JP2003034853A - HEAT TREATMENT METHOD FOR Ni-BASED ALLOY - Google Patents
HEAT TREATMENT METHOD FOR Ni-BASED ALLOYInfo
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- JP2003034853A JP2003034853A JP2001223343A JP2001223343A JP2003034853A JP 2003034853 A JP2003034853 A JP 2003034853A JP 2001223343 A JP2001223343 A JP 2001223343A JP 2001223343 A JP2001223343 A JP 2001223343A JP 2003034853 A JP2003034853 A JP 2003034853A
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Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、ガスタービン、ジ
ェットエンジンなどの高温部品、特に動翼あるいは静翼
に使用されるＮｉ基合金の熱処理方法に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a heat treatment method for Ni-based alloys used for high temperature parts such as gas turbines and jet engines, especially for moving blades or stationary blades.
【０００２】[0002]
【従来の技術】周知の如く、例えばガスタービンの動翼
等の高温部品には、Ｎｉ基合金が使用されている。こう
した動翼は高温下で応力をかけられながら長時間使用さ
れるので、運転中にクリープ損傷を受け、減肉やき裂部
が生じたりする。2. Description of the Related Art As is well known, Ni-based alloys are used for high temperature parts such as rotor blades of gas turbines. Since such a moving blade is used for a long time while being stressed under high temperature, it suffers from creep damage during operation, resulting in wall thinning and cracking.
【０００３】そこで、こうした減肉やき裂部の溶接ある
いはロー付け補修、更には母材（Ｎｉ基耐熱合金）のミ
クロ組織的回復を狙って、γ’相（Ｎｉ３Ａｌ金属間化
合物）の固溶温度若しくはそれ以上の加熱を行なってい
る。Therefore, for the purpose of such thinning, welding or brazing of cracks, and repair of the microstructure of the base material (Ni-base heat-resistant alloy), solidification of the γ'phase (Ni 3 Al intermetallic compound) is aimed at. Heating at melting temperature or higher.
【０００４】しかし、その加熱の際に、母材の表層部に
深さ〜０．２ｍｍ程度の再結晶層が発生する。この理由
は、動翼新製時に耐酸化コーティングの下地処理として
Ａｌ ２Ｏ３によるブラスト処理を行なうことにより表層
部に塑性歪が発生し、高温の熱処理で塑性歪の発生部が
再結晶するためである。この再結晶は、実作業上避ける
ことができない。However, during the heating, the surface layer of the base metal
A recrystallized layer having a depth of about 0.2 mm is generated. The reason for this
Is used as a base treatment for the oxidation resistant coating when the rotor blade is newly manufactured.
Al TwoOThreeSurface by blasting with
Plastic strain occurs in the part, and the part where plastic strain occurs due to high temperature heat treatment
This is for recrystallization. Avoid this recrystallization in actual work
I can't.
【０００５】[0005]
【発明が解決しようとする課題】ところで、上述のよう
に発生した再結晶は、高温強度を低下させる（クリープ
破断強度、疲労強度等の低下）ので、再結晶部の強度上
昇が望まれていた。By the way, since the recrystallization generated as described above lowers the high temperature strength (creep rupture strength, fatigue strength, etc.), it is desired to increase the strength of the recrystallized portion. .
【０００６】本発明はこうした事情を考慮してなされた
ので、通常の段階的な熱処理の前に、Ｎｉ基合金製母材
の表層部に径０．３〜０．５μｍのγ’相が析出するよ
うに高温熱処理を施すことにより、母材の表層部も健全
にγ’相が析出するようにして再結晶部の強度向上を図
り得るＮｉ基合金の熱処理方法を提供することを目的と
する。Since the present invention has been made in consideration of such circumstances, a γ'phase having a diameter of 0.3 to 0.5 μm is precipitated on the surface layer of the Ni-base alloy base material before the usual stepwise heat treatment. It is an object of the present invention to provide a heat treatment method for a Ni-based alloy capable of improving the strength of the recrystallized portion by performing the high temperature heat treatment so that the surface layer portion of the base material also precipitates γ ′ phase soundly. .
【０００７】[0007]
【課題を解決するための手段】本発明は、ガスタービ
ン、ジェットエンジンなどの高温部品に使用されるＮｉ
基合金を熱処理する方法において、Ｎｉ基合金製母材を
γ’相の固溶温度もしくはそれ以上の温度で通常の熱処
理を施す前に、母材の表層部に径０．３〜０．５μｍの
γ’相が析出するような高温熱処理を施すことを特徴と
するＮｉ基合金の熱処理方法である。SUMMARY OF THE INVENTION The present invention is a Ni used in high temperature parts such as gas turbines and jet engines.
In the method of heat-treating a base alloy, before the Ni-base alloy base material is subjected to normal heat treatment at a solid solution temperature of the γ'phase or higher, the surface layer of the base material has a diameter of 0.3 to 0.5 μm. Is a high-temperature heat treatment for precipitating the γ'phase of the above.
【０００８】[0008]
【発明の実施の形態】以下、本発明について更に詳細に
説明する。本発明者等は、母材表層部における再結晶部
の強度低下について種々研究を重ねたところ、強度低下
の一因として、再結晶中のγ’相が０．１μｍ以下（通
常約０．３〜０．５μｍ）に微細析出し、脆くなること
を究明した。また、微細析出するのは、再結晶部に転位
等孔子欠陥が大量に導入され、これを起点にγ’相の核
が生成し、成長するためである。BEST MODE FOR CARRYING OUT THE INVENTION The present invention will be described in more detail below. The inventors of the present invention have conducted various studies on the reduction in strength of the recrystallized portion in the surface layer portion of the base material. As a cause of the reduction in strength, the γ ′ phase during recrystallization is 0.1 μm or less (usually about 0.3 μm). It was determined that fine precipitates were formed in a thickness of up to 0.5 μm, and the resulting material became brittle. Further, the reason for fine precipitation is that a large amount of dislocation-like spore defects are introduced into the recrystallized portion, and nuclei of the γ ′ phase are generated and grow from this as a starting point.
【０００９】そこで、本発明では、通常の段階的な熱処
理（例えば、１１２０℃×２時間＋８４３℃×２４時
間）の前に、Ｎｉ基合金製母材の表層部に径０．３〜
０．５μｍの健全なγ’相が析出するように高温熱処理
を施すことにより、母材の表層部も健全にγ’相が析出
するようにして再結晶部の強度向上を図ろうとした。Therefore, in the present invention, before the usual stepwise heat treatment (for example, 1120 ° C. × 2 hours + 843 ° C. × 24 hours), the surface layer portion of the Ni-base alloy base material has a diameter of 0.3 to
It was attempted to improve the strength of the recrystallized portion by performing high-temperature heat treatment so that a sound γ ′ phase of 0.5 μm was precipitated so that the γ ′ phase was also soundly precipitated in the surface layer portion of the base material.
【００１０】本発明において、所定の径のγ’相が析出
するような高温熱処理としては、温度１１８０℃〜１２
６０℃、２〜１０時間で熱処理することが好ましい。こ
こで、温度が１１８０℃未満ではγ’相が固溶せず、温
度が１２６０℃を越えるとγ’相に融解が生じる。従っ
て、γ’相が固溶するとともに初期融解を生じない温度
範囲として上記範囲を設定した。In the present invention, a high temperature heat treatment for precipitating a γ'phase having a predetermined diameter is performed at a temperature of 1180 ° C to 12 ° C.
It is preferable to perform heat treatment at 60 ° C. for 2 to 10 hours. Here, if the temperature is lower than 1180 ° C, the γ'phase does not form a solid solution, and if the temperature exceeds 1260 ° C, melting occurs in the γ'phase. Therefore, the above range was set as a temperature range in which the γ'phase is solid-dissolved and initial melting does not occur.
【００１１】本発明において、通常の熱処理としては、
例えば温度１１１０〜１１３０℃、１〜５時間での熱処
理、急冷工程と、ひきつづき行う温度８４０〜８６０
℃、１６〜２４時間での熱処理、急冷工程との段階的な
熱処理が挙げられる（実施例１、２に対応）。これは、
温度や熱処理時間が上記範囲を外れると、減肉やき裂部
の溶接あるいはロー付けの補修が十分に行われないから
である。また、通常の熱処理としては、例えば温度１２
００〜１２３０℃、１〜５時間での熱処理、急冷工程
と、ひきつづき行う温度１０７０〜１０９０℃、２〜６
時間での熱処理、急冷工程と、さらに行う温度８４０〜
８８０℃、１６〜２４時間での熱処理、急冷工程との段
階的な熱処理が挙げられる（実施例３、４に対応）。な
お、上記急冷とは、例えば３０００℃／ｈ程度を意味す
る。In the present invention, the usual heat treatment includes
For example, heat treatment at a temperature of 1101 to 1130 ° C. for 1 to 5 hours, a quenching step, and a temperature of 840 to 860 continuously performed.
Examples include heat treatment at 16 ° C. for 16 to 24 hours and stepwise heat treatment with a quenching step (corresponding to Examples 1 and 2). this is,
This is because, if the temperature or heat treatment time is out of the above range, the thickness reduction, the welding of the crack portion or the brazing repair cannot be sufficiently performed. Moreover, as the normal heat treatment, for example, a temperature of 12
Heat treatment at 10 to 1230 ° C. for 1 to 5 hours, a quenching step, and temperature to be continuously performed 1070 to 1090 ° C., 2 to 6
Time heat treatment, quenching process, and further temperature 840-
Examples include heat treatment at 880 ° C. for 16 to 24 hours and stepwise heat treatment with a quenching step (corresponding to Examples 3 and 4). The rapid cooling means, for example, about 3000 ° C./h.
【００１２】本発明において、高温熱処理後、５０〜６
００℃／ｈ程度のゆっくりした速度で徐冷することが好
ましい。この理由は、速度が５０℃／ｈ未満では時間が
かかり過ぎ、速度が６００℃／ｈを越えると再結晶相に
おけるγ’相の核が十分に大きくならないからである。In the present invention, after the high temperature heat treatment, 50 to 6
It is preferable to slowly cool at a slow rate of about 00 ° C./h. The reason for this is that if the speed is less than 50 ° C./h, it takes too long, and if the speed exceeds 600 ° C./h, the nuclei of the γ ′ phase in the recrystallized phase do not become sufficiently large.
【００１３】本発明において、母材の表層部に径０．３
〜０．５μｍのγ’相が析出するように高温熱処理を施
すのは、通常、適度な強度をもつ健全な母材における
γ’相の径が０．３〜０．５μｍの範囲にあるからであ
る。In the present invention, the diameter of the surface layer of the base material is 0.3.
The high temperature heat treatment is performed so that the γ'phase of ~ 0.5 μm is precipitated, because the diameter of the γ'phase in a sound base metal having appropriate strength is usually in the range of 0.3 to 0.5 μm. Is.
【００１４】[0014]
【実施例】以下、本発明の各実施例に係るＮｉ基合金の
熱処理方法について説明する。但し、下記実施例で述べ
る各部材の材質、数値等は一例を示すもので、本発明の
権利範囲を特定するものではない。EXAMPLES The heat treatment methods for Ni-based alloys according to the examples of the present invention will be described below. However, the materials, numerical values, etc. of the respective members described in the following examples are merely examples, and do not specify the scope of rights of the present invention.
【００１５】（実施例１）実施例１では、Ｎｉ基合金が
ＩＮ７３８ＬＣ（インターナショナルニッケルカンパニ
ー社製の商品名），即ちＮｉ−１６Ｃｒ−８．５Ｃｏ−
１．７Ｍｏ−２．８Ｗ−１．７Ｔａ−１Ｎｂ−３．５Ｔ
ｉ−３．５Ａｌである場合について試験した。図１を参
照する。(Example 1) In Example 1, the Ni-based alloy was IN738LC (trade name of International Nickel Company), that is, Ni-16Cr-8.5Co-.
1.7Mo-2.8W-1.7Ta-1Nb-3.5T
The case of i-3.5Al was tested. Please refer to FIG.
【００１６】まず、母材としてのＮｉ基合金に例えば１
２００℃で〜８時間、熱処理を施した後、例えば６００
℃／ｈでＮｉ基合金を徐冷した（第１の熱処理工程Ａ）
（室温まで連続して冷却してもよい）。つづいて、通常
の熱処理工程（第２の熱処理工程Ｂ、第３の熱処理工程
Ｃ）を行った。即ち、第２の熱処理工程Ｂでは、１１２
０℃で２時間熱処理した後、例えば３０００℃／ｈでＮ
ｉ基合金急冷を行った（室温まで連続して冷却してもよ
い）。第３の熱処理工程Ｃでは、８４３℃で２４時間熱
処理した後、例えば３０００℃／ｈでＮｉ基合金急冷を
行った。First, for example, a Ni-based alloy as a base material is
After heat treatment at 200 ° C for ~ 8 hours, for example 600
The Ni-based alloy was gradually cooled at ℃ / h (first heat treatment step A)
(It may be cooled to room temperature continuously). Then, the usual heat treatment process (2nd heat treatment process B, 3rd heat treatment process C) was performed. That is, in the second heat treatment step B, 112
After heat treatment at 0 ° C for 2 hours, N at 3000 ° C / h, for example
The i-based alloy was rapidly cooled (may be continuously cooled to room temperature). In the third heat treatment step C, after heat treatment at 843 ° C. for 24 hours, Ni-based alloy quenching was performed at, for example, 3000 ° C./h.
【００１７】このように、実施例１では、通常の熱処理
工程の前に、該熱処理よりも高温（１２００℃）で熱処
理を行うことにより、Ｎｉ基合金の表層部にも健全な径
０．３〜０．５μｍのγ’相が析出させることができ
る。また、高温での熱処理後徐冷を行うため、γ’相の
核を大きくすることができる。従って、表層部の再結晶
層が従来のように脆く無く、再結晶層の強度を向上する
ことができる。As described above, in Example 1, by performing the heat treatment at a temperature (1200 ° C.) higher than that of the heat treatment before the normal heat treatment step, the surface diameter of the Ni-based alloy has a healthy diameter of 0.3. A .gamma. 'Phase of .about.0.5 .mu.m can be precipitated. Further, since the anneal is performed after the heat treatment at a high temperature, the nuclei of the γ'phase can be enlarged. Therefore, the recrystallized layer in the surface layer portion is not brittle as in the conventional case, and the strength of the recrystallized layer can be improved.
【００１８】事実、従来の場合、図５に示すように、母
材としてのＮｉ基合金１の表層部に再結晶層が形成さ
れ、再結晶層中のγ’相２が０．１μｍ以下に微細析出
された。これに対し、実施例１による場合、図６に示す
ように、Ｎｉ基合金１の表層部に再結晶層が形成され、
再結晶層中のγ’相２が０．３〜０．５μｍと従来の場
合と比べて大きな径で析出された。In fact, in the conventional case, as shown in FIG. 5, a recrystallized layer is formed on the surface layer portion of the Ni-based alloy 1 as a base material, and the γ'phase 2 in the recrystallized layer is 0.1 μm or less. Finely deposited. On the other hand, in the case of Example 1, as shown in FIG. 6, a recrystallized layer is formed on the surface layer portion of the Ni-based alloy 1,
The γ ′ phase 2 in the recrystallized layer was 0.3 to 0.5 μm and was deposited with a larger diameter than in the conventional case.
【００１９】なお、実施例１の第１の熱処理工程におい
て、１２００℃で熱処理を行なったが、温度範囲は１１
８０℃〜１２１０℃であればよい。この理由は、１１８
０℃未満ではγ’相が固溶せず、１２１０℃を越えると
合金成分の偏析に起因してγ相に融解が生じるからであ
る。In the first heat treatment step of Example 1, heat treatment was performed at 1200 ° C., but the temperature range was 11
It may be 80 ° C to 1210 ° C. The reason for this is 118
This is because the γ'phase does not form a solid solution below 0 ° C, and the melting occurs in the γ phase due to segregation of alloy components above 1210 ° C.
【００２０】また、実施例１では、徐冷を６００℃で行
なった場合について述べたが、これに限らず、５０〜６
００℃／ｈの範囲であればよい。この理由は、この速度
範囲で冷却すると再結晶相におけるγ’相の核が大きく
なるからである。Further, in the first embodiment, the case where the gradual cooling is performed at 600 ° C. has been described, but the present invention is not limited to this, and 50 to 6 is possible.
It may be in the range of 00 ° C / h. The reason for this is that the nuclei of the γ'phase in the recrystallized phase become large when cooled in this speed range.
【００２１】（実施例２）実施例２では、Ｎｉ基合金が
ＭＧＡ１４００ＣＣ（三菱重工業（株）社製の商品
名），即ちＮｉ−１４Ｃｒ−１０Ｃｏ−１．７Ｍｏ−
４．６Ｗ−４．８Ｔａ−２．４Ｔｉ−４Ａｌである場合
について試験した。図２を参照する。(Example 2) In Example 2, the Ni-based alloy was MGA1400CC (trade name of Mitsubishi Heavy Industries, Ltd.), that is, Ni-14Cr-10Co-1.7Mo-.
The case of 4.6W-4.8Ta-2.4Ti-4Al was tested. Please refer to FIG.
【００２２】まず、母材としてのＮｉ基合金に例えば１
２００℃で〜８時間、熱処理を施した後、例えば６００
℃／ｈでＮｉ基合金を徐冷した（第１の熱処理工程Ａ）
（室温まで連続して冷却してもよい）。つづいて、通常
の熱処理工程（第２の熱処理工程Ｂ、第３の熱処理工程
Ｃ）を行った。即ち、第２の熱処理工程Ｂでは、１１２
０℃で２時間熱処理した後、３０００℃／ｈでＮｉ基合
金を急冷した（室温まで連続して冷却してもよい）。第
３の熱処理工程Ｃでは、８５３℃で２４時間熱処理した
後、３０００℃／ｈでＮｉ基合金を急冷した。実施例２
によれば、実施例１と同様な効果が得られる。First, for example, a Ni-based alloy as a base material is
After heat treatment at 200 ° C for ~ 8 hours, for example 600
The Ni-based alloy was gradually cooled at ℃ / h (first heat treatment step A)
(It may be cooled to room temperature continuously). Then, the usual heat treatment process (2nd heat treatment process B, 3rd heat treatment process C) was performed. That is, in the second heat treatment step B, 112
After heat treatment at 0 ° C. for 2 hours, the Ni-based alloy was rapidly cooled at 3000 ° C./h (may be continuously cooled to room temperature). In the third heat treatment step C, after heat treatment at 853 ° C. for 24 hours, the Ni-based alloy was rapidly cooled at 3000 ° C./h. Example 2
According to this, the same effect as that of the first embodiment can be obtained.
【００２３】なお、実施例２の第１の熱処理工程におい
て、高温熱処理を１２００℃で行なった場合について述
べたが、これに限らず、温度範囲は１２００℃〜１２５
０℃であればよい。その理由は、１２００℃未満では
γ’相が固溶せず、１２５０℃を越えるとγ相に融解が
生じるからである。また、高温熱処理後の徐冷速度も実
施例１の場合と同様である。Although the high temperature heat treatment is performed at 1200 ° C. in the first heat treatment step of the second embodiment, the temperature range is not limited to 1200 ° C. to 125 ° C.
It may be 0 ° C. The reason is that the γ'phase does not form a solid solution below 1200 ° C and the γ phase melts above 1250 ° C. The slow cooling rate after the high temperature heat treatment is also the same as in the case of Example 1.
【００２４】（実施例３）実施例３では、Ｎｉ基合金が
ＭＧＡ１４００ＤＳ’（三菱重工業（株）社製の商品
名、実施例２の合金とは鋳造法が異なる），即ちＮｉ−
１４Ｃｒ−１０Ｃｏ−１．７Ｍｏ−４．６Ｗ−４．８Ｔ
ａ−２．４Ｔｉ−４Ａｌである場合について試験した。
図３を参照する。(Example 3) In Example 3, the Ni-based alloy was MGA1400DS '(trade name of Mitsubishi Heavy Industries, Ltd., the casting method is different from that of the alloy of Example 2), that is, Ni-.
14Cr-10Co-1.7Mo-4.6W-4.8T
The case of a-2.4Ti-4Al was tested.
Please refer to FIG.
【００２５】まず、母材としてのＮｉ基合金に例えば１
２３０℃で〜８時間、熱処理を施した後、例えば６００
℃／ｈでＮｉ基合金を徐冷した（第１の熱処理工程Ａ）
（室温まで連続して冷却してもよい）。つづいて、通常
の熱処理工程（第２の熱処理工程Ｂ、第３の熱処理工程
Ｃ、第４の熱処理工程Ｄ）を順次行った。即ち、第２の
熱処理工程Ｂでは、１２１０℃で２時間熱処理した後、
３０００℃／ｈでＮｉ基合金急冷を行った（室温まで連
続して冷却してもよい）。第３の熱処理工程Ｃでは、１
０８０℃で４時間熱処理した後、３０００℃／ｈでＮｉ
基合金を急冷した。第４の熱処理工程Ｄでは、８５０℃
で２４時間熱処理した後、３０００℃／ｈでＮｉ基合金
を急冷した。実施例３によれば、実施例１と同様な効果
が得られる。First, for example, a Ni-based alloy as a base material is
After heat treatment at 230 ° C for ~ 8 hours, for example 600
The Ni-based alloy was gradually cooled at ℃ / h (first heat treatment step A)
(It may be cooled to room temperature continuously). Subsequently, normal heat treatment steps (second heat treatment step B, third heat treatment step C, fourth heat treatment step D) were sequentially performed. That is, in the second heat treatment step B, after heat treatment at 1210 ° C. for 2 hours,
Ni-based alloy was rapidly cooled at 3000 ° C./h (it may be continuously cooled to room temperature). In the third heat treatment step C, 1
After heat treatment at 080 ℃ for 4 hours, Ni at 3000 ℃ / h
The base alloy was quenched. 850 ° C. in the fourth heat treatment step D
After heat-treating for 24 hours, the Ni-based alloy was rapidly cooled at 3000 ° C./h. According to the third embodiment, the same effect as that of the first embodiment can be obtained.
【００２６】なお、実施例３の第１の熱処理工程におい
て、高温熱処理を１２３０℃で行なった場合について述
べたが、これに限らず、温度範囲は１２３０℃〜１２５
０℃であればよい。その理由は、１２３０℃未満では
γ’相が固溶せず、１２５０℃を越えるとγ相に融解が
生じるからである。また、高温熱処理後の徐冷速度も実
施例１の場合と同様である。In the first heat treatment step of Example 3, the high temperature heat treatment was performed at 1230 ° C., but the temperature range is not limited to 1230 ° C. to 125 ° C.
It may be 0 ° C. The reason is that the γ'phase does not form a solid solution below 1230 ° C and the γ phase melts above 1250 ° C. The slow cooling rate after the high temperature heat treatment is also the same as in the case of Example 1.
【００２７】（実施例４）実施例４では、Ｎｉ基合金が
ＣＭ２４７ＬＣ（キャノンマスケゴン社製の商品名），
即ちＮｉ−８．４Ｃｒ−１０Ｃｏ−０．５Ｍｏ−９．５
Ｗ−３Ｔａ−０．８Ｔｉ−５．５Ａｌ−１．４Ｈｆであ
る場合について試験した。図４を参照する。(Example 4) In Example 4, the Ni-based alloy was CM247LC (trade name of Canon Muskegon),
That is, Ni-8.4Cr-10Co-0.5Mo-9.5.
The case of W-3Ta-0.8Ti-5.5Al-1.4Hf was tested. Please refer to FIG.
【００２８】まず、母材としてのＮｉ基合金に例えば１
２５０℃で〜８時間（ｈ）、熱処理を施した後、例えば
６００℃／ｈでＮｉ基合金を徐冷した（第１の熱処理工
程Ａ）（室温まで連続して冷却してもよい）。つづい
て、熱処理工程（第２の熱処理工程Ｂ、第３の熱処理工
程Ｃ、第４の熱処理工程Ｄ）を順次行った。即ち、第２
の熱処理工程Ｂでは、例えば１２３０℃で２時間熱処理
した後、３０００℃／ｈでＮｉ基合金を急冷した（室温
まで連続して冷却してもよい）。第３の熱処理工程Ｃで
は、１０８０℃で４時間熱処理した後、３０００℃／ｈ
でＮｉ基合金を急冷した。第４の熱処理工程Ｄでは、８
７０℃で２０時間熱処理した後、３０００℃／ｈでＮｉ
基合金を急冷した。First, for example, a Ni-based alloy as a base material is
After heat treatment was performed at 250 ° C. for ˜8 hours (h), the Ni-based alloy was gradually cooled at, for example, 600 ° C./h (first heat treatment step A) (may be continuously cooled to room temperature). Subsequently, heat treatment steps (second heat treatment step B, third heat treatment step C, and fourth heat treatment step D) were sequentially performed. That is, the second
In the heat treatment step B, the Ni-base alloy was rapidly cooled at 3000 ° C./h (for example, continuously cooled to room temperature) after being heat-treated at 1230 ° C. for 2 hours. In the third heat treatment step C, after heat treatment at 1080 ° C. for 4 hours, 3000 ° C./h
Then, the Ni-based alloy was rapidly cooled. In the fourth heat treatment step D, 8
After heat treatment at 70 ℃ for 20 hours, Ni at 3000 ℃ / h
The base alloy was quenched.
【００２９】実施例４によれば、実施例１と同様な効果
が得られる。According to the fourth embodiment, the same effect as that of the first embodiment can be obtained.
【００３０】なお、実施例４の第１の熱処理工程におい
て、高温熱処理を１２５０℃で行なった場合について述
べたが、これに限らず、温度範囲は１２３０℃〜１２６
０℃であればよい。その理由は、１２３０℃未満では
γ’相が固溶せず、１２６０℃を越えるとγ相に融解が
生じるからである。また、高温熱処理後の徐冷速度も実
施例１の場合と同様である。The case where the high temperature heat treatment is performed at 1250 ° C. in the first heat treatment step of Example 4 has been described, but the present invention is not limited to this, and the temperature range is 1230 ° C. to 126 ° C.
It may be 0 ° C. The reason is that the γ'phase does not form a solid solution below 1230 ° C and the γ phase melts above 1260 ° C. The slow cooling rate after the high temperature heat treatment is also the same as in the case of Example 1.
【００３１】[0031]
【発明の効果】以上詳述したように本発明によれば、通
常の段階的な熱処理の前に、Ｎｉ基合金製母材の表層部
に径０．３〜０．５μｍのγ’相が析出するような高温
熱処理を施すことにより、母材の表層部も健全にγ’相
が析出するようにして再結晶部の強度向上を図り得るＮ
ｉ基合金の熱処理方法を提供できる。As described above in detail, according to the present invention, the γ ′ phase having a diameter of 0.3 to 0.5 μm is formed on the surface layer portion of the Ni-based alloy base material before the usual stepwise heat treatment. By subjecting the base material to a high temperature heat treatment so as to cause precipitation, the γ ′ phase can be soundly precipitated even in the surface layer portion of the base material, and the strength of the recrystallized portion can be improved N
A heat treatment method for an i-based alloy can be provided.
【図１】本発明の実施例１に係るＮｉ基合金の熱処理方
法における温度と時間との関係を示す特性図。FIG. 1 is a characteristic diagram showing a relationship between temperature and time in a heat treatment method for a Ni-based alloy according to Example 1 of the present invention.
【図２】本発明の実施例２に係るＮｉ基合金の熱処理方
法における温度と時間との関係を示す特性図。FIG. 2 is a characteristic diagram showing a relationship between temperature and time in a heat treatment method for a Ni-based alloy according to Example 2 of the present invention.
【図３】本発明の実施例３に係るＮｉ基合金の熱処理方
法における温度と時間との関係を示す特性図。FIG. 3 is a characteristic diagram showing the relationship between temperature and time in the heat treatment method for a Ni-based alloy according to Example 3 of the present invention.
【図４】本発明の実施例４に係るＮｉ基合金の熱処理方
法における温度と時間との関係を示す特性図。FIG. 4 is a characteristic diagram showing a relationship between temperature and time in a heat treatment method for a Ni-based alloy according to Example 4 of the present invention.
【図５】従来の熱処理方法によって得られたＮｉ基合金
の表面を顕微鏡（×５０００倍）で撮影した写真の一部
を模式的に示す図。FIG. 5 is a diagram schematically showing a part of a photograph of the surface of a Ni-based alloy obtained by a conventional heat treatment method taken with a microscope (× 5000).
【図６】本発明の熱処理方法によって得られたＮｉ基合
金の表面を顕微鏡（×５０００倍）で撮影した写真の一
部を模式的に示す図。FIG. 6 is a diagram schematically showing a part of a photograph of the surface of a Ni-based alloy obtained by the heat treatment method of the present invention taken with a microscope (× 5000 times).
１…Ｎｉ基合金（母材）、 ２…γ’相。 1 ... Ni-based alloy (base material), 2 ... γ'phase.
───────────────────────────────────────────────────── フロントページの続き (51)Int.Cl.7 識別記号 ＦＩ テーマコート゛(参考） Ｃ２２Ｆ 1/00 ６８２ Ｃ２２Ｆ 1/00 ６８２ ６９１ ６９１Ｂ ６９１Ｃ ６９２ ６９２ (72)発明者 上村 好古 兵庫県高砂市荒井町新浜２丁目１番１号 三菱重工業株式会社高砂製作所内 Ｆターム(参考） 3G002 EA04 EA06 ─────────────────────────────────────────────────── ─── Continuation of front page (51) Int.Cl. 7 Identification code FI theme code (reference) C22F 1/00 682 C22F 1/00 682 692 691 691B 691C 692 692 (72) Inventor Uemura Yoshiko Takasago, Hyogo Prefecture 2-1-1 Nihama, Arai-cho Mitsubishi Heavy Industries, Ltd. Takasago Plant F-term (reference) 3G002 EA04 EA06
Claims (5)
高温部品に使用されるＮｉ基合金を熱処理する方法にお
いて、 Ｎｉ基合金製母材をγ’相の固溶温度もしくはそれ以上
の温度で通常の熱処理を施す前に、母材の表層部に径
０．３〜０．５μｍのγ’相が析出するような高温熱処
理を施すことを特徴とするＮｉ基合金の熱処理方法。1. A method for heat-treating a Ni-base alloy used in high-temperature parts such as a gas turbine and a jet engine, in which a Ni-base alloy base material is subjected to normal heat treatment at a solid solution temperature of a γ'phase or higher. Before the heat treatment, a heat treatment method for a Ni-based alloy is performed by performing high temperature heat treatment such that a γ ′ phase having a diameter of 0.3 to 0.5 μm is precipitated on the surface layer portion of the base material.
熱処理とは、温度１１８０℃〜１２６０℃、２〜１０時
間で熱処理することであることを特徴とする請求項１記
載のＮｉ基合金の熱処理方法。2. The Ni according to claim 1, wherein the high temperature heat treatment for precipitating a γ ′ phase having a predetermined diameter is a heat treatment at a temperature of 1180 ° C. to 1260 ° C. for 2 to 10 hours. Heat treatment method for base alloy.
３０℃、１〜５時間での熱処理、急冷工程と、ひきつづ
き行う温度８４０〜８６０℃、１６〜２４時間での熱処
理、急冷工程との段階的な熱処理であることを特徴とす
る請求項１記載のＮｉ基合金の熱処理方法。3. A normal heat treatment means a temperature of 1110-11.
2. A stepwise heat treatment comprising heat treatment at 30 [deg.] C. for 1 to 5 hours, a quenching step, and heat treatment at a temperature of 840 to 860 [deg.] C. for 16 to 24 hours, followed by quenching. Method for heat treatment of Ni-based alloy of
３０℃、１〜５時間での熱処理、急冷工程と、ひきつづ
き行う温度１０７０〜１０９０℃、２〜６時間での熱処
理、急冷工程と、さらに行う温度８４０〜８６０℃、１
６〜２４時間での熱処理、急冷工程との段階的な熱処理
であることを特徴とする請求項１記載のＮｉ基合金の熱
処理方法。4. The ordinary heat treatment means a temperature of 1200-12.
Heat treatment at 30 ° C. for 1 to 5 hours, a rapid cooling step, temperature 1070 to 1090 ° C. continuously performed, heat treatment at 2 to 6 hours, a rapid cooling step, and further performed temperature 840 to 860 ° C.
The heat treatment method for a Ni-based alloy according to claim 1, which is a stepwise heat treatment including a heat treatment for 6 to 24 hours and a quenching step.
冷することを特徴とする請求項１若しくは請求項２記載
のＮｉ基合金の熱処理方法。5. The heat treatment method for a Ni-based alloy according to claim 1, wherein the high temperature heat treatment is followed by slow cooling at 50 to 600 ° C./h.
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