CN119407107A - A single crystal high temperature alloy turbine blade shell and preparation method thereof - Google Patents
A single crystal high temperature alloy turbine blade shell and preparation method thereof Download PDFInfo
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- CN119407107A CN119407107A CN202411528612.8A CN202411528612A CN119407107A CN 119407107 A CN119407107 A CN 119407107A CN 202411528612 A CN202411528612 A CN 202411528612A CN 119407107 A CN119407107 A CN 119407107A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/08—Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
- B22C9/082—Sprues, pouring cups
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
- B22C7/02—Lost patterns
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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Abstract
The invention relates to the technical field of turbine blades, in particular to a monocrystalline superalloy turbine blade shell and a preparation method thereof, wherein the shell comprises a pouring cup, a sprue, a runner, a slag collecting groove, a seed crystal cavity and a seed crystal growth cavity; the two ends of the sprue are respectively connected with the pouring cup and the sprue, the seed crystal cavity is perpendicular to the inlet channel of the slag collecting groove at the other end of the sprue and is positioned below the seed crystal growth cavity, and the seed crystal growth cavity is respectively communicated with the seed crystal cavity, the slag collecting groove and the sprue. The seed crystal setting mode eliminates the gap between the seed crystal and the seed crystal cavity, and avoids seeding defects caused by the existence of the gap. And the length of the pasty area of the seed crystal is obviously reduced by designing the pouring channel structure and the slag collecting groove, so that the seeding defect in the seeding process of the seed crystal is avoided as much as possible.
Description
Technical Field
The invention relates to the technical field of turbine blades, in particular to a monocrystalline superalloy turbine blade shell and a preparation method thereof.
Background
Single crystal superalloys have many advantages such as excellent high temperature strength, oxidation resistance, creep resistance, and the like. Under high temperature environment, single crystal superalloy can maintain high strength and stability, and therefore is widely used in the manufacture of turbine blades for aeroengines and gas turbines.
Directional solidification techniques are required in the manufacture of single crystal superalloy turbine blades. The method comprises the steps of realizing directional solidification, pouring alloy liquid into a shell, and solidifying the alloy liquid along a certain direction through a specific directional solidification process, so as to obtain the turbine blade with a single grain structure. In the preparation of single crystals by directional solidification, seeding is first required so that only one crystal grain enters the cavity, on the basis of which the crystal slowly grows gradually into a single crystal blade composed of one crystal grain. Among them, seed crystal is a seeding method commonly used for preparing single crystal turbine blades.
In the prior art, for convenience in placing the seed crystal into the mold shell, a certain gap exists between the seed crystal and the seed crystal cavity. Numerous studies have shown that the gap between the seed crystal and the seed cavity is one of the main causes of seeding failure. In addition, since the seed crystal at the lower part of the shell is kept in a solid state due to the lower temperature before the casting of the alloy liquid, the upper part of the seed crystal is melted into a liquid state by the high temperature, and a transition area, namely a pasty area exists between the melted and unmelted parts. In the transition region, crystal nuclei are liable to occur, resulting in failure of seeding of the single crystal due to defects of the blade crystal.
Therefore, how to improve the success rate of single crystal seeding when preparing single crystal blades is a technical problem that needs to be solved currently.
Disclosure of Invention
The invention aims to provide a monocrystalline superalloy turbine blade shell and a preparation method thereof, which are used for solving the technical problems.
The invention provides a single crystal superalloy turbine blade shell, which comprises a pouring cup, a sprue, a runner, a slag collecting groove, a seed crystal cavity and a seed crystal growth cavity, wherein the pouring cup is arranged on the pouring cup;
The two ends of the sprue are respectively connected with the pouring cup and the sprue, the seed crystal cavity is perpendicular to the inlet channel of the slag collecting groove at the other end of the sprue and is positioned below the seed crystal growth cavity, and the seed crystal growth cavity is respectively communicated with the seed crystal cavity, the slag collecting groove and the sprue.
The invention also provides a preparation method of the single crystal superalloy turbine blade shell, which comprises the following steps:
determining the length of a seed crystal flushing section and the length L of a seed crystal completely non-melting section according to the size of a turbine blade of the single crystal superalloy and the thermophysical parameters of the casting alloy;
Determining the cavity structure of the single crystal superalloy turbine blade shell according to the length of the seed crystal flushing section;
placing seed crystals on a chassis, and preparing a wax pattern;
and (3) based on a cavity structure, carrying out shell coating, dewaxing and sintering on the monocrystalline wax mould with the seed crystal to obtain the monocrystalline superalloy turbine blade shell.
The invention also provides application of the single-crystal superalloy turbine blade shell in an aeroengine and a gas turbine.
The invention has the technical effects and advantages that:
The invention discloses a single-crystal superalloy turbine blade shell which comprises a pouring cup, a sprue, a cross runner, a slag collecting groove, a seed crystal cavity and a seed crystal growth cavity, wherein two ends of the sprue are respectively connected with the pouring cup and the cross runner, the seed crystal cavity is perpendicular to the other end of the cross runner and an inlet channel of the slag collecting groove and is positioned below the seed crystal growth cavity, and the seed crystal growth cavity is respectively communicated with the seed crystal cavity, the slag collecting groove and the cross runner.
The seed crystal setting mode eliminates the gap between the seed crystal and the seed crystal cavity (the cavity is formed by the cavity of the mold shell, and the seed crystal cavity is a part of the cavity), and avoids the seeding defect caused by the existence of the gap. And the length of the pasty area of the seed crystal is obviously reduced by designing the pouring channel structure and the slag collecting groove, so that the seeding defect in the seeding process of the seed crystal is avoided as much as possible.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art. FIG. 1 is a schematic illustration of a single crystal superalloy turbine blade shell structure;
the reference numerals comprise a 1-pouring cup, a 2-straight pouring gate, a 3-transverse pouring gate, a 4-slag collecting tank, a 5-seed crystal and a 6-seed crystal growth cavity.
Detailed Description
The following description of the embodiments of the present invention 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 invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that, the structures, proportions, sizes and the like shown in the drawings attached to the present specification are used for understanding and reading only in conjunction with the disclosure of the present specification, and are not intended to limit the applicable limitations of the present invention, so that any modification of the structures, variation of proportions or adjustment of sizes of the structures, proportions and the like should not be construed as essential to the present invention, and should still fall within the scope of the disclosure of the present invention without affecting the efficacy and achievement of the present invention. Also, the terms such as "upper," "lower," "left," "right," "middle," and "a" and the like recited in the present specification are merely for descriptive purposes and are not intended to limit the scope of the invention, but are intended to provide relative positional changes or modifications without materially altering the technical context in which the invention may be practiced.
In order to solve the defects in the prior art, the invention discloses a single-crystal superalloy turbine blade shell, which comprises a pouring cup 1, a sprue 2, a runner 3, a slag collecting groove 4, a seed crystal cavity and a seed crystal growth cavity 6 as shown in figure 1.
The two ends of the sprue 2 are respectively connected with the sprue cup 1 and the sprue 3, the seed crystal cavity is perpendicular to the other end of the sprue 3 and the inlet channel of the slag collecting tank 4 and is positioned below the seed crystal growth cavity 6, and the seed crystal growth cavity 6 is respectively communicated with the seed crystal cavity, the slag collecting tank 4 and the sprue 3.
The sprue 2 adopts a taper with a smaller lower part and a larger upper part, and the taper is 1-3 degrees.
Wherein the cross runner 3 has a smaller cross-sectional area than the small end of the sprue 2.
Wherein, the slag collecting groove 4 receives molten metal with broken dendrites, the dendrites after breaking are prevented from forming a crystallization core, and the volume of the slag collecting groove 4 is 10 times larger than that of the flushing section of the seed crystal 5.
The diameter of the inlet channel of the slag collecting groove 4 is larger than that of the cross gate 3, the length of the inlet channel is larger than or equal to that of the inlet channel, and the diameter of the inner cavity of the slag collecting groove 4 is 10-20mm and the height is 15-25mm.
Wherein, the distance L between the seed crystal growth cavity 6 and the bottom surface of the single crystal superalloy turbine blade shell is the length of the seed crystal 5 without melting the segment completely.
The invention also provides a preparation method of the single crystal superalloy turbine blade shell, which comprises the following steps:
1. and determining the length of a flushing section of the seed crystal 5 and the length L of a section of the seed crystal 5 which is not melted completely according to the size of the turbine blade of the single crystal superalloy and the thermophysical parameters of the casting alloy.
The method specifically comprises the steps of determining the length L of the completely non-melting section of the seed crystal 5 according to the thermophysical parameters of the casting alloy, determining the length of the seed crystal according to the size of the turbine blade of the single crystal superalloy, and determining the length of the flushing section of the seed crystal 5 according to the length of the seed crystal and the length L of the completely non-melting section of the seed crystal 5.
Wherein the length L of the completely unmelted segment of the seed crystal 5 is determined by the following formula;
Where T 0 is room temperature, T S is solidus, and f (G) T is a temperature gradient function with respect to temperature in the seed crystal.
2. And determining the cavity structure of the single crystal superalloy turbine blade shell according to the length of the flushing section of the seed crystal 5.
The method specifically comprises the steps of calculating kinetic energy required to be generated when the alloy is poured according to the length of a flushing section of the seed crystal 5, and determining the size and position information of the slag collecting groove 4, the sprue 2 and the runner 3 according to the kinetic energy required to be generated when the alloy is poured.
3. A seed crystal 5 is placed on the base plate and a wax pattern is prepared.
4. And (3) based on a cavity structure, carrying out shell coating, dewaxing and sintering on the monocrystalline wax mould with the seed crystal 5 to obtain the monocrystalline superalloy turbine blade shell.
The method specifically comprises the steps of preparing seed crystals according to the diameter of the seed crystals required by preparing the single crystal superalloy turbine blade, and preparing a wax pattern and a mold shell. And a seed crystal is put in the process of preparing the wax mould, so that no gap exists between the side surface of the seed crystal and a seed crystal cavity of a subsequently formed mould shell. And then the monocrystalline wax mould with the seed crystal is subjected to shell coating, dewaxing and sintering to obtain the monocrystalline shell with the seed crystal.
It should be noted that specific steps in the process for preparing the single crystal superalloy turbine blade shell, such as shell coating, dewaxing, sintering, etc., are all prior art, and are not described herein too much, and detailed reference is made to application number 201410742333.1.
The invention also provides application of the single-crystal superalloy turbine blade shell in an aeroengine and a gas turbine.
In order to eliminate the fit clearance between the seed crystal and the seed crystal cavity, the seed crystal can be put in the process of preparing the wax mould before the coating, and then the single crystal wax mould with the seed crystal is subjected to shell coating, dewaxing and sintering, so that no clearance exists between the shell surrounding the seed crystal and the seed crystal in the directional solidification process, and dendrite nucleation caused by filling of alloy liquid due to existence of the clearance in the prior art is avoided.
Meanwhile, when the seed crystal is adopted to prepare the single crystal blade, the structure such as a sprue, a cross runner and a slag collecting groove is designed to enable the casting metal liquid to have kinetic energy capable of flushing away a flushing section of the seed crystal, so that a back melting pasty area of the seed crystal is reduced or even removed, a relatively flat solid-liquid interface is formed by enabling the length of the pasty area between an unmelted part of the seed crystal and the casting alloy liquid to be as small as possible, and dendrite growth is carried out on the basis of the interface by directional solidification, thereby obtaining a good seeding effect.
In order to better explain the present solution, the following examples are also provided.
Examples
A method for preparing a shell of a DD6 alloy blade, which comprises the following steps:
The blade has a directional solidification temperature lower than 1500 ℃ due to the weakness of the core and the like, and the unmelted length of the seed crystal is 10mm as calculated by the previous formula.
The diameter of the seed crystal is 2mm according to the size of the blade, the seed length is 15mm. And the seed crystal is put in when the wax mould is prepared, so that no gap exists between the side surface of the seed crystal and the seed crystal cavity of the shell formed later. And then the monocrystalline wax mould with the seed crystal is subjected to shell coating, dewaxing and sintering to obtain the monocrystalline shell mould with the seed crystal.
In order to obtain enough kinetic energy, the proportion of the cavity structure near the seed crystal is set according to the following conditions that, for example, the diameter of a slag collecting groove 4 is 12mm, the height is 20mm, the diameter of an inlet channel of the slag collecting groove is 4mm, the length of the inlet channel is 4mm, the diameter of a cross runner 3 is 3mm, the length of the inlet channel is 4.5mm, the diameter of the small end of a straight runner 2 is 5mm, and the taper of the straight runner is 1 DEG with a smaller lower taper and a larger upper taper.
In the preparation process of the blade, most of pasty areas are eliminated in the casting process by the design of a seeding structure, and a relatively flat solid-liquid interface is formed in the seed crystal. And carrying out dendritic crystal growth on the basis of the interface by directional solidification, thereby obtaining good seeding effect. Meanwhile, the slag collecting groove 4 is used for receiving molten metal with broken dendrites, so that the broken dendrites are prevented from forming a crystallization core. 410 blades are prepared by adopting the seeding mode, and the seeding success rate is more than 97%.
It should be noted that the foregoing description is only a preferred embodiment of the present invention, and although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood that modifications, equivalents, improvements and modifications to the technical solution described in the foregoing embodiments may occur to those skilled in the art, and all modifications, equivalents, and improvements are intended to be included within the spirit and principle of the present invention.
Claims (12)
1. The single crystal superalloy turbine blade shell is characterized by comprising a pouring cup (1), a sprue (2), a runner (3), a slag collecting groove (4), a seed crystal cavity and a seed crystal growth cavity (6);
The two ends of the straight pouring gate (2) are respectively connected with the pouring cup (1) and the transverse pouring gate (3), the seed crystal cavity is perpendicular to the inlet channel of the slag collecting groove (4) at the other end of the transverse pouring gate (3) and is positioned below the seed crystal growth cavity (6), and the seed crystal growth cavity (6) is respectively communicated with the seed crystal cavity, the slag collecting groove (4) and the transverse pouring gate (3).
2. The single crystal superalloy turbine blade shell according to claim 1, characterised in that the two ends of the sprue (2) are of different conicity;
wherein, one end of the sprue (2) connected with the cross gate (3) is a small taper end.
3. The single crystal superalloy turbine blade shell as in claim 2, wherein the taper is in the range of 1 ° to 3 °.
4. The single crystal superalloy turbine blade shell as in claim 2 wherein the cross-sectional area of the runner (3) is smaller than the cross-sectional area of the small taper end of the sprue (2).
5. The single crystal superalloy turbine blade shell according to claim 1, characterised in that the volume of the slag trap (4) is larger than 10 times the volume of the flushing section of the seed crystal (5);
The seed crystal cavity divides the seed crystal into two sections, the outer section of the cavity is a seed crystal flushing section, and the inner section of the cavity is a seed crystal completely non-melting section.
6. The single-crystal superalloy turbine blade shell according to claim 1, wherein the diameter of the inlet channel of the slag collecting tank (4) is larger than the diameter of the runner (3), the length of the inlet channel is larger than or equal to the diameter of the inlet channel, and the diameter of the inner cavity of the slag collecting tank (4) is 10-20mm and the height is 15-25mm.
7. The single crystal superalloy turbine blade shell according to claim 1, wherein the seed crystal growth chamber (6) is at a distance L from the bottom surface of the single crystal superalloy turbine blade shell of the length of the seed crystal (5) that is completely unmelted.
8. A method of manufacturing a single crystal superalloy turbine blade shell based on any of claims 1 to 7 comprising:
determining the length of a seed crystal flushing section and the length L of a seed crystal completely non-melting section according to the size of a turbine blade of the single crystal superalloy and the thermophysical parameters of the casting alloy;
Determining the cavity structure of the single crystal superalloy turbine blade shell according to the length of the seed crystal flushing section;
placing seed crystals on a chassis, and preparing a wax pattern;
and (3) based on a cavity structure, carrying out shell coating, dewaxing and sintering on the monocrystalline wax mould with the seed crystal to obtain the monocrystalline superalloy turbine blade shell.
9. The method of claim 8 wherein determining the length of the seed flushing segment and the length L of the seed completely unmelted segment based on the single crystal superalloy turbine blade size and the thermophysical parameters of the cast alloy comprises:
determining the length L of the completely non-melting section of the seed crystal according to the thermophysical parameters of the casting alloy;
Determining the length of seed crystals according to the size of the single-crystal superalloy turbine blade;
and determining the length of the seed crystal flushing section according to the length of the seed crystal and the length L of the seed crystal completely unmelted section.
10. The method of claim 9 wherein the length L of the seed crystal completely unmelted segment is determined by the formula;
Where T 0 is room temperature, T S is solidus, and f (G) T is a temperature gradient function with respect to temperature in the seed crystal.
11. The method of claim 8, wherein determining a cavity configuration of the single crystal superalloy turbine blade shell based on the seed flushing segment length comprises:
Calculating kinetic energy required to be generated when casting alloy according to the length of the seed crystal flushing section;
and determining the size and position information of the slag collecting groove, the sprue and the cross runner according to the kinetic energy required to be generated when the alloy is poured.
12. Use of a single crystal superalloy turbine blade shell according to any of the claims 1-7 for an aircraft engine and a gas turbine.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202411528612.8A CN119407107A (en) | 2024-10-30 | 2024-10-30 | A single crystal high temperature alloy turbine blade shell and preparation method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202411528612.8A CN119407107A (en) | 2024-10-30 | 2024-10-30 | A single crystal high temperature alloy turbine blade shell and preparation method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119703021A (en) * | 2025-02-17 | 2025-03-28 | 中国航发北京航空材料研究院 | A method for preparing single crystal high temperature alloy blades using seed crystals |
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