CN114737084A - High-strength creep-resistant high-temperature alloy and preparation method thereof - Google Patents
High-strength creep-resistant high-temperature alloy and preparation method thereof Download PDFInfo
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/002—Hybrid process, e.g. forging following casting
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22B—PRODUCTION AND REFINING OF METALS; PRETREATMENT OF RAW MATERIALS
- C22B9/00—General processes of refining or remelting of metals; Apparatus for electroslag or arc remelting of metals
- C22B9/04—Refining by applying a vacuum
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
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- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/0433—Nickel- or cobalt-based alloys
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
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- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention provides a high-strength creep-resistant high-temperature alloy and a preparation method thereof, belonging to the technical field of metallurgy. The alloy comprises the following components in percentage by mass: cr: 10.00% -12.00%, Co: 12.00% -18.00%, W: 5.50% -7.50%, Mo: 1.50% -3.50%, Al: 3.00% -4.20%, Ti: 3.00% -4.20%, Nb: 1.00% -2.20%, Ta: 0.40% -1.50%, C: 0.01% -0.04%, B: 0.01% -0.04%, Zr: 0.09% -1.20%, Hf is less than 0.10%, and the balance is Ni, wherein the gamma' phase forming elements Al, Ti, Nb and Ta in the high-temperature alloy comprise the following components in percentage by mass: 9.5 percent to 10.3 percent (Al + Ti + Nb + Ta); the mass percentage content of the gamma' phase in the high-temperature alloy is 50% -55%; the mass ratio of Al to Ti in the high-temperature alloy is as follows: 0.9-1.0 (Al/Ti). The method can prepare the alloy and the disc part thereof. The disk part of the alloy can meet the requirements of future aviation turboshaft engines on high temperature resistance, high strength and creep resistance.
Description
Technical Field
The invention relates to the technical field of metallurgy, in particular to a high-strength creep-resistant high-temperature alloy and a preparation method thereof.
Background
Powder disks are one of the most critical, most core, hot end components of aircraft engines. The gradual improvement of the performance of the engine requires that the turbine disc material has good comprehensive mechanical properties. Since the powder superalloy has the advantages of uniform structure, fine crystal grains, high yield strength, good fatigue performance and the like, the powder superalloy is successfully applied to a plurality of high-performance engines. However, the prior art alloys have difficulty meeting the technical requirements of the aviation turboshaft engine.
Disclosure of Invention
In view of the above, the invention provides a high-strength creep-resistant high-temperature alloy and a preparation method thereof, and the high-strength creep-resistant high-temperature alloy prepared by the preparation method can meet the requirements of future aviation turboshaft engines on high temperature resistance, high strength and creep resistance, so that the high-strength creep-resistant high-temperature alloy is more practical.
In order to achieve the first object, the technical scheme of the high-strength creep-resistant superalloy provided by the invention is as follows:
the invention provides a high-strength creep-resistant high-temperature alloy which comprises the following components in percentage by mass: cr: 10.00% -12.00%, Co: 12.00% -18.00%, W: 5.50% -7.50%, Mo: 1.50% -3.50%, Al: 3.00% -4.20%, Ti: 3.00% -4.20%, Nb: 1.00% -2.20%, Ta: 0.40% -1.50%, C: 0.01% -0.04%, B: 0.01% -0.04%, Zr: 0.09-1.20 percent of Hf is less than 0.10 percent, and the balance is Ni, wherein,
in the high-strength creep-resistant high-temperature alloy, the total mass percentage of gamma' phase forming elements Al, Ti, Nb and Ta is as follows: 9.5 percent to 10.3 percent (Al + Ti + Nb + Ta); the mass percentage content of the gamma' phase in the high-strength creep-resistant high-temperature alloy is 50-55%;
the mass ratio of Al to Ti in the high-strength creep-resistant high-temperature alloy is as follows: 0.9 to 1.0 of (Al/Ti).
The high-strength creep-resistant high-temperature alloy provided by the invention can be further realized by adopting the following technical measures.
Preferably, the tensile strength of the high-strength creep-resistant superalloy disc is higher than 1650MPa at room temperature, and the tensile strength of the high-strength creep-resistant superalloy disc is higher than 1400MPa at 700 ℃.
Preferably, the high strength creep-resistant superalloy disc has a specific strength at room temperature of greater than 0.2Nm/kg and the high strength creep-resistant superalloy disc has a specific strength at 700 ℃ of greater than 0.16 Nm/kg.
Preferably, the service life of the high-strength creep-resistant superalloy disc piece is not less than 350h when the creep residual strain reaches 0.2% under the conditions of 704 ℃ and 690 MPa.
Preferably, the high strength creep resistant superalloy has a disk grain size of grade ASTM9-ASTM12 as specified in GB/T6394.
In order to achieve the second object, the technical scheme of the preparation method of the high-strength creep-resistant high-temperature alloy provided by the invention is as follows:
the preparation method of the high-strength creep-resistant high-temperature alloy provided by the invention comprises the following steps:
obtaining an original additive of the high-strength creep-resistant high-temperature alloy, wherein the original additive comprises the following components in percentage by mass: cr: 10.00% -12.00%, Co: 12.00% -18.00%, W: 5.50% -7.50%, Mo: 1.50% -3.50%, Al: 3.00% -4.20%, Ti: 3.00% -4.20%, Nb: 1.00% -2.20%, Ta: 0.40% -1.50%, C: 0.01% -0.04%, B: 0.01% -0.04%, Zr: 0.09-1.20 percent of Ni, less than 0.10 percent of Hf, and the balance of Ni; wherein the gamma' phase forming elements Al, Ti, Nb and Ta in the high-strength creep-resistant high-temperature alloy comprise the following components in percentage by mass: 9.5 percent to 10.3 percent (Al + Ti + Nb + Ta); the gamma' phase in the high-strength creep-resistant high-temperature alloy is 50-55% by mass; the mass ratio of Al to Ti in the high-strength creep-resistant high-temperature alloy is as follows: 0.9-1.0 (Al/Ti);
and carrying out vacuum induction melting on the original additive of the high-strength creep-resistant high-temperature alloy to prepare a master alloy ingot of the high-strength creep-resistant high-temperature alloy, wherein the melting temperature is 1500-1600 ℃, and the melting vacuum degree is 0.1-0.5 Pa.
The preparation method of the high-strength creep-resistant high-temperature alloy provided by the invention can be further realized by adopting the following technical measures.
Preferably, the preparation method of the alloy powder of the high-strength creep-resistant superalloy further comprises the following steps:
and (3) preparing the alloy powder of the high-strength creep-resistant high-temperature alloy by using the bar of the high-strength creep-resistant powder high-temperature alloy through an argon atomization powder preparation process.
Preferably, the preparation method of the high-strength creep-resistant superalloy disc piece further comprises the following steps:
the alloy powder is subjected to vacuum dynamic degassing at 300-400 ℃, and the vacuum degree is less than 3 multiplied by 10-1Pa, then putting the powder sheath into a powder sheath and sealing and welding to obtain an alloy powder sheath after sealing and welding;
compacting and forming the sealed and welded alloy powder sheath to obtain a compact ingot blank;
and carrying out post-treatment on the compact ingot blank to obtain the high-strength creep-resistant high-temperature alloy disc.
Preferably, in the step of obtaining the compact ingot blank by performing densification forming on the sealed and welded alloy powder sheath, the densification forming method is hot isostatic pressing, the hot isostatic pressing temperature is 1120-1180 ℃, and the hot isostatic pressing pressure is not less than 97 MPa.
Preferably, in the step of obtaining the disc of the high-strength creep-resistant superalloy by post-processing the dense ingot blank, the post-processing method specifically comprises the following steps:
carrying out hot isostatic pressing on the compact ingot blank to obtain a high-temperature alloy bar;
isothermal forging is carried out on the high-temperature alloy bar to obtain a disc-shaped piece, wherein the isothermal forging temperature is 1050-1150 ℃, and the isothermal forging deformation rate is 0.1-0.4 mm/s;
and carrying out solution heat treatment on the disc-shaped piece to obtain the high-strength creep-resistant high-temperature alloy disc-shaped piece, wherein the solution heat treatment temperature is 1100-1140 ℃, and the solution heat treatment time is 2-4 h.
Preferably, during the step of performing surface modification treatment on the alloy powder in the sheath and then sealing and welding to obtain the sealed and welded alloy powder sheath, the alloy powder is sieved to 53-105 μm before being filled in the sheath.
The high-strength creep-resistant high-temperature alloy prepared by the preparation method of the high-strength creep-resistant high-temperature alloy provided by the invention has the following advantages:
(1) the gamma' phase forming elements Al, Ti, Nb and Ta in the powder superalloy have the following total mass fractions: 9.5 percent to 10.3 percent of (Al + Ti + Nb + Ta), and the higher total content of the gamma ' phase forming elements can ensure that the content of the gamma ' phase in the alloy reaches more than 50 percent, and improve the barrier effect of the gamma ' relative dislocation motion, thereby improving the strength level and the creep resistance of the alloy;
(2) the content of the W element in the powder high-temperature alloy is increased to 5.5-7.5%, and the high W content can improve the temperature bearing capacity of the alloy on one hand, so that the alloy can be used for a long time within the temperature range of 700-800 ℃; on the other hand, the lattice distortion of the matrix can be increased, and the solid solution strengthening effect of the alloy is improved, so that the creep resistance of the alloy is obviously improved;
(3) the preparation method of the high-strength creep-resistant powder high-temperature alloy can ensure the metallurgical quality of the powder high-temperature alloy and realize the precise regulation and control of the grain size of the alloy, thereby ensuring the optimal comprehensive mechanical property of the alloy;
(4) compared with FGH95 and FGH96 alloys, the high-strength creep-resistant powder high-temperature alloy prepared by the preparation method can obtain the highest strength level of 650-750 ℃ and the optimal creep property under the condition of 704 ℃/690 MPa.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a schematic metallographic microstructure of a high-strength creep-resistant superalloy provided by an embodiment of the present invention;
FIG. 2 is a schematic metallographic microstructure of an FGH95 alloy;
FIG. 3 is a schematic metallographic microstructure of an FGH96 alloy;
FIG. 4 is a schematic metallographic microstructure of an FGH720Li alloy.
Detailed Description
In view of the above, the invention provides a high-strength creep-resistant high-temperature alloy and a preparation method thereof, and the high-strength creep-resistant high-temperature alloy prepared by the preparation method can meet the requirements of future aviation turboshaft engines on high temperature resistance, high strength and creep resistance, so that the high-strength creep-resistant high-temperature alloy is more practical.
To further illustrate the technical means and effects of the present invention adopted to achieve the predetermined objects, the following detailed description of the high strength creep resistant superalloy and the preparation method thereof according to the present invention, the specific implementation manner, structure, characteristics and effects thereof are provided with reference to the accompanying drawings and preferred embodiments. In the following description, different "one embodiment" or "an embodiment" refers to not necessarily the same embodiment. Furthermore, the particular features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
The term "and/or" herein is merely an association describing an associated object, meaning that three relationships may exist, e.g., a and/or B, with the specific understanding that: both a and B may be contained, a may be present alone, or B may be present alone, and any of the three cases described above may be provided.
The inventor finds out that:
along with the improvement of the power-weight ratio of the turboshaft engine, the temperature of the inlet of the turbine is continuously improved, the design temperature of the disk edge of the turbine of the fifth-generation military turboshaft engine reaches more than 750 ℃, the disk edge temperature level of the turboshaft engine with the power-weight ratio of 14-15 is further improved, and thus higher requirements are provided for the temperature bearing capacity of materials. The temperature bearing capacity of the FGH95 alloy and the FGH720Li alloy which are widely applied to turboshaft engines at present cannot reach 750 ℃, and the requirement of advanced aeroengines cannot be met.
The turbine disc of the turboshaft engine has the characteristics of high rotating speed, high stress level, small notch radius and the like, and the turbine disc material is required to have higher strength and notch sensitivity resistance. The temperature bearing capacity of the FGH96 alloy can reach 750 ℃, but the strength level of the alloy is low, and the alloy cannot meet the requirement of the next generation of turboshaft engine on high strength.
The turbine disc is used as a core component of the aircraft engine and is subjected to high-temperature and high-stress service conditions, but the high-temperature and high-stress state can reach the maximum value only in the process of starting or stopping the engine, and the general duration time is only 3-5 minutes. However, as aircraft have evolved, higher demands have been placed on flight speed and maneuverability, which has resulted in engines that are also required to maintain high temperature, high stress conditions while cruising, typically for hours rather than just minutes. The high-temperature alloy is in service at high temperature and high stress for a long time, and serious creep deformation is inevitably caused, so the creep-resistant alloy gradually becomes the design direction of the powder high-temperature alloy.
In conclusion, the prior FGH95 alloy, FGH96 alloy, FGH720Li alloy and the like in China cannot meet the requirements of high temperature resistance, high strength and creep resistance of future aviation turboshaft engines, so that a novel powder high-temperature alloy with more excellent comprehensive performance needs to be designed in a targeted manner, and the alloy can meet the requirements of high strength of the disk center part of the turbine disk and creep resistance of the disk edge part.
On one hand, the invention designs a high-strength creep-resistant powder high-temperature alloy used at the temperature of more than 750 ℃ based on the nano phase transformation strengthening mechanism of the powder high-temperature alloy, and on the other hand, the comprehensive performance of the alloy is improved by reasonably matching the proportion of solid solution strengthening elements such as Co, Cr, Mo, W and the like in the alloy and gamma 'phase forming elements such as Al, Ti, Nb, Ta and the like in the alloy and improving the gamma' phase strengthening effect in the alloy; on the other hand, the higher W element content increases the distortion energy of the gamma phase of the alloy matrix, and further improves the creep resistance of the matrix phase. Meanwhile, a small amount of Hf element is added into the alloy to improve the grain boundary strength of the alloy, so that the comprehensive mechanical property of the alloy is improved.
Excellent comprehensive performance and stable microstructure. In order to ensure the microstructure of the alloy, the invention develops the applicable preparation process of the alloy according to the characteristics of the components of the alloy and defines the control range of the microstructure (grain size) of the alloy.
Examples and comparative examples
The preparation method of the 7 high-strength creep-resistant powder high-temperature alloys comprises the following steps:
TABLE 1 composition of the components in percent by mass of specific examples of disks of powdered superalloys of the invention
S1, preparing raw materials according to the components and mass fractions in the table 1, and preparing a master alloy bar by adopting a vacuum induction melting process;
s2, preparing the master alloy bar into alloy powder by adopting an argon atomization powder preparation process;
s3, screening the alloy powder to 53-105 microns, then loading the alloy powder into a stainless steel sheath with the size phi of 350mm multiplied by 600mm, carrying out vacuum surface modification treatment, and then sealing and welding;
s4, performing hot isostatic pressing densification forming on the sealed and welded powder sheath;
s5, hot isostatic pressing is adopted to extrude the densified hot isostatic pressing ingot blank into a high-temperature alloy bar;
s6, forging the hot extrusion bar into a disc-shaped piece by adopting isothermal forging;
and S7, carrying out heat treatment on the disk-shaped piece subjected to isothermal forging to obtain the final disk-shaped piece.
TABLE 2 comparative table of preparation parameters for specific examples of disks of powdered superalloys of the invention
The grain size of the powder superalloy prepared by the embodiment of the invention is ASTM10 grade (shown in figure 1), and the 7-component embodiment is compared with the properties of 3 powder superalloy FGH95 alloys (grain size ASTM10 grade, shown in figure 2), FGH96 alloys (grain size ASTM8 grade, shown in figure 3) and FGH720Li (grain size ASTM10 grade, shown in figure 4) which are mature in China, and the comparison results are shown in tables 2-5.
TABLE 3 comparison of tensile strength at room temperature between the disks of the alloys of the examples of the invention and 3 of the domestic alloys
TABLE 4 comparison of 700 ℃ tensile Strength of the alloys of the examples of the present invention with 3 kinds of domestic alloys
TABLE 5 comparison of 750 ℃ tensile strength of the alloys of the examples of the present invention with 3 kinds of domestic existing alloys
TABLE 6 comparison of creep life of the alloys of the examples of the present invention with 3 of the alloys already in China
As shown in the data in Table 3, the yield strength range at room temperature of 7 examples of the invention is 1211MPa to 1264MPa, the tensile strength range is 1670MPa to 1734MPa, the specific strength range is 201.78 to 206.18, the three strength indexes are all higher than that of FGH95 alloy, FGH96 alloy and FGH720Li alloy, and only the yield strength of FGH95 alloy can fall within the high-temperature yield strength range of the powder.
As shown in the data in Table 4, the yield strength of the 7 examples of the invention at 700 ℃ is 1172MPa to 1231MPa, the tensile strength is 1414MPa to 1451MPa, the specific strength is 168.13 to 172.53, and all the three strength indexes are far higher than that of FGH95 alloy, FGH96 alloy and FGH720Li alloy.
As shown in the data in Table 5, the yield strength of the 7 examples of the invention at 750 ℃ ranges from 1141MPa to 1184MPa, the tensile strength ranges from 1284MPa to 1313MPa, the specific strength ranges from 152.44 to 156.00, and all the three strength indexes are far higher than that of FGH95 alloy, FGH96 alloy and FGH720Li alloy.
As shown in the data in Table 6, the creep test is carried out on 7 examples of the invention under the condition of 704 ℃/690MPa, and the creep life range when the creep residual deformation reaches 0.2% is 378 h-481 h, which is far longer than the creep life of the FGH95 alloy, the FGH96 alloy and the FGH720Li alloy under the same condition.
In conclusion, compared with the FGH95 alloy, the FGH96 alloy and the FGH720Li alloy which are mature and applied in China, the 7 embodiments of the invention have the capabilities of high strength and high creep resistance, can meet the strength requirement of the disk center of the turbine disk and the creep resistance requirement of the disk edge under a fine grain state, and are ideal materials for the turbine disk of the future advanced turboshaft engine.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (11)
1. The high-strength creep-resistant high-temperature alloy is characterized by comprising the following components in percentage by mass: cr: 10.00% -12.00%, Co: 12.00% -18.00%, W: 5.50% -7.50%, Mo: 1.50% -3.50%, Al: 3.00% -4.20%, Ti: 3.00% -4.20%, Nb: 1.00% -2.20%, Ta: 0.40% -1.50%, C: 0.01% -0.04%, B: 0.01% -0.04%, Zr: 0.09-1.20 percent of Hf is less than 0.10 percent, and the balance is Ni, wherein,
in the high-strength creep-resistant high-temperature alloy, the total mass percentage of gamma' phase forming elements Al, Ti, Nb and Ta is as follows: 9.5 percent to (Al + Ti + Nb + Ta) to 10.3 percent; the mass percentage content of the gamma' phase in the high-strength creep-resistant high-temperature alloy is 50-55%;
the mass ratio of Al to Ti in the high-strength creep-resistant high-temperature alloy is as follows: 0.9-1.0 (Al/Ti).
2. The high strength creep-resistant superalloy according to claim 1, wherein the high strength creep-resistant superalloy disc has a tensile strength of more than 1650MPa at room temperature and a tensile strength of more than 1400MPa at 700 ℃.
3. The high strength creep-resistant superalloy as in claim 1, wherein the high strength creep-resistant superalloy disc has a specific strength of greater than 0.2Nm/kg at room temperature and the high strength creep-resistant superalloy disc has a specific strength of greater than 0.16Nm/kg at 700 ℃.
4. The high strength creep-resistant superalloy as in claim 1, wherein the disc of the high strength creep-resistant superalloy has a creep residual strain of 0.2% with a lifetime of not less than 350 hours at 704 ℃ and 690 MPa.
5. The high strength creep-resistant superalloy of claim 1, wherein the disc grain size of the high strength creep-resistant superalloy is ASTM9-ASTM12 grade as specified in GB/T6394.
6. The method of making a high strength creep-resistant superalloy as in any of claims 1-5, comprising the steps of:
obtaining an original additive of the high-strength creep-resistant high-temperature alloy, wherein the original additive comprises the following components in percentage by mass: cr: 10.00% -12.00%, Co: 12.00% -18.00%, W: 5.50% -7.50%, Mo: 1.50% -3.50%, Al: 3.00% -4.20%, Ti: 3.00% -4.20%, Nb: 1.00% -2.20%, Ta: 0.40% -1.50%, C: 0.01% -0.04%, B: 0.01% -0.04%, Zr: 0.09-1.20 percent of the total weight of the alloy, less than 0.10 percent of Hf and the balance of Ni; wherein the gamma' phase forming elements Al, Ti, Nb and Ta in the high-strength creep-resistant high-temperature alloy comprise the following components in percentage by mass: 9.5 percent to 10.3 percent (Al + Ti + Nb + Ta); the gamma' phase in the high-strength creep-resistant high-temperature alloy is 50-55% by mass; the mass ratio of Al to Ti in the high-strength creep-resistant high-temperature alloy is as follows: 0.9 to 1.0 percent of (Al/Ti);
and carrying out vacuum induction melting on the original additive of the high-strength creep-resistant high-temperature alloy to prepare a master alloy ingot of the high-strength creep-resistant high-temperature alloy, wherein the melting temperature is 1500-1600 ℃, and the melting vacuum degree is 0.1-0.5 Pa.
7. The method of claim 6, wherein the method of preparing the high strength creep-resistant superalloy powder further comprises the steps of:
and (3) preparing the alloy powder of the high-strength creep-resistant high-temperature alloy by using the bar of the high-strength creep-resistant powder high-temperature alloy through an argon atomization powder preparation process.
8. The method of claim 7, wherein the method of manufacturing the high strength creep-resistant superalloy disc further comprises the steps of:
the alloyThe powder is subjected to vacuum dynamic degassing at 300-400 ℃, and the vacuum degree is less than 3 multiplied by 10-1Pa, then putting the powder sheath into a powder sheath and sealing and welding to obtain an alloy powder sheath after sealing and welding;
compacting and forming the sealed and welded alloy powder sheath to obtain a compact ingot blank;
and carrying out post-treatment on the compact ingot blank to obtain the high-strength creep-resistant high-temperature alloy disc.
9. The method for preparing the high-strength creep-resistant superalloy according to claim 8, wherein in the step of densifying and forming the sealed and welded alloy powder sheath to obtain a densified ingot blank, the densifying and forming method is hot isostatic pressing, the hot isostatic pressing temperature is 1120-1180 ℃, and the hot isostatic pressing pressure is not less than 97 MPa.
10. The method for preparing the high strength creep-resistant superalloy according to claim 8, wherein during the step of post-processing the compact ingot blank to obtain the disc of the high strength creep-resistant superalloy, the post-processing method specifically comprises the following steps:
carrying out hot isostatic pressing on the compact ingot blank to obtain a high-temperature alloy bar;
isothermal forging is carried out on the high-temperature alloy bar to obtain a disc-shaped piece, wherein the isothermal forging temperature is 1050-1150 ℃, and the isothermal forging deformation rate is 0.1-0.4 mm/s;
and carrying out solution heat treatment on the disc-shaped piece to obtain the high-strength creep-resistant high-temperature alloy disc-shaped piece, wherein the solution heat treatment temperature is 1100-1140 ℃, and the solution heat treatment time is 2-4 h.
11. The method as claimed in claim 8, wherein the step of sealing the alloy powder after the surface modification treatment in the sheath to obtain the sealed alloy powder sheath is performed, and the alloy powder is sieved to 53-105 μm before being packed in the sheath.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN87103970A (en) * | 1986-06-02 | 1987-12-16 | 联合工艺公司 | The goods of nickel-base heat resisting superalloy and manufacture method |
| CN1871367A (en) * | 2003-08-29 | 2006-11-29 | 霍尼韦尔国际公司 | High temperature powder metallurgy superalloy with enhanced fatigue & creep resistance |
| CN104561662A (en) * | 2014-11-17 | 2015-04-29 | 江苏环亚电热仪表有限公司 | Powder alloy and production technique thereof |
| CN106661675A (en) * | 2014-08-18 | 2017-05-10 | 通用电气公司 | Enhanced superalloys by zirconium addition |
| CN109385589A (en) * | 2017-08-10 | 2019-02-26 | 三菱日立电力系统株式会社 | The preparation method of Ni based alloy component |
| CN109706346A (en) * | 2018-12-28 | 2019-05-03 | 西安欧中材料科技有限公司 | A kind of nickel base superalloy and the article formed by alloy |
| CN110337500A (en) * | 2017-02-21 | 2019-10-15 | 日立金属株式会社 | Ni base superalloy and its manufacturing method |
| CN110640151A (en) * | 2018-06-26 | 2020-01-03 | 中南大学 | Nickel-based alloy, preparation method thereof and manufactured article |
| EP3633052A1 (en) * | 2017-05-22 | 2020-04-08 | Kawasaki Jukogyo Kabushiki Kaisha | High temperature component and method for producing same |
| JPWO2020031579A1 (en) * | 2018-08-07 | 2020-08-20 | 日立金属株式会社 | Method for producing Ni-base superheat-resistant alloy and Ni-base superheat-resistant alloy |
| CN111868287A (en) * | 2018-03-06 | 2020-10-30 | 日立金属株式会社 | Method for producing Ni-based superalloy and Ni-based superalloy |
-
2022
- 2022-06-07 CN CN202210631907.2A patent/CN114737084A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN87103970A (en) * | 1986-06-02 | 1987-12-16 | 联合工艺公司 | The goods of nickel-base heat resisting superalloy and manufacture method |
| CN1871367A (en) * | 2003-08-29 | 2006-11-29 | 霍尼韦尔国际公司 | High temperature powder metallurgy superalloy with enhanced fatigue & creep resistance |
| CN106661675A (en) * | 2014-08-18 | 2017-05-10 | 通用电气公司 | Enhanced superalloys by zirconium addition |
| CN104561662A (en) * | 2014-11-17 | 2015-04-29 | 江苏环亚电热仪表有限公司 | Powder alloy and production technique thereof |
| CN110337500A (en) * | 2017-02-21 | 2019-10-15 | 日立金属株式会社 | Ni base superalloy and its manufacturing method |
| EP3633052A1 (en) * | 2017-05-22 | 2020-04-08 | Kawasaki Jukogyo Kabushiki Kaisha | High temperature component and method for producing same |
| CN109385589A (en) * | 2017-08-10 | 2019-02-26 | 三菱日立电力系统株式会社 | The preparation method of Ni based alloy component |
| CN111868287A (en) * | 2018-03-06 | 2020-10-30 | 日立金属株式会社 | Method for producing Ni-based superalloy and Ni-based superalloy |
| CN110640151A (en) * | 2018-06-26 | 2020-01-03 | 中南大学 | Nickel-based alloy, preparation method thereof and manufactured article |
| JPWO2020031579A1 (en) * | 2018-08-07 | 2020-08-20 | 日立金属株式会社 | Method for producing Ni-base superheat-resistant alloy and Ni-base superheat-resistant alloy |
| CN109706346A (en) * | 2018-12-28 | 2019-05-03 | 西安欧中材料科技有限公司 | A kind of nickel base superalloy and the article formed by alloy |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115652147A (en) * | 2022-12-29 | 2023-01-31 | 北京钢研高纳科技股份有限公司 | Powder high-temperature alloy and preparation method and application thereof |
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