8-12 hours), wherein the positioning schematic diagram of the ceramic positioning strip is shown in figure 1, the structure of the ceramic core is shown in figure 2, and the structure of the ceramic positioning strip is shown in figure 3; then coating a high-temperature adhesive on the surface of the ceramic positioning strip, which is in contact with the ceramic core, quickly inserting the ceramic positioning strip between the two ceramic core heads, and standing at room temperature until the ceramic positioning strip is completely dried, so that the ceramic positioning strip can be firmly bonded; and finally, placing the hollow turbine guide vane into a mould to be pressed by a wax mould, and wrapping and fixing the hollow turbine guide vane in the mould shell in the subsequent shell making process, thereby forming the fixing method of the ceramic core for accurately positioning the hollow turbine guide vane.
The method for positioning the silicon-based ceramic core is particularly suitable for preparing the single crystal/directional hollow turbine guide blade.
Drawings
FIG. 1 is a schematic view of the positioning of a ceramic positioning strip.
FIG. 2 is a schematic illustration of a ceramic core construction.
FIG. 3 is a schematic view of a structure of a ceramic positioning strip.
FIG. 4 is a schematic view of a ceramic core bonded to a ceramic positioning strip.
Reference numerals: 1. a ceramic core; 2. a ceramic positioning strip; 3. a high temperature binder; 21. a T-shaped ceramic positioning strip; 22. rectangular ceramic positioning strip.
Detailed Description
Example 1
Firstly, preparing split ceramic cores and ceramic positioning strip biscuits for forming independent cavities, wherein the ceramic cores and the ceramic positioning strips are both prepared from silicon dioxide-based materials, and the plasticizer is paraffin-based plasticizer; the width W of the split ceramic core is 80mm, and the width W of the core head1Is 10mm, and the distance T between two adjacent split ceramic cores is 5 mm; size of ceramic positioning bar: t is1＝9mm，T2＝3mm，H1＝2mm，H25 mm; sintering the ceramic core and the ceramic positioning strip biscuit to prepare a finished ceramic core and a finished ceramic positioning strip, wherein the sintering temperature of the ceramic core and the ceramic positioning strip is 1180 ℃, and the sintering time is 8 hours; then smearing a small amount of high-temperature adhesive on the surface of the ceramic positioning strip, which is in contact with the ceramic core, quickly inserting the adhesive between core heads of the two ceramic cores, standing at room temperature until the adhesive is completely dried, wherein the high-temperature adhesive is a mixture of EC95 fused corundum powder and silica sol, the mesh number of the EC95 fused corundum powder is 600 meshes, the average particle size of the silica sol is 8nm, the pH value is 8.5, and SiO is used as the SiO adhesive2The content (mass ratio) is 18 percent, Na2The content (mass ratio) of O is 0.2%, and the powder-liquid ratio (mass ratio) is 3: 1; and finally, placing the hollow turbine guide vane into a mould to be pressed by a wax mould, and wrapping and fixing the hollow turbine guide vane in the mould shell in the subsequent shell making process, thereby forming the fixing method of the ceramic core for accurately positioning the hollow turbine guide vane.
Example 2
Firstly, preparing split ceramic cores and ceramic positioning strip biscuits for forming independent cavities, wherein the ceramic cores and the ceramic positioning strips are both prepared from silicon dioxide-based materials, and the plasticizer is paraffin-based plasticizer; the width W of the split ceramic core is 250mm, and the width W of the core head1The distance T between two adjacent split ceramic cores is 20mm, and the distance T is 25 mm; size of ceramic positioning bar: t is1＝30mm，T2＝19.5mm，H1＝10mm，H224.5 mm; sintering the ceramic core and the ceramic positioning strip biscuit to prepare a finished ceramic core and a finished ceramic positioning strip, wherein the sintering temperature of the ceramic core and the ceramic positioning strip is 1200 ℃, and the sintering time is 12 hours; then smearing a small amount of high-temperature adhesive on the surface of the ceramic positioning strip, which is in contact with the ceramic core, quickly inserting the high-temperature adhesive between core heads of the two ceramic cores, standing at room temperature until the high-temperature adhesive is completely dried, and firmly bonding, wherein the high-temperature adhesive is a mixture of EC95 fused corundum powder and silica sol, the mesh number of the EC95 fused corundum powder is 800 meshes, the average particle size of the silica sol is 15nm, the pH value is 10, and SiO is2The content (mass ratio) is 25 percent, Na2The content (mass ratio) of O is 0.4%, and the powder-liquid ratio (mass ratio) is 3.5: 1; and finally, placing the hollow turbine guide vane into a mould to be pressed by a wax mould, and wrapping and fixing the hollow turbine guide vane in the mould shell in the subsequent shell making process, thereby forming the fixing method of the ceramic core for accurately positioning the hollow turbine guide vane.
Example 3
Firstly, preparing split ceramic cores and ceramic positioning strip biscuits for forming independent cavities, wherein the ceramic cores and the ceramic positioning strips are both prepared from silicon dioxide-based materials, and the plasticizer is paraffin-based plasticizer; the width W of the split ceramic core is 150mm, and the width W of the core head115mm, and the distance T between two adjacent split ceramic cores is 12 mm; size of ceramic positioning bar: t is1＝20mm，T2＝11mm，H1＝5mm，H212 mm; sintering the ceramic core and the ceramic positioning strip biscuit to prepare a finished ceramic core and a finished ceramic positioning strip, wherein the sintering temperature of the ceramic core and the ceramic positioning strip is 1190 ℃, and the sintering time is 10 hours; then smearing a small amount of high-temperature adhesive on the surface of the ceramic positioning strip, which is in contact with the ceramic core, quickly inserting the high-temperature adhesive between core heads of the two ceramic cores, standing at room temperature until the high-temperature adhesive is completely dried, and firmly bonding, wherein the high-temperature adhesive is a mixture of EC95 fused corundum powder and silica sol, the mesh number of the EC95 fused corundum powder is 600 meshes, the average particle size of the silica sol is 10nm, the pH value is 9.5, and SiO is used as a bonding agent2The content (mass ratio) is 22 percent, and Na2The content (mass ratio) of O is 0.3%, the powder-to-liquid ratio (mass ratio) is 3.2:1; and finally, placing the hollow turbine guide vane into a mould to be pressed by a wax mould, and wrapping and fixing the hollow turbine guide vane in the mould shell in the subsequent shell making process, thereby forming the fixing method of the ceramic core for accurately positioning the hollow turbine guide vane.
The invention is not the best known technology.
The above embodiments are merely illustrative of the technical ideas and features of the present invention, and the purpose thereof is to enable those skilled in the art to understand the contents of the present invention and implement the present invention, and not to limit the protection scope of the present invention. All equivalent changes and modifications made according to the spirit of the present invention should be covered within the protection scope of the present invention.
Claims (9)
1. A method for positioning a silicon-based ceramic core for a single crystal/directional guide blade is characterized by comprising the following steps: the method comprises the steps of firstly inserting a ceramic positioning strip coated with a high-temperature adhesive between two split ceramic core heads for forming independent cavities, drying at room temperature, bonding the high-temperature adhesive into a whole after the high-temperature adhesive is completely dried, and then wrapping and fixing the high-temperature adhesive inside a formwork in the subsequent shell making process.
2. The method of positioning a silicon-based ceramic core as recited in claim 1, wherein: width T of ceramic positioning strip inserted between two divided ceramic cores2The distance T between the two ceramic cores is 0.5-2mm smaller; width T of ceramic positioning strip not inserted between two divided ceramic cores1The distance T between the two ceramic cores is 4-10mm larger; height H of ceramic positioning strip inserted between two divided ceramic cores2Width W of core head of ceramic core1The size is 0.5-5 mm.
3. The method of positioning a silicon-based ceramic core as recited in claim 2, wherein: the width W of the split ceramic core is 80-250mm, and the width W of the core head110-25mm, and the distance T between two adjacent split ceramic cores is 5-20 mm.
4. The method of positioning a silicon-based ceramic core as recited in claim 3, wherein: the split ceramic core and the ceramic positioning strip are made of silicon dioxide base materials, and the plasticizer is paraffin-based plasticizer.
5. The method of positioning a silicon-based ceramic core as recited in claim 1, wherein: the longitudinal section of the ceramic positioning strip inserted between the two split ceramic core heads for forming the independent cavity is T-shaped or rectangular at the same time, or the section of one end is T-shaped, and the section of the other end is rectangular.
6. The method of positioning a silicon-based ceramic core as recited in claim 1, wherein: the high-temperature binder adopts a mixture of EC95 fused corundum powder and silica sol, the mesh number of the EC95 fused corundum powder is 600 meshes and 800 meshes, the average grain size of the silica sol is 8-15nm, the pH value is 8.5-10, and the SiO of the silica sol is2The content is 18-25 wt.%, Na2The content of O is less than or equal to 0.4 wt.%, and the mass ratio of the powder to the liquid is 3-3.5: 1.
7. The method for positioning a silicon-based ceramic core as recited in claim 1, comprising the steps of:
firstly, preparing a split ceramic core and a ceramic positioning strip biscuit for forming an independent cavity; sintering the ceramic core and the ceramic positioning strip biscuit to prepare a finished ceramic core and a finished ceramic positioning strip; then coating a high-temperature adhesive on the surface of the ceramic positioning strip, which is in contact with the ceramic core, quickly inserting the ceramic positioning strip between the two ceramic core heads, and standing at room temperature until the ceramic positioning strip is completely dried, so that the ceramic positioning strip can be firmly bonded; and finally, placing the hollow turbine guide vane into a mould to be pressed by a wax mould, and wrapping and fixing the hollow turbine guide vane in the mould shell in the subsequent shell making process, thereby forming the fixing method of the ceramic core for accurately positioning the hollow turbine guide vane.
8. The method of positioning a silicon-based ceramic core as recited in claim 1, wherein: the sintering temperature of the ceramic core and the ceramic positioning strip is 1180-1200 ℃, and the sintering time is 8-12 hours.
9. The method of positioning a silicon-based ceramic core as recited in claim 1, wherein: the method is used for producing single crystal/directional hollow turbine guide blades.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911177491.6A CN111036852B (en) | 2019-11-26 | 2019-11-26 | Method for positioning silicon-based ceramic core for single crystal/directional guide blade |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102873275A (en) * | 2012-09-28 | 2013-01-16 | 西安航空动力股份有限公司 | Fixing method of isometric crystal and columnar crystal ceramic mold core in mold shell |
| CN103286275A (en) * | 2013-05-13 | 2013-09-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Single crystal guide vane ceramic mould core positioning method |
| US20140102656A1 (en) * | 2012-10-12 | 2014-04-17 | United Technologies Corporation | Casting Cores and Manufacture Methods |
| CN104439059A (en) * | 2014-12-08 | 2015-03-25 | 中国南方航空工业(集团)有限公司 | Production method of wax mold of hollow blade and mold used in production method |
| CN104923722A (en) * | 2015-06-24 | 2015-09-23 | 西安航空动力股份有限公司 | Method for controlling hollow guide blade upper edge plate cavity wall thickness |
-
2019
- 2019-11-26 CN CN201911177491.6A patent/CN111036852B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102873275A (en) * | 2012-09-28 | 2013-01-16 | 西安航空动力股份有限公司 | Fixing method of isometric crystal and columnar crystal ceramic mold core in mold shell |
| US20140102656A1 (en) * | 2012-10-12 | 2014-04-17 | United Technologies Corporation | Casting Cores and Manufacture Methods |
| CN103286275A (en) * | 2013-05-13 | 2013-09-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Single crystal guide vane ceramic mould core positioning method |
| CN104439059A (en) * | 2014-12-08 | 2015-03-25 | 中国南方航空工业(集团)有限公司 | Production method of wax mold of hollow blade and mold used in production method |
| CN104923722A (en) * | 2015-06-24 | 2015-09-23 | 西安航空动力股份有限公司 | Method for controlling hollow guide blade upper edge plate cavity wall thickness |
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