CN116833391A - Preparation method of single-crystal superalloy turbine blade - Google Patents
Preparation method of single-crystal superalloy turbine blade Download PDFInfo
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- CN116833391A CN116833391A CN202310635697.9A CN202310635697A CN116833391A CN 116833391 A CN116833391 A CN 116833391A CN 202310635697 A CN202310635697 A CN 202310635697A CN 116833391 A CN116833391 A CN 116833391A
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- 239000013078 crystal Substances 0.000 title claims abstract description 143
- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 37
- 238000002360 preparation method Methods 0.000 title claims abstract description 13
- 238000010899 nucleation Methods 0.000 claims abstract description 70
- 238000007711 solidification Methods 0.000 claims abstract description 34
- 230000008023 solidification Effects 0.000 claims abstract description 34
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 24
- 239000000956 alloy Substances 0.000 claims abstract description 24
- 239000007788 liquid Substances 0.000 claims abstract description 18
- 238000005266 casting Methods 0.000 claims abstract description 16
- 238000004519 manufacturing process Methods 0.000 claims abstract description 15
- 230000035772 mutation Effects 0.000 claims abstract description 12
- 238000000034 method Methods 0.000 claims description 24
- 238000005245 sintering Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- 230000008018 melting Effects 0.000 claims description 5
- 238000002844 melting Methods 0.000 claims description 5
- 230000000694 effects Effects 0.000 abstract description 3
- 239000002585 base Substances 0.000 description 8
- 239000000919 ceramic Substances 0.000 description 5
- 238000001816 cooling Methods 0.000 description 5
- 230000006911 nucleation Effects 0.000 description 4
- 239000002002 slurry Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000004512 die casting Methods 0.000 description 3
- 239000012535 impurity Substances 0.000 description 3
- 239000007791 liquid phase Substances 0.000 description 3
- 239000007790 solid phase Substances 0.000 description 3
- 230000006978 adaptation Effects 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 210000001787 dendrite Anatomy 0.000 description 2
- 238000001035 drying Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 239000003513 alkali Substances 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 125000005842 heteroatom Chemical group 0.000 description 1
- 239000012071 phase Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000010956 selective crystallization Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D27/00—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting
- B22D27/04—Influencing the temperature of the metal, e.g. by heating or cooling the mould
- B22D27/045—Directionally solidified castings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
Abstract
The application relates to a preparation method of a single crystal superalloy turbine blade, which comprises the following steps: determining the placement position and the three-dimensional direction of a blade wax pattern in a wax pattern module according to the appearance of the single crystal superalloy turbine blade; according to the placement positions of the blade wax patterns in the wax pattern module and the three-dimensional directions, analyzing the section mutation positions where mixed crystals possibly appear in the casting process, arranging a wax pattern of a seeding structure at the most tip of each section mutation position, and bonding the blade wax patterns, the wax pattern of the seeding structure and the wax pattern of a pouring system together to obtain a wax pattern module, wherein seed crystals with consistent three-dimensional orientation are arranged at the bottoms of the blade wax patterns and the bottom of the wax pattern of the seeding structure and are connected with a wax pattern of a base; manufacturing a shell type on the basis of the wax mould module; and filling alloy liquid into the shell, and preparing the single crystal superalloy turbine blade in directional solidification equipment. The preparation method has obvious effect of reducing the mixed crystals at the abrupt change of the section, does not need to specially design the seeding structure, and is easy to realize engineering application.
Description
Technical Field
The application relates to the technical field of manufacturing of turbine blades of engines, in particular to a method for preparing a single-crystal superalloy turbine blade.
Background
The high-performance aeroengine turbine blade must work under the conditions of high temperature, high load, high rotation speed, complex stress, gas corrosion and the like, and the service environment is extremely harsh. The monocrystal superalloy is integrally formed by one crystal grain, eliminates the adverse effect of a crystal boundary in a severe service environment, has excellent high-temperature comprehensive performance, and is the preferred material of the turbine blade of the prior high-performance aeroengine.
The single crystal superalloy turbine blade is typically fabricated by a selective crystallization process or a seed crystal process in combination with directional solidification techniques. As shown in FIG. 1, in the seed crystal method, a seed crystal 02 which is formed by single crystal grains and has specific orientation is arranged at the bottom end of a blade shell type 01, the upper end of the seed crystal 02 is connected with a blade part by a process block, and the lower end of the seed crystal 02 is connected with a cooling crystallizer 03. After the blade shell 01 is filled with the alloy liquid 05, the alloy liquid is solidified upwards from the seed crystal to form a solid phase 04 with the three-dimensional orientation of the crystal consistent with that of the seed crystal, and then the single crystal blade formed by single crystal grains is formed.
However, when there is a sudden change in cross-section in the solidification path, the liquid phase at the distal end of the sudden change in cross-section may solidify into a solid phase of random crystal orientation prior to the single crystal growing from the seed crystal, i.e., the individual nucleation solidification region 06, as shown in FIG. 2, continues to solidify and grow so as to form a hetero-crystal of a crystal orientation that is completely different from that of the bulk of the blade, directly affecting the single crystal integrity of the single crystal blade.
In order to avoid the impurity crystals caused by the above conditions, a method for increasing seeding is generally adopted at present to improve the integrity of single crystals. As shown in fig. 3, a seeding structure 07 is introduced into a casting mould, and the position of the casting mould close to the seed crystal 02 is connected with the far end of the section abrupt change position, so that the far end of the section abrupt change is solidified directly upwards from a solid-liquid interface at the seeding position without being singly nucleated; theoretically, the crystallographic orientation in seeding structure 07 is the same as seed 02, allowing the abrupt cross-sectional distal end to achieve the same crystallographic orientation as seed 02. However, because the directional solidification process of the single-crystal superalloy blade is very complex, the seeding structure 07 is designed by fully considering the influences of a liquid-phase flow field, a temperature field, solute diffusion and the like on solidification characteristics, and when the design is incorrect, the alloy orientation obtained by the far-end solidification with abrupt cross section change is easily different from the orientation at the seed crystal 02, and still forms a grain boundary and even generates miscellaneous crystals.
Disclosure of Invention
The application aims to provide a preparation method of a single-crystal superalloy turbine blade, so as to prevent the generation of mixed crystals at the abrupt change position of the blade shell-shaped section in the directional solidification process.
In order to achieve the above purpose, the present application provides the following technical solutions:
a preparation method of a single crystal superalloy turbine blade comprises the following steps:
determining the placement position and the three-dimensional direction of a blade wax pattern in a wax pattern module according to the appearance of a single crystal superalloy turbine blade, wherein the wax pattern module comprises the blade wax pattern, a seeding structure wax pattern connected with the blade wax pattern, a casting system wax pattern and a base wax pattern;
analyzing according to the placement positions and three-dimensional directions of the blade wax patterns in the wax pattern module to obtain section mutation positions where mixed crystals possibly appear in the casting process, arranging the wax pattern with the seeding structure at the most tip of each section mutation position, manufacturing the blade wax patterns, the wax pattern with the seeding structure and the wax pattern with a pouring system, and bonding the blade wax patterns, the wax pattern with the seeding structure to obtain the wax pattern module, wherein the wax pattern module is made of meltable wax;
seed crystals are arranged at the bottoms of the blade wax mould and the seeding structure wax mould, the seed crystals are connected with the base wax mould, the crystal orientation of each seed crystal in a coordinate system formed by the seed crystals is consistent, and the crystal three-dimensional orientation of the whole space coordinate system of the wax mould module is also consistent;
manufacturing a shell on the basis of the wax mould module, melting and removing the meltable wax material, and sintering;
and placing the shell mold in directional solidification equipment, injecting alloy liquid into the shell mold, and then carrying out directional drawing to enable the alloy liquid to be directionally solidified upwards from the seed crystal, and sequentially growing into the single-crystal high-temperature alloy turbine blade with the orientation consistent with the seed crystal.
Optionally, the shell type includes pouring system part, blade part and draws brilliant structure part, draw brilliant structure part to include linkage segment and draw brilliant section, the seed crystal is inlayed and is located in the linkage segment, draw the brilliant section connect in the linkage segment with between the blade part, draw the inner chamber of brilliant section along the linkage segment to the blade part direction is gradually expanded.
Optionally, the outer contour of the junction between the cavity of the seeding section and the cavity of the blade part gradually expands along the direction from the seeding section to the blade part.
Optionally, the shape of the section of the cavity of the seeding section connected with the section abrupt change position perpendicular to the temperature gradient of the directional solidification equipment is the shape of the edge at the connection position of the seeding section and the section abrupt change position.
Optionally, along the direction from the connecting section to the blade part, the die cavity of the seeding section is gradually expanded perpendicular to the outer contour of the cross section of the temperature gradient of the directional solidification equipment.
Optionally, the directional solidification device is a high temperature gradient vacuum directional solidification furnace.
Optionally, the wax pattern module includes a plurality of the blade wax pattern, a plurality of the die-casting structure wax pattern, one the pouring cup wax pattern, a plurality of the pouring gate wax pattern and a plurality of the riser wax pattern, the pouring cup wax pattern is disposed above each of the blade wax patterns, each of the blade wax patterns is connected to each of the blade wax patterns through the pouring gate wax pattern corresponding to each of the blade wax patterns, each of the pouring gate wax pattern and each of the riser wax patterns is connected to each of the blade wax patterns, and the die-casting structure wax pattern corresponding to each of the blade wax patterns is disposed below a connection position corresponding to each of the blade wax patterns and the die-casting structure.
According to the technical scheme, the application discloses a preparation method of a single-crystal superalloy turbine blade, which comprises the following steps: determining the placement position and the three-dimensional direction of a blade wax pattern in a wax pattern module according to the appearance of a single crystal superalloy turbine blade, wherein the wax pattern module comprises the blade wax pattern, a seeding structure wax pattern connected with the blade wax pattern, a casting system wax pattern and a base wax pattern; according to the placement position and three-dimensional direction analysis of the blade wax pattern in the wax pattern module, obtaining the section mutation position where mixed crystals possibly appear in the casting process, arranging a crystal-guiding structure wax pattern at the most tip of each section mutation position, manufacturing the blade wax pattern, the crystal-guiding structure wax pattern and the pouring system wax pattern, and bonding the blade wax pattern, the crystal-guiding structure wax pattern and the pouring system wax pattern together to obtain a wax pattern module, wherein the wax pattern module is made of meltable wax; arranging seed crystals with consistent three-dimensional orientation at the bottom of the leaf wax mould and the bottom of the seeding structure wax mould, connecting the seed crystals with the base wax mould, and keeping consistent crystal orientation of each seed crystal in a coordinate system formed by the seed crystals and consistent crystal three-dimensional orientation in a whole space coordinate system of the wax mould module; manufacturing a shell mold on the basis of a wax mold module, melting and removing the meltable wax material, and sintering the shell mold to enable the shell mold to have proper strength; placing the shell mould in directional solidification equipment, injecting alloy liquid into the shell mould, and then carrying out directional drawing to enable the alloy to be directionally solidified upwards from the seed crystal, and sequentially growing into the single-crystal high-temperature alloy turbine blade with the orientation consistent with the seed crystal.
According to the preparation method of the single crystal superalloy turbine blade, one blade corresponds to a plurality of seed crystals, the three-dimensional orientations of the seed crystals are completely consistent, the most tips of the abrupt change positions of the sections are respectively connected with the seed crystal phases with the completely consistent three-dimensional orientations, the alloy with the consistent orientations can be respectively solidified in the directional solidification process, and finally the whole single crystal blade with the completely consistent three-dimensional orientations is formed, so that the preparation method is simple in process, obvious in effect of reducing the impurity crystals at the abrupt change positions of the sections, free of special design of crystal guiding structures, and easy to realize engineering application.
Drawings
In order to more clearly illustrate the embodiments of the application or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of a prior art seed crystal process for casting single crystal blades;
FIG. 2 is a schematic diagram of a prior art seed crystal process for casting single crystal blades to form a hetero-crystal by separately nucleation and solidification at the distal end of a section abrupt change of the blade shell;
FIG. 3 is a schematic diagram of a prior art method for improving the impurity crystal of a seed crystal cast single crystal blade at a section mutation of a blade shell by adopting a seeding structure;
FIG. 4 is a schematic view of a shell-type and cooling crystallizer used in the method for preparing a single crystal superalloy turbine blade according to an embodiment of the present application;
FIG. 5 is a cross-sectional view taken along the direction A in FIG. 4;
FIG. 6 is a flow chart of a method for preparing a single crystal superalloy turbine blade in accordance with an embodiment of the present application.
In fig. 1 to 3:
01 is a blade shell type; 02 is seed crystal; 03 is a cooling crystallizer; 04 is a solid phase; 05 is alloy liquid; 06 is a single nucleation coagulated region due to abrupt cross-section changes; 07 is a seeding structure;
in fig. 4 and 5:
1 is a shell type; 101 is a blade portion; 102 is a seeding structure; 2 is seed crystal; 3 is a cooling crystallizer; and 4 is alloy liquid.
Detailed Description
The core of the application is to provide a preparation method of a single-crystal superalloy turbine blade, which can avoid the generation of mixed crystals at the abrupt change position of the blade shell section in the directional solidification process.
The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
Referring to fig. 4 to 6, fig. 4 is a schematic diagram of a shell mold and a cooling crystallizer used in a method for preparing a single crystal superalloy turbine blade according to an embodiment of the present application; FIG. 5 is a cross-sectional view taken along the direction A in FIG. 4; FIG. 6 is a flow chart of a method for preparing a single crystal superalloy turbine blade in accordance with an embodiment of the present application.
The embodiment of the application discloses a preparation method of a single-crystal superalloy turbine blade, which comprises the following steps:
s10: determining the placement position and the three-dimensional direction of a blade wax pattern in a wax pattern module according to the appearance of a single crystal superalloy turbine blade, wherein the wax pattern module comprises the blade wax pattern, a seeding structure wax pattern connected with the blade wax pattern, a casting system wax pattern and a base wax pattern;
the pouring system wax mould comprises pouring cup wax moulds, pouring gate wax moulds, riser wax moulds and base wax moulds, the pouring gate wax moulds are arranged according to the quantity of the blade wax moulds in the wax mould module, namely one pouring gate wax mould corresponds to one blade wax mould, one or more blade wax moulds can be arranged in the wax mould module, the blade wax moulds and the single crystal superalloy turbine blade are manufactured according to the proportion of 1:1, the tips of the corresponding abrupt change positions of the sections of each blade wax mould are respectively connected with a plurality of seeding structure wax moulds, the wax mould module can only be provided with one pouring cup wax mould, the pouring cup wax moulds can be connected with all pouring gates, a plurality of pouring cup wax moulds can be arranged, the pouring cup wax moulds are shared by the pouring gate wax moulds, and the riser wax moulds are arranged according to the actual structure of the blade wax moulds.
S20: according to the placement position and three-dimensional direction analysis of the blade wax pattern in the wax pattern module, obtaining the section mutation position where mixed crystals possibly appear in the casting process, arranging a crystal-guiding structure wax pattern at the most tip of each section mutation position, manufacturing the blade wax pattern, the crystal-guiding structure wax pattern and the pouring system wax pattern, and bonding the blade wax pattern, the crystal-guiding structure wax pattern and the pouring system wax pattern together to obtain a wax pattern module, wherein the wax pattern module is made of meltable wax;
it is known that when there is a sudden change in cross section in the solidification path, the liquid phase at the distal end of the sudden change in cross section may solidify before the single crystal grown from the seed crystal 2, forming a hetero crystal with an orientation completely different from that of the blade body, directly affecting the single crystal integrity of the single crystal blade, and therefore, a seeding structure wax pattern is provided at the most distal end of each sudden change in cross section, and the position of the mold close to the seed crystal 2 is connected to the distal end of the sudden change in cross section, so that the distal end of the sudden change in cross section solidifies without nucleation alone, but from the solid-liquid interface at the seeding site. Of course, in addition to the abrupt position of the cross section of the blade, the lower end of the main body portion of the blade wax pattern also needs to be provided with a seeding structure wax pattern.
S30: seed crystals are arranged at the bottoms of the leaf wax mould and the seeding structure wax mould, the seed crystals are connected with the base wax mould, the crystal orientation of each seed crystal is consistent in a coordinate system formed by the seed crystals, and the crystal three-dimensional orientation of the whole space coordinate system of the wax mould module is also consistent;
the seed crystals with consistent three-dimensional orientation refer to the seed crystals with consistent three-dimensional orientation in the space of the whole wax mould module, and the three-dimensional orientation of a single seed crystal is consistent.
S40: and manufacturing a shell mold on the basis of the wax mold module, melting and removing the meltable wax material, and sintering the shell mold 1, wherein the shell mold 1 comprises a blade part 101, a seeding structure part 102 connected with the blade part 101, a casting system part and a base part, and a cavity of the blade part 101 is respectively communicated with a cavity of the seeding structure part 102 and a cavity of the casting system part, and sintering is carried out to ensure that the shell mold 1 has proper strength.
S50: placing the shell in directional solidification equipment, injecting alloy liquid into the shell, and then carrying out directional drawing to enable the alloy liquid to be directionally solidified upwards from a seed crystal, and sequentially growing into a single-crystal high-temperature alloy turbine blade with the orientation consistent with the seed crystal;
placing the shell in directional solidification equipment, and vacuumizing the directional solidification equipment; and then the alloy liquid 4 is filled in the shell type 1 and is kept stand, so that the alloy liquid is directionally pulled after no convection, and the solid-liquid interface position is kept to have high temperature gradient in the process of directional pulling, therefore, the alloy liquid is solidified upwards from the seed crystal 2 in sequence, a single crystal blade formed by single crystal grains with the same orientation as the seed crystal 2 is gradually formed, and finally the shell type is removed to obtain the single crystal high temperature alloy turbine blade.
After the shell 1 is removed, the single-crystal superalloy turbine blade is also required to be inspected, and the surface of the single-crystal superalloy turbine blade is trimmed after the single-crystal superalloy turbine blade is inspected to be qualified; for hollow blades, the core should also be removed.
Compared with the prior art, the preparation method of the single crystal superalloy turbine blade provided by the embodiment of the application adopts one blade to correspond to a plurality of seed crystals 2, the three-dimensional orientation of each seed crystal 2 is completely consistent, the most pointed ends of the abrupt change positions of each section are respectively connected with the seed crystals 2 with the completely consistent three-dimensional orientation, and in the directional solidification process, the single crystal superalloy turbine blade can be respectively solidified into an alloy with the consistent three-dimensional orientation, and finally the whole body with the completely consistent three-dimensional orientation, namely the single crystal blade is formed.
As shown in fig. 4, in the embodiment of the present application, the shell 1 includes a blade portion 101, a seeding structure portion 102 and a pouring system portion (not shown in the figure), the seeding structure portion 102 includes a connection section and a seeding section, the seed crystal 2 is embedded in the connection section, the seeding section is connected between the connection section and the blade portion 101, and an inner cavity of the seeding section gradually expands along a direction from the connection section to the blade portion 101, so that the seeding section gradually transits to the blade portion 101, and a section mutation is reduced.
Preferably, as shown in fig. 4, in the embodiment of the present application, the outer contour at the connection between the cavity of the seeding section and the cavity of the blade part 101 is gradually expanded along the direction from the seeding section to the blade part, so that a step between the cavity of the seeding section and the cavity of the blade part 101 is completely avoided.
Further optimizing the technical scheme, in the embodiment of the application, the shape of the section of the die cavity of the seeding section connected with the section abrupt change position of the blade part, which is perpendicular to the temperature gradient direction of the directional solidification equipment, is the shape of the edge of the connection part of the seeding section and the section abrupt change position.
The cross section of the cavity of the seeding section connected with the main body of the blade part, which is perpendicular to the temperature gradient direction of the directional solidification equipment, is the cross section of the junction of the seeding section and the main body of the blade part, the outer contour of the cross section of the cavity of the seeding section, which is perpendicular to the temperature gradient direction of the directional solidification equipment, is gradually expanded along the direction from the connection section to the blade part 101, and the dendrite growth direction of the monocrystal and the temperature gradient direction of the directional solidification furnace can be the same or different, i.e. the temperature gradient direction of the directional solidification furnace is necessarily the vertical direction, while the dendrite growth direction of the monocrystal is not necessarily the vertical direction.
In the above step S40, manufacturing the shell mold 1 on a module basis includes:
the ceramic slurry is coated on the outer surface of the module, a ceramic slurry layer is formed after drying treatment, the ceramic slurry can be coated for multiple times, and after each coating is coated with one layer of drying treatment, the next coating is coated.
And heating and melting the removing module, and sintering the ceramic slurry layer to form the shell 1.
In the above step S60, removing the shell 1 includes:
placing the single-crystal superalloy turbine blade with the shell 1 into an autoclave;
pouring the prefabricated alkali liquor into an autoclave, and heating and pressurizing for preset time;
and taking out the single crystal superalloy turbine blade for cleaning.
When preparing hollow blades, the internal ceramic core should also be removed.
Preferably, in the embodiment of the present application, the directional solidification device is a high temperature gradient vacuum directional solidification furnace.
In the embodiment of the application, the die set comprises a plurality of blade wax dies, a plurality of seeding structure wax dies, a pouring cup, a plurality of pouring gates and a plurality of riser heads, wherein the pouring cup is arranged above each blade wax die, the pouring cup is connected with each blade wax die through the pouring gate corresponding to each blade wax die one by one, each pouring gate and each riser head are respectively connected with each blade wax die, and the seeding structure wax die corresponding to each blade wax die one by one is arranged below the blade wax die. In the description of embodiments of the application, "plurality" means two or more than two.
It should be noted that, in the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described as different from other embodiments, and identical and similar parts between the embodiments are all enough to be referred to each other.
If a flowchart is used in the present application, the flowchart is used to describe the operations performed by a system according to an embodiment of the present application. It should be appreciated that the preceding or following operations are not necessarily performed in order precisely. Rather, the steps may be processed in reverse order or simultaneously. Also, other operations may be added to or removed from these processes.
The principles and embodiments of the present application have been described herein with reference to specific examples, the description of which is intended only to facilitate an understanding of the core concepts of the application. It should be noted that it will be apparent to those skilled in the art that various modifications and adaptations of the application can be made without departing from the principles of the application and these modifications and adaptations are intended to be within the scope of the application as defined in the following claims.
Claims (7)
1. A preparation method of a single crystal superalloy turbine blade is characterized by comprising the following steps:
determining the placement position and the three-dimensional direction of a blade wax pattern in a wax pattern module according to the appearance of a single crystal superalloy turbine blade, wherein the wax pattern module comprises the blade wax pattern, a seeding structure wax pattern connected with the blade wax pattern, a casting system wax pattern and a base wax pattern;
analyzing according to the placement positions and three-dimensional directions of the blade wax patterns in the wax pattern module to obtain section mutation positions where mixed crystals possibly appear in the casting process, arranging the wax pattern with the seeding structure at the most tip of each section mutation position, manufacturing the blade wax patterns, the wax pattern with the seeding structure and the wax pattern with a pouring system, and bonding the blade wax patterns, the wax pattern with the seeding structure to obtain the wax pattern module, wherein the wax pattern module is made of meltable wax;
seed crystals are arranged at the bottoms of the blade wax mould and the seeding structure wax mould, the seed crystals are connected with the base wax mould, the crystal orientation of each seed crystal in a coordinate system formed by the seed crystals is consistent, and the crystal three-dimensional orientation of the whole space coordinate system of the wax mould module is also consistent;
manufacturing a shell on the basis of the wax mould module, melting and removing the meltable wax material, and sintering;
and placing the shell mold in directional solidification equipment, injecting alloy liquid into the shell mold, and then carrying out directional drawing to enable the alloy liquid to be directionally solidified upwards from the seed crystal, and sequentially growing into the single-crystal high-temperature alloy turbine blade with the orientation consistent with the seed crystal.
2. The method for preparing a single crystal superalloy turbine blade according to claim 1, wherein the shell comprises a casting system part, a blade part and a seeding structure part, the seeding structure part comprises a connecting section and a seeding section, the seed crystal is embedded in the connecting section, the seeding section is connected between the connecting section and the blade part, and the inner cavity of the seeding section gradually expands along the direction from the connecting section to the blade part.
3. The method for producing a single crystal superalloy turbine blade according to claim 2, wherein the outer contour of the junction of the die cavity of the seeding section and the die cavity of the blade section gradually expands in the direction from the seeding section to the blade section.
4. The method for producing a single crystal superalloy turbine blade according to claim 2, wherein the shape of the section of the cavity of the seeding section connected to the abrupt cross-section position perpendicular to the temperature gradient direction of the directional solidification equipment is the shape of the edge at the connection of the seeding section and the abrupt cross-section position.
5. The method for producing a single crystal superalloy turbine blade according to claim 2, wherein the die cavity of the seeding section is gradually widened along the direction from the connecting section to the blade section, perpendicular to the outer contour of the cross section in the direction of the temperature gradient of the directional solidification apparatus.
6. The method for producing a single crystal superalloy turbine blade according to any of claims 1 to 4, wherein the directional solidification equipment is a high temperature gradient vacuum directional solidification furnace.
7. The method according to any one of claims 1 to 4, wherein the wax pattern module comprises a plurality of the blade wax patterns, a plurality of the seeding structure wax patterns, one pouring cup wax pattern, a plurality of the pouring gate wax patterns and a plurality of the riser wax patterns, the pouring cup wax pattern is disposed above each of the blade wax patterns, the pouring cup wax patterns are connected to each of the blade wax patterns through the pouring gate wax patterns corresponding to each of the blade wax patterns one by one, each of the pouring gate wax patterns and each of the riser wax patterns are connected to each of the blade wax patterns, and the seeding structure wax patterns corresponding to each of the blade wax patterns one by one are disposed below the connection positions of the blade wax patterns corresponding to the seeding structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310635697.9A CN116833391A (en) | 2023-05-31 | 2023-05-31 | Preparation method of single-crystal superalloy turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310635697.9A CN116833391A (en) | 2023-05-31 | 2023-05-31 | Preparation method of single-crystal superalloy turbine blade |
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| Publication Number | Publication Date |
|---|---|
| CN116833391A true CN116833391A (en) | 2023-10-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310635697.9A Pending CN116833391A (en) | 2023-05-31 | 2023-05-31 | Preparation method of single-crystal superalloy turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116833391A (en) |
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- 2023-05-31 CN CN202310635697.9A patent/CN116833391A/en active Pending
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