JP2006057115A - METHOD FOR RECONDITIONING Ni-BASED SINGLE CRYSTAL SUPERALLOY MATERIAL - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a method for reconditioning a Ni-based single crystal superalloy material with acicular harmful precipitates in the matrix. <P>SOLUTION: The method for reconditioning the Ni-based single crystal superalloy material includes heat-treating the Ni-based single crystal superalloy material 10 with the harmful precipitates in the matrix at a temperature range of a decomposition temperature of the harmful precipitates or higher and a partial-melting temperature of the Ni-based single crystal superalloy material or lower (step A), to decompose the harmful precipitates. <P>COPYRIGHT: (C)2006,JPO&NCIPI

Description

  The present invention relates to a method for regenerating a Ni-based single crystal superalloy material in which harmful precipitates are precipitated in a matrix.

Ni-based alloys are generally used as components for components such as turbine blades of jet engines and gas turbine engines. When a turbine blade composed of this Ni-based alloy is used for a long time under high temperature and high stress, the γ ′ phase (Ni ₃ Al) becomes coarse, resulting in a problem that strength characteristics deteriorate.

  Therefore, a method for regenerating the strength of a turbine blade having deteriorated strength characteristics has been proposed as described below.

  (1) A solution treatment is performed on a turbine blade composed of a Ni-base alloy casting at a temperature slightly higher than the temperature at which the γ 'phase of the alloy is completely dissolved and lower than the melting temperature of the alloy dendrite. Thereafter, it is held at 1100 to 1150 ° C. and subjected to a semi-solution treatment for precipitating a primary γ ′ phase, and then an aging treatment for precipitating a secondary γ ′ phase smaller than the primary γ ′ phase (Patent Document 1). reference).

  (2) Solution treatment and aging treatment are applied to the Ni-based super heat resistant crystal alloy material. The solution treatment is, for example, 1345 ° C. × 0.5 h, and the aging treatment is, for example, two-stage aging of 1080 ° C. × 5 h → air cooling → 870 ° C. × 20 h → air cooling (see Patent Document 2).

JP 2000-80455 A JP-A-9-78212

  By the way, in recent years, in turbine blades, improvement in heat-resistant temperature has been demanded, and turbine blades composed of a Ni-based single crystal superalloy have begun to be used.

  It is known that when this turbine blade is used for a long time under high temperature and high stress, needle-like (or plate-like, massive) harmful precipitates called TCP (Topologically Close-Packed) phase are precipitated in the matrix. Yes. The precipitation of the TCP phase in the turbine blade matrix reduces the creep life of the turbine blade. Therefore, there is a demand for a method for recovering the creep life of a turbine blade in which a TCP phase is precipitated in a matrix.

  However, using either of the methods (1) and (2), the TCP phase of the TCP phase precipitation turbine blade cannot be lost, and the turbine blade on which the TCP phase is precipitated can be replaced with a new material. The current situation is that there is no way.

  An object of the present invention created in view of the above circumstances is to provide a method for regenerating a Ni-based single crystal superalloy material in which harmful precipitates are precipitated in a matrix.

  In order to achieve the above object, a method for regenerating a Ni-based single crystal superalloy material according to the present invention is a method for regenerating a Ni-based single crystal superalloy material in which harmful precipitates are precipitated in a matrix. The alloy material is heat-treated in a temperature range not lower than the decomposition temperature of the harmful precipitate and not higher than the partial melting temperature of the Ni-based single crystal superalloy material to decompose the harmful precipitate.

The heat treatment is applied to a Ni-based single crystal superalloy material in which the decomposition temperature of harmful precipitates is lower than the reprecipitation temperature of the γ ′ phase mainly composed of Ni ₃ Al. Here, the heat treatment is preferably performed in a temperature range not lower than the reprecipitation temperature of the γ ′ phase and not higher than the partial melting temperature of the Ni-based single crystal superalloy material.

Further, the heat treatment is performed on the Ni-based single crystal superalloy material in which the decomposition temperature of the harmful precipitate is higher than the reprecipitation temperature of the γ ′ phase composed of Ni ₃ Al.

  On the other hand, the Ni-based single crystal superalloy material according to the present invention is obtained by decomposing harmful precipitates precipitated in the matrix using the above-described regeneration method.

  According to the present invention, it is possible to regenerate and recover the creep life of the Ni-based single crystal superalloy material in which harmful precipitates are precipitated in the matrix.

  DESCRIPTION OF EXEMPLARY EMBODIMENTS Hereinafter, a preferred embodiment of the invention will be described with reference to the accompanying drawings.

The method for regenerating a Ni-based single crystal superalloy material according to a preferred embodiment of the present invention is used for a long time under high temperature and high stress (used over time), and is in the form of needles (or plates or blocks) in the matrix. It is intended for a Ni-based single crystal superalloy material in which a TCP phase (hazardous precipitate) is deposited. The crystal structure of this matrix is a two-phase structure in which fine γ ′ phase (Ni ₃ Al) is precipitated in a lattice form in the γ phase which is the matrix phase.

  Here, as the constituent material of the Ni-based single crystal superalloy material, any material conventionally used as a turbine blade material of a jet engine or a gas turbine engine can be applied, and is not particularly limited. Specifically, Al-Ta-W-Co-Cr-Mo-Hf-Re-Ni alloy, Al-Ta-W-Co-Cr-Mo-Hf-Re-Ru-Ni alloy, For example, 2nd generation Ni-based single crystal superalloy (TMS-82 +, ReneN5 (both registered trademarks)), 3rd generation Ni-based single crystal superalloy (TMS-75, CMSX-10 (both registered trademarks)) 4th generation Ni-based single crystal superalloy (TMS-138 (registered trademark)) and the like.

  As shown in FIG. 1, first, a Ni-based single crystal superalloy material 10 in which a needle-like TCP phase is precipitated in a matrix is prepared. This Ni-based single crystal superalloy material 10 has a significantly reduced creep life because the TCP phase that is the starting point of creep fracture is precipitated.

  Therefore, in order to regenerate and restore the creep life of the Ni-based single crystal superalloy material 10, the Ni-based single crystal superalloy material 10 has a temperature higher than the decomposition (or solid solution) temperature of the TCP phase. Heat treatment is performed in a temperature range below the partial melting temperature of the alloy material (step A). In this heat treatment, as shown in FIG. 2, the temperature is increased from the temperature T0 (= normal temperature) to the temperature T1, and then held at the temperature T1 for a certain time (t2-t1), and then cooled and returned to the temperature T0. These steps are included.

The Ni-based single crystal superalloy material 10 has a TCP phase decomposition temperature (T _{TCP phase} ) lower than a _{γ ′ phase} reprecipitation temperature (T _{γ ′ phase} ) composed of Ni ₃ Al and a higher one. There is. FIG. 3 illustrates an example in which the decomposition temperature of the TCP phase is lower than the reprecipitation temperature of the γ ′ phase (T _{TCP phase} <T _{γ ′ phase} ). As shown in FIG. 3, when the heat treatment is performed at a temperature lower than the decomposition temperature (= T31) of the TCP phase, the TCP phase is naturally not decomposed, and the effect of decomposing the TCP phase by the heat treatment cannot be expected. In addition, when the heat treatment is performed above the partial melting temperature (= T33) of the Ni-based single crystal superalloy material 10, the Ni-based single crystal superalloy material 10 itself is partially melted and the shape cannot be maintained. Therefore, it becomes unusable.

  In contrast, when heat treatment is performed in the temperature range T31 to T32 (region 31), as a result of the heat treatment, the TCP phase precipitated in the matrix is decomposed and transformed into a (γ + γ ′) phase and disappears. On the other hand, when the heat treatment is performed in the temperature range of T32 to T33 (region 32), the TCP phase is decomposed and the γ ′ phase is reprecipitated as a result of the heat treatment. As a result, the TCP phase precipitated in the matrix disappears, and the γ ′ phase is further uniformly and refined (for example, refined to less than 1 μm).

From the above, the Ni-based single crystal superalloy material 10 of T _{TCP phase} <T _{γ ′ phase} is subjected to heat treatment in the regions 31 and 32, preferably in the region 32. The heat treatment temperature and the heat treatment time are appropriately determined according to the type of the Ni-based single crystal superalloy material 10, and are not particularly limited. For example, the heat treatment temperature is 1200 to 1400 ° C., preferably 1230 to 1380 ° C., and the heat treatment time is 5 hours or more, preferably 12 to 48 hours, more preferably 20 to 30 hours. Under these heat treatment conditions, when the heat treatment temperature is high, the heat treatment time is short. Conversely, when the heat treatment temperature is low, the heat treatment time is long.

  The Ni-based single crystal superalloy material 15 after the heat treatment is appropriately subjected to an aging treatment (step B) to obtain the Ni-based single crystal superalloy material 15 in which the TCP phase is decomposed. In this aging treatment, the heating pattern is appropriately determined according to the type of the Ni-based single crystal superalloy material 10. For example, the heating pattern includes only primary aging, primary aging + secondary aging, or primary aging + secondary aging + third-order aging.

  Next, the operation of the present embodiment will be described.

When the Ni-based single crystal superalloy material 10 with T _{TCP phase} <T _{γ ′} is subjected to heat treatment in the region 31 shown in FIG. 3, the TCP phase precipitated in the matrix is decomposed into (γ + γ ′) phase. It transforms and disappears. Since the TCP phase is a starting point of creep rupture, the disappearance of the TCP phase avoids a decrease in the creep life of the Ni-based single crystal superalloy material 15.

  That is, in the method for regenerating a Ni-based single crystal superalloy material according to the present embodiment, the Ni-based single crystal superalloy material 10 in which a needle-like TCP phase is precipitated in the matrix is heat-treated in the temperature range of the region 31. Is applied to obtain the Ni-based single crystal superalloy material 15 in which the TCP phase is decomposed. The creep life of this Ni-based single crystal superalloy material 15 has been regenerated and recovered to a level almost equivalent to that of a new Ni-based single crystal superalloy material.

On the other hand, when the Ni-based single crystal superalloy material 10 with T _{TCP phase} <T _{γ ′} is subjected to heat treatment in the region 32 shown in FIG. 3, the TCP phase decomposes and disappears, and γ ′ phase reprecipitation (re-precipitation) Crystal). Since the TCP phase is a starting point of creep rupture, the disappearance of the TCP phase avoids a decrease in the creep life of the Ni-based single crystal superalloy material 15. Further, the γ 'phase is reprecipitated, so that the crystal structure of the matrix is further uniformed and refined. As a result, the strength of the matrix itself is improved, and further, the strength of the Ni-based single crystal superalloy material 15 itself is improved, and the creep life itself is improved.

  That is, in the method for regenerating a Ni-based single crystal superalloy material according to the present embodiment, the Ni-based single crystal superalloy material 10 in which needle-like TCP phases are precipitated in the matrix is heat-treated in the temperature range of the region 32. As a result, it is possible to obtain the Ni-based single crystal superalloy material 15 in which the TCP phase is decomposed and the γ ′ phase is reprecipitated. The creep life of the Ni-based single crystal superalloy material 15 is regenerated and recovered to a level equivalent to (or nearly equal to) that of a new Ni-based single crystal superalloy material.

  As a result, even if the acicular TCP phase is precipitated in the matrix of the Ni-based single crystal superalloy material, by applying the method for regenerating the Ni-based single crystal superalloy material according to this embodiment, its creep life Can be regenerated and recovered to the same level as a new Ni-based single crystal superalloy material. Here, the Ni-based single crystal superalloy material according to the present embodiment is mainly used as a turbine blade, and its product cost is generally very high. The regeneration method of the Ni-based single crystal superalloy material according to the present embodiment regenerates its creep life without replacing the Ni-based single crystal superalloy material, on which the TCP phase is deposited, with a new one, with the passage of time. Since it can be recovered, the cost can be greatly reduced.

  In addition, conventionally, Ni-based single crystal superalloy material in which a TCP phase is precipitated with use over time has been mainly disposed of, but the method for regenerating Ni-based single crystal superalloy material according to the present embodiment is used. Since it becomes possible to regenerate by applying, it is possible to reduce the disposal cost. That is, the method for recycling the Ni-based single crystal superalloy material according to the present embodiment is also an environmentally friendly method that is excellent in reducing dust.

  Next, another embodiment of the present invention will be described with reference to the accompanying drawings.

In the regeneration method of the Ni-based single crystal superalloy material according to the previous embodiment, the decomposition temperature of the _{TCP phase} (T _{TCP phase} ) is the reprecipitation temperature of the γ ′ phase composed of Ni ₃ Al (T _{γ ′ phase} ). For lower (T _{TCP phase} <T _{γ ′ phase} ).

On the other hand, in the method for regenerating the Ni-based single crystal superalloy material according to the present embodiment, the reprecipitation temperature of the γ ′ phase in which the decomposition temperature of the _{TCP phase} (T _{TCP phase} ) is composed of Ni ₃ Al T γ _'phase) high than (T _{TCP phase>} T _γ' relates to a _phase).

  Specifically, similarly to the regeneration method according to the previous embodiment, first, a Ni-based single crystal superalloy material 10 in which a needle-like TCP phase is precipitated in a matrix is prepared. In order to regenerate and recover the creep life of the Ni-based single crystal superalloy material 10, the Ni-based single crystal superalloy material 10 is made to have a decomposition temperature of the TCP phase or more and a partial melting temperature of the Ni-based single crystal superalloy material or less. The heat treatment is performed in the temperature range.

  As shown in FIG. 4, when the heat treatment is performed at a reprecipitation temperature lower than the γ ′ phase (= T41), the γ ′ phase does not reprecipitate, and the reprecipitation effect of the γ ′ phase by the heat treatment cannot be expected. In addition, when the heat treatment is performed beyond the partial melting temperature (= T43) of the Ni-based single crystal superalloy material 10, the Ni-based single crystal superalloy material 10 itself is partially melted and the shape cannot be maintained. Therefore, heat treatment becomes impossible. On the other hand, when heat treatment is performed in the temperature range of T41 to T42 (region 41), reprecipitation (recrystallization) of the γ ′ phase occurs as a result of the heat treatment. As a result, the γ 'phase in the matrix is further uniformly and refined. In this heat treatment, the creep life itself can be improved to some extent by improving the strength of the matrix itself. However, a decrease in the creep life due to the TCP phase of the Ni-based single crystal superalloy material 10 cannot be avoided.

  In contrast, when heat treatment is performed in the temperature range T42 to T43 (region 42), as a result of the heat treatment, the γ 'phase is reprecipitated, and the TCP phase precipitated in the matrix is decomposed (γ + γ' ) It transforms into a phase and disappears.

As described above, the Ni-based single crystal superalloy material 10 in which the T _{TCP phase} > T _{γ ′ phase} is subjected to heat treatment in the region 42. The heat treatment temperature and the heat treatment time are appropriately determined according to the type of the Ni-based single crystal superalloy material 10, and are not particularly limited. For example, the heat treatment temperature is 1300 to 1400 ° C., preferably 1320 to 1380 ° C., and the heat treatment time is 5 hours or longer, preferably 12 to 48 hours, more preferably 20 to 30 hours. Under these heat treatment conditions, when the heat treatment temperature is high, the heat treatment time is short. Conversely, when the heat treatment temperature is low, the heat treatment time is long.

  The Ni-based single crystal superalloy material after heat treatment is appropriately subjected to an aging treatment, whereby a Ni-based single crystal superalloy material 15 in which the TCP phase is decomposed is obtained (see FIG. 1).

  Next, the operation of the present embodiment will be described.

When the Ni-base single crystal superalloy material 10 with T _{TCP phase} > T _{γ ′} is subjected to heat treatment in the region 42 shown in FIG. 4, reprecipitation (recrystallization) of the γ ′ phase occurs and the TCP phase decomposes. Disappear. By reprecipitation of the γ 'phase, the crystal structure of the matrix is made more uniform and refined. As a result, the strength of the matrix itself is improved, and further, the strength of the Ni-based single crystal superalloy material 15 itself is improved, and the creep life itself is improved. In addition, since the TCP phase is a starting point of creep fracture, the disappearance of the TCP phase avoids a decrease in the creep life of the Ni-based single crystal superalloy material 15.

  That is, also in the method for regenerating the Ni-based single crystal superalloy material according to the present embodiment, the heat treatment is performed in the region 32 (see FIG. 3) in the method for regenerating the Ni-based single crystal superalloy material according to the previous embodiment. The same effect can be obtained.

  As described above, the present invention is not limited to the above-described embodiment, and it goes without saying that various other things are assumed.

  Next, although this invention is demonstrated based on an Example, this invention is not limited to these Examples.

  Ni-based single crystal superalloy material using TMS-138 (5.9Al-5.9Ta-5.9W-5.8Co-2.9Cr-2.9Mo-0.1Hf-4.9Re-2.0Ru-Ni (Bal.); Wt%) Three (test materials) were produced. Using each test material, a simulated operation was performed with a profile of 1100 ° C. × 200 h, and a needle-like TCP phase was precipitated in the matrix (TCP phase-deposited material).

  Each TCP phase-deposited material was heat-treated at 1200 ° C. × 24 h, 1250 ° C. × 24 h, and 1300 ° C. × 24 h (test materials 1a to 1c). The degree of transformation of the TCP phase in each of the test materials 1a to 1c after the heat treatment was observed.

  As a result, as shown in FIGS. 5 (a) and 5 (b), in the test material 1a subjected to heat treatment at 1200 ° C. × 24 h, the needle-like TCP phase (in FIG. 5 (b)) is still in the matrix. , As indicated by the arrows) remained precipitated, and almost no transformation of the TCP phase was observed. Further, in FIGS. 5A and 5B, the γ ′ phase indicated by the black pattern is precipitated in a lattice form in the γ phase that is the parent phase indicated by the white pattern. The 'phase was as coarse as several μm.

  On the other hand, as shown in FIGS. 6A and 6B, in the test material 1b subjected to the heat treatment of 1250 ° C. × 24 h, a part of the TCP phase in the matrix is decomposed and ( It was transformed and decomposed into a (γ + γ ′) phase (indicated by an arrow in FIG. 6B). In addition, in FIGS. 6A and 6B, fine (less than 1 μm) γ ′ phase shown by a black pattern precipitates in a lattice pattern in a non-uniform manner in the γ phase shown by a white pattern. The beginning was observed.

  In addition, as shown in FIGS. 7A and 7B, in the test material 1c subjected to the heat treatment of 1300 ° C. × 24 h, the TCP phase in the matrix is almost completely decomposed, and the TCP phase is Almost no observation was made. Further, in FIGS. 7A and 7B, the fine (less than 1 μm) γ ′ phase shown by the black pattern is uniformly and lattice-like in the γ phase shown by the white pattern. Reprecipitation was observed.

  From the above, when applying the Ni-based single crystal superalloy material regeneration method according to the present invention to the TMS-138 material in which the TCP phase is precipitated, if the heat treatment at 1250 ° C. × 24 h is performed, only the decomposition of the TCP phase will occur. It was confirmed that when the heat treatment at 1300 ° C. × 24 h was performed, decomposition of the TCP phase and reprecipitation of the γ ′ phase occurred.

  A creep test was performed on the test material, TCP phase precipitation material, and test materials 1a to 1c in [Example 1] under the conditions of 1100 ° C. and 137 MPa. The elapsed time when the strain was 0.01 (creep life when the creep deformation was 1%) was evaluated.

  In FIG. 8, the test material (new material) indicated by a circle has a creep life of about 400 hours. In contrast, the TCP phase-deposited material after the simulated operation indicated by □ in FIG. 8 has a creep life of about 80 hours, which is about 80% lower than the creep life of the test material.

  The test material 1a (shown by Δ in FIG. 8) obtained by subjecting the TCP phase-deposited material to a heat treatment of 1200 ° C. × 24 h has a creep life of only about 100 h, and has almost no effect on regeneration and recovery of the creep life by the heat treatment. It was not obtained.

  In contrast, the test material 1b (shown by a black circle in FIG. 8) obtained by subjecting the TCP phase-deposited material to a heat treatment of 1250 ° C. × 24 h has a creep life of about 240 h, and the creep life of the TCP phase-deposited material. Compared to, it recovered about 3 times. In addition, the test material 1c (shown by ◇ in FIG. 8) obtained by subjecting the TCP phase-deposited material to a heat treatment of 1300 ° C. × 24 h has a creep life of about 300 h, which is compared with the creep life of the TCP phase-deposited material. It had recovered to about 4 times.

  From the above, by applying the Ni-based single crystal superalloy material regeneration method according to the present invention to the TMS-138 material in which the TCP phase is precipitated, its creep life can be greatly regenerated and recovered. It could be confirmed. In addition, it was confirmed that the test material 1c in which the TCP phase was decomposed and the γ ′ phase was reprecipitated was regenerated and recovered more than the test material 1b in which the TCP phase was only decomposed. .

  CMSX-10 (5.7Al-8.4Ta-5.5W-3.3Co-2.3Cr-0.4Mo-0.3Ti-0.1Nb-0.03Hf-6.3Re-Ni (Bal.); Wt%) and Ni-based single crystal Two superalloy materials (test materials) were prepared. Using each test material, a simulated operation was performed with a profile of 1200 ° C. × 24 h, and a needle-like TCP phase was precipitated in the matrix (TCP phase-deposited material).

  Each TCP phase precipitate was subjected to 1300 ° C. × 24 h → gas fan cooling (GFC) and 1350 ° C. × 24 h → gas fan cooling (test materials 3a and 3b). The degree of transformation of the TCP phase in each of the test materials 3a and 3b after the heat treatment was observed.

  As a result, as shown in FIGS. 9 (a) and 9 (b), in the test material 3a subjected to the heat treatment of 1300 ° C. × 24 h, the needle-like TCP phase (FIG. 9 (a), In FIG. 9 (b), as indicated by 91) remained precipitated, and almost no transformation of the TCP phase was observed. However, in FIGS. 9 (a) and 9 (b), the fine (less than 1 μm) γ ′ phase indicated by the black pattern precipitates in a lattice pattern in a non-uniform manner within the γ phase indicated by the white pattern. The beginning was observed.

  Further, as shown in FIGS. 10 (a) and 10 (b), in the test material 3b subjected to the heat treatment of 1350 ° C. × 24 h, the TCP phase in the matrix is completely decomposed and the (γ + γ ′) phase is obtained. It was transformed and decomposed (indicated by 101 in FIG. 10B), and almost no TCP phase was observed. 10A and 10B, the fine (less than 1 μm) γ ′ phase shown by the black pattern is uniformly and lattice-like in the γ phase shown by the white pattern. Reprecipitation was observed.

  As described above, when the heat treatment of 1300 ° C. × 24 h is applied to the CMSX-10 material in which the TCP phase is precipitated, when the Ni-based single crystal superalloy material regeneration method according to the present invention is applied, the γ ′ phase is regenerated. Only precipitation occurred, and it was confirmed that when heat treatment at 1350 ° C. × 24 h was performed, decomposition of the TCP phase and reprecipitation of the γ ′ phase occurred.

It is a figure which shows the flow of the reproduction | regeneration method of the Ni base single crystal superalloy material which concerns on suitable one embodiment of this invention. It is a figure which shows the profile of the heat processing in FIG. It is a figure which shows the relationship between the decomposition temperature of a TCP phase at the time of heat processing (T _{TCP phase} ), and the reprecipitation temperature of a _{γ ′ phase} (T _{γ ′ phase} ), and T _{TCP phase} <T _{γ ′ phase} . It is a figure which shows the relationship between the decomposition temperature (T _{TCP phase} ) of the TCP phase at the time of heat processing, and the reprecipitation temperature (T _{γ 'phase} ) of the _{γ' phase} , where T _{TCP phase} > T _{γ 'phase} . It is a crystal structure observation figure of the test material 1a in [Example 1]. FIG. 5B is a partially enlarged view of FIG. It is a crystal structure mirror observation figure of the test material 1b in [Example 1]. FIG. 6B is a partially enlarged view of FIG. It is a crystal structure mirror observation figure of the test material 1c in [Example 1]. FIG. 7B is a partially enlarged view of FIG. It is a figure which shows the creep test result of the test material in [Example 2], a TCP phase precipitation material, and the test materials 1a-1c. In FIG. 8, the horizontal axis indicates time, and the vertical axis indicates distortion. It is a crystal structure mirror observation figure of the test material 3a in [Example 3]. FIG. 9B is a partially enlarged view of FIG. It is a crystal structure observation figure of the test material 3b in [Example 3]. FIG. 10B is a partially enlarged view of FIG.

Explanation of symbols

10 Ni-based single crystal superalloy material with TCP phase (hazardous precipitate) deposited
stepA heat treatment

Claims (5)

  In a method for regenerating a Ni-based single crystal superalloy material in which harmful precipitates are precipitated in a matrix, the Ni-based single crystal superalloy material has a decomposition temperature of the harmful precipitates or higher and a Ni-based single crystal superalloy material. A method for reclaiming a Ni-based single crystal superalloy material, wherein heat treatment is performed in a temperature range equal to or lower than the partial melting temperature of to decompose harmful precipitates. The Ni-based single crystal according to claim 1, wherein the heat treatment is performed on the Ni-based single crystal superalloy material having a decomposition temperature of the harmful precipitate lower than a reprecipitation temperature of a γ 'phase mainly composed of Ni ₃ Al. A method for regenerating a crystalline superalloy material.   The method for regenerating a Ni-based single crystal superalloy material according to claim 2, wherein the heat treatment is performed in a temperature range not lower than the reprecipitation temperature of the γ 'phase and not higher than a partial melting temperature of the Ni-based single crystal superalloy material. 2. The Ni-based single crystal superalloy according to claim 1, wherein the heat treatment is performed on the Ni-based single crystal superalloy material having a decomposition temperature of the harmful precipitate higher than a reprecipitation temperature of the γ ′ phase composed of Ni ₃ Al. Recycle method of alloy material. 5. A Ni-based single crystal superalloy material characterized by decomposing harmful precipitates precipitated in a matrix using the regeneration method according to claim 1.

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