WO2015151808A1 - Fe-Ni基超耐熱合金の製造方法 - Google Patents
Fe-Ni基超耐熱合金の製造方法 Download PDFInfo
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- WO2015151808A1 WO2015151808A1 PCT/JP2015/057991 JP2015057991W WO2015151808A1 WO 2015151808 A1 WO2015151808 A1 WO 2015151808A1 JP 2015057991 W JP2015057991 W JP 2015057991W WO 2015151808 A1 WO2015151808 A1 WO 2015151808A1
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- C—CHEMISTRY; METALLURGY
- 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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- 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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- the present invention relates to a method for producing a Fe—Ni base superalloy.
- the 718 alloy which is an Fe—Ni-based superalloy used as a gas turbine component for aircraft and power generation, has excellent mechanical properties and is the most widely used superalloy. In particular, high fatigue strength is required for large rotating parts of jet engines and gas turbines. For this reason, the 718 alloy used for such parts needs to have high fatigue strength by uniformly refining crystal grains.
- a method of uniformly refining crystal grains usually, after producing a billet from an ingot of 718 alloy, by performing hot working in a temperature range of 930 to 1010 ° C. using the pinning effect of the delta phase, Examples thereof include a method of forming a fine recrystallized structure and then performing a solution heat treatment and an aging treatment, or a direct aging treatment.
- AGG abnormal-grain-growth
- FIG. 2 when hot working is performed under low strain conditions in stamping forging or ring rolling, delta during hot working, cooling after hot working, or solution treatment after hot working. It may cause abnormal-grain-growth (hereinafter sometimes referred to as “AGG”) in which crystal grains rapidly grow over the phase pinning.
- AGG abnormal-grain-growth
- FIG. 2 When AGG as shown in FIG. 2 is developed, the uniform fine structure is destroyed, resulting in a problem that fatigue characteristics are impaired.
- an influencing factor that prevents AGG is specified, and distortion of 0.125 or more is applied to the entire region of the component.
- Patent Document 1 When a 718 alloy is used for a component that emphasizes fatigue strength, the alloy must have a uniform and very fine grain structure with an ASTM grain size number of 9 or more.
- the invention described in Patent Document 1 is excellent in that AGG can be prevented by subsequent solution treatment by applying a strain of 0.125 or more to the entire region of the 718 alloy part in the hot forging process.
- hot working includes stamping forging, ring rolling, and the like.
- strain is imparted to the 718 alloy at various strain rates. For example, when a strain of about 0.125 is applied to a 718 alloy at low strain rate conditions, hot processing may still be performed in a region where AGG is expressed, and a fine grain structure can be obtained. There was no problem. This problem becomes a problem particularly when a large-sized forged product or a ring-rolled product subjected to stamping forging or ring rolling is manufactured using the 718 alloy.
- An object of the present invention is to provide a method for producing an Fe—Ni-based superalloy that can suppress AGG and obtain a fine grain structure having an ASTM grain size number of 9 or more.
- the present invention has been made in view of the above-described problems. That is, the present invention relates to 0.08 mass% or less C, 0.35 mass% or less Si, 0.35 mass% or less Mn, 0.015 mass% or less P, and 0.015 mass%.
- the method for producing a Fe—Ni-base superalloy according to the present invention may include a solution treatment step of performing a solution treatment for 0.5 to 10 hours in the range of 950 to 1000 ° C.
- heat treatment is performed at a temperature of 600 to 930 ° C. for 5 to 60 hours after the hot working step and before the solution treatment step.
- a heat treatment step can be included.
- the method for producing a Fe—Ni-base superalloy according to the present invention includes a first temporary effect treatment step of performing a first temporary effect treatment for 2 to 20 hours in the range of 700 to 750 ° C. after the solution treatment step. Can do.
- the method for producing a Fe—Ni-base superalloy according to the present invention includes a second aging treatment step of performing a second aging treatment in the range of 600 to 650 ° C. for 2 to 20 hours after the first temporary treatment treatment step. be able to.
- the present invention it is possible to avoid the AGG of the Fe—Ni base superalloy and to obtain a uniform fine crystal grain structure having an ASTM grain size number of 9 or more.
- the reliability of fatigue characteristics of a jet engine, a gas turbine member, or the like using this Fe—Ni base superalloy can be improved.
- the present invention includes at least a hot working step of hot working a material of a Fe—Ni base superalloy having a predetermined alloy composition.
- a hot working process such as hot forging
- the object is to prevent abnormal crystal grain growth by optimizing hot working conditions for various strain rates such as stamping forging and ring rolling.
- a specific example of the hot working process will be described below.
- the alloy composition of the Fe—Ni based super heat-resistant alloy specified in the present invention is known as an NCF718 alloy (Fe—Ni based super heat resistant alloy) shown in JIS-G4901, and therefore a detailed description of the composition is as follows. Omit. Here, “4.75 to 5.50% by mass of Nb + Ta” means that the Fe—Ni-based superalloy has a total composition of Nb and Ta of 4.75 to 5.50% by mass. .
- a material of the Fe—Ni based super heat resistant alloy in a temperature range of 930 to 1010 ° C. is hot worked. This is because by using a material in this temperature range, recrystallization can be promoted during hot working such as hot forging. When the temperature of the material before hot working is less than 930 ° C., recrystallization during hot working hardly occurs. On the other hand, when the temperature of the material before hot working exceeds 1010 ° C., recrystallization during hot working is promoted, but the size of the recrystallized grains to be generated increases, so it is difficult to obtain fine grains. It becomes.
- the material of the Fe—Ni base superalloy at 930 to 1010 ° C. can be obtained, for example, by heating the material before hot working.
- the hot working condition is [equivalent strain] ⁇ 0.139 ⁇ [equivalent strain rate (/ sec) over the entire area of the material of the Fe—Ni base superalloy in the temperature range of 930 to 1010 ° C. )]
- the relationship ⁇ 0.30 is satisfied.
- This relational expression is applied to hot forging including stamping forging, hot die forging, and isothermal forging, and equivalent strain assumed in hot working such as a ring mill is 5 or less, and equivalent strain rate is 0.0001 to 10 / sec.
- a preferable upper limit of the equivalent strain is 4, more preferably 3.5.
- a preferable lower limit of the equivalent strain rate is 0.001 / second, and more preferably 0.005 / second.
- a preferable upper limit of the equivalent strain rate is 5 / second, more preferably 1 / second.
- the equivalent strain and the equivalent strain rate represent the strain and strain rate when the vertical and shear six-axis elements are converted into a single axis.
- AGG is expressed when the crystal grain size before hot working is about 8 or more in terms of ASTM grain size number, and the finer the initial crystal grain, the higher the sensitivity. According to the study by the present inventor, as shown in FIG. 1, it is recognized that the range (B) in which AGG occurs is larger as the strain rate is lower. This tendency is due to the fact that, under the condition of low strain rate, for example, strain is accumulated again in dynamic recrystallization that occurred during stamping forging. Due to the movement. On the other hand, AGG can usually be prevented in a low strain region (C) that satisfies the relationship of the following formula.
- this region (C) is a region corresponding to a dead zone during hot working, refinement by recrystallization cannot be expected.
- the region (A) is a region where crystal grain refining can be performed by recrystallization, and AGG can also be prevented.
- a region (B) where AGG is expressed also exists.
- the relational expression of the region (B) is as follows.
- a suitable strain is applied to the entire area of the hot working material so as to satisfy the following relational expression, thereby preventing AGG more reliably.
- relational expressions indicating the regions (A) to (C) are obtained by performing multiple regression on the relationship between the equivalent strain in which AGG occurs and the equivalent strain rate based on the results of the tissue observation.
- the method for producing a Fe—Ni-based superalloy according to the present invention can perform a solution treatment after the hot working step. Moreover, the heat treatment process which heats the said alloy as a preheating can be performed before a solution treatment. Then, after the solution treatment, the first temporary effect treatment can be performed. Furthermore, a second aging process can be performed after the first temporary effect process. Specific examples of these processes are described below.
- this heat treatment step it is possible to further reduce the risk of developing AGG in a solution treatment at 950 to 1000 ° C. performed later.
- the removal of accumulated strain energy in this preheating treatment is performed by positively precipitating precipitates. That is, gamma double prime and gamma prime contributing to strength improvement are precipitated in a temperature range of 600 to 800 ° C., and a delta phase is precipitated at 800 to 930 ° C.
- this preheating treatment after holding for a certain time at a specific temperature and performing a first stage preheating treatment for depositing gamma double prime and gamma prime, the temperature is then raised to a certain temperature and held for a certain time.
- a two-stage heat treatment can be performed in which a second-stage preheating treatment for precipitating the delta phase is performed.
- the preheating temperature is less than 600 ° C.
- the precipitation of gamma double prime and gamma prime cannot be expected.
- the preheating temperature exceeds 930 ° C.
- crystal grains may grow before the accumulated strain energy is removed.
- the preheating time is less than 5 hours, the effects of removing the accumulated strain energy and depositing the precipitate may be insufficient.
- the preliminary heat treatment time exceeds 60 hours, further improvement in the effect cannot be expected.
- the preheating treatment conditions before the solution treatment are preferably in the range of 600 to 930 ° C. for 5 to 60 hours.
- a preferred lower limit of the preheating temperature is 650 ° C, more preferably 700 ° C.
- a preferable upper limit of the preheat treatment temperature is 920 ° C, more preferably 910 ° C.
- the minimum with the preferable preheat processing time is 7 hours, More preferably, it is 10 hours.
- a preferable upper limit of the preheating treatment time is 50 hours, and more preferably 40 hours.
- the heating temperature during the solution treatment is also important. If the heating temperature of the solution treatment is less than 950 ° C., the delta phase is excessively precipitated during the solution treatment, so that the amount of gamma double prime deposited in the subsequent aging treatment is reduced, leading to a decrease in the overall strength. On the other hand, when the solution treatment temperature exceeds 1000 ° C., crystal grains grow with a decrease in the pinning effect of the delta phase, and the tensile strength and fatigue strength decrease. Therefore, the solution treatment temperature is 950 to 1000 ° C. The temperature is preferably 950 to 990 ° C. The retention time for the solution treatment is 0.5 to 10 hours. If it is less than 0.5 hour, the solid solution effect of the compound precipitated during cooling after the end of hot working is low. On the other hand, treatment exceeding 10 hours is economically inefficient and may cause growth of fine crystal grains. Preferably it is 1 to 3 hours.
- the solution heat-treated Fe—Ni base superalloy is held at 700 to 750 ° C. for 2 to 20 hours, then cooled to 600 to 650 ° C., and then held at 600 to 650 ° C. for 2 to 20 hours.
- a second aging treatment can be performed.
- the purpose of the aging treatment is to obtain a high temperature and high strength by finely precipitating the precipitation strengthening phase of the gamma prime phase and the gamma double prime phase. Only the second aging treatment on the low temperature side may take too much time to precipitate the precipitation strengthening phase. Therefore, as the first temporary treatment, the aging treatment is performed on the high temperature side and the gamma prime phase and the gamma double prime phase Precipitation can be promoted.
- the treatment temperature of the first temporary treatment is set to a temperature range of 700 to 750 ° C. Preferably, it is 710 to 730 ° C.
- the holding time of the treatment temperature of the first temporary treatment is less than 2 hours, the precipitation of the gamma prime phase or the gamma double prime phase becomes insufficient.
- the holding time of the first temporary effect treatment exceeds 20 hours, the effect of precipitation of the gamma prime phase or the gamma double prime phase may be saturated, which is not economical. Therefore, the holding time of the first temporary treatment is in the range of 2 to 20 hours. Preferably, it is 4 to 15 hours.
- the treatment temperature of the second aging treatment is set to a temperature range of 600 to 650 ° C.
- the temperature is preferably 610 to 630 ° C.
- the holding time of the treatment temperature of the second aging treatment is 2 to 20 hours for the same reason as the first temporary treatment described above. Preferably, it is 4 to 15 hours.
- Example 1 After performing upset forging in a temperature range of 950 to 1000 ° C. using a billet having a chemical composition corresponding to the Fe—Ni base super heat-resistant alloy (718 alloy) shown in Table 1, within the temperature range of 950 to 1000 ° C. Then, ring rolling was performed. Next, in order to remove strain remaining in the thermal alloy, the thermal alloy is held at 980 ° C. for 1 hour, and then air-cooled to room temperature, and a small compression test piece shown in FIG. It was. Using this small compression test piece as a test material, a hot working test was conducted to investigate factors affecting the generation of AGG.
- the crystal grain size of the test material was an average crystal grain size number 10 as measured by ASTM-E112.
- the effects of strain and strain rate on the factors that cause AGG were investigated.
- the heating temperature is 980 ° C.
- the rolling reduction is 10 to 50%
- the nominal strain rate calculated from the compression rate relative to the height of the specimen before compression is 0.005 to 0.5 / sec
- the cooling rate after compression is 540
- a compression test was performed under the condition of ° C./min. Thereafter, the test piece was subjected to a solution treatment at 980 ° C. for 1 hour, and the longitudinal section was observed with an optical microscope.
- the equivalent strain and the equivalent strain rate at the site where the structure was observed were determined by reproducing a hot working test using a commercially available forging analysis software DEFORM. When the crystal grain size number after the solution treatment was less than 9, it was determined that AGG was expressed.
- Table 2 shows the compression test conditions, crystal grain size number (ASTM), and AGG determination results.
- region (A) and region (C) are regions where AGG is not expressed, and region (B) is a region where AGG is expressed.
- region (A) is a region that can be refined by recrystallization and can also prevent AGG.
- Region (C) is a region corresponding to a dead zone during hot working, and cannot be miniaturized by recrystallization.
- the width of the region (B) becomes wider as the equivalent strain rate becomes smaller, it was found that the range of equivalent strain in which AGG occurs becomes larger. From the result of FIG.
- Hot forging was performed using 800 kg of a hot working material made of a Fe—Ni based super heat resistant alloy (718 alloy) having the composition shown in Table 1. Hot forging was performed on a hot working material in a temperature range of 980 to 1000 ° C. so that the equivalent strain satisfied the relationship of the following formula over the entire area of the hot working material. After hot forging, preheating and solution treatment under the six conditions (a) to (f) shown in Table 3 are performed for the purpose of suppressing the crystal grain growth during the solution treatment as much as possible. A first aging treatment at 8 ° C. for 8 hours and a second aging treatment at 621 ° C. for 8 hours were performed.
- Table 4 shows the results of measuring the crystal grain size of the material that has been subjected to hot forging without performing the solution treatment and the solution treatment material. Even when the normal solution treatment was performed without preheating, a crystal grain size of 9 or more was obtained (condition (a)). It was found that the heat treatment conditions (b) to (f) including preheating further suppressed the growth of crystal grains as compared with the normal solution treatment conditions (a). Of the heat treatment conditions including preheating, conditions (b), (c) and (d) by two-stage heating at 720 ° C. and 900 ° C. were the most effective.
- the manufacturing method of the present invention when the manufacturing method of the present invention is applied, the AGG of the Fe—Ni-base superalloy is suppressed, and a fine grain structure having an ASTM grain size number of 9 or more can be obtained. From this, the reliability of the fatigue characteristics of a jet engine, a gas turbine member, etc. can be improved.
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Abstract
Description
即ち本発明は、0.08質量%以下のCと、0.35質量%以下のSiと、0.35質量%以下のMnと、0.015質量%以下のPと、0.015質量%以下のSと、50.0~55.0質量%のNiと、17.0~21.0質量%のCrと、2.8~3.3質量%のMoと、1.0質量%以下のCoと、0.30質量%以下のCuと、0.20~0.80質量%のAlと、0.65~1.15質量%のTiと、4.75~5.50質量%のNb+Taと、0.006質量%以下のBと、残部がFeおよび不可避的な不純物からなる組成を有するFe-Ni基超耐熱合金の製造方法において、前記組成を有する素材を熱間加工する熱間加工工程を少なくとも含み、前記熱間加工工程は、930~1010℃の前記素材を、当該素材の全域で、[相当歪]≧0.139×[相当歪速度(/sec)]-0.30の関係を満足するように熱間加工する工程を少なくとも含む、Fe-Ni基超耐熱合金の製造方法である。
また、本発明のFe-Ni基超耐熱合金の製造方法では、950~1000℃の範囲で0.5~10時間の固溶化処理を行う固溶化処理工程を含むことができる。
また、本発明のFe-Ni基超耐熱合金の製造方法では、前記熱間加工工程の後であって、前記固溶化処理工程の前に、600~930℃の範囲で5~60時間熱処理する熱処理工程を含むことができる。
また、本発明のFe-Ni基超耐熱合金の製造方法では、前記固溶化処理工程後、700~750℃の範囲で2~20時間の第一時効処理を行う第一時効処理工程を含むことができる。
また、本発明のFe-Ni基超耐熱合金の製造方法では、前記第一時効処理工程後、600~650℃の範囲で2~20時間の第二時効処理を行う第二時効処理工程を含むことができる。
本発明は、所定の合金組成を有するFe-Ni基超耐熱合金の素材を熱間加工する熱間加工工程を少なくとも含む。熱間鍛造等の熱間加工工程において、型打ち鍛造やリング圧延などの種々の歪速度に対する熱間加工条件を最適化することにより、異常結晶粒成長を防止することにある。熱間加工工程の具体例について、以下に説明する。
なお、本発明で規定するFe-Ni基超耐熱合金の合金組成は、JIS-G4901に示されるNCF718合金(Fe-Ni基超耐熱合金)として知られるものであるため、組成に関する詳細な説明は割愛する。ここで、「4.75~5.50質量%のNb+Ta」は、Fe-Ni基超耐熱合金がその組成として、NbとTaを合計で4.75~5.50質量%含むという意味である。
微細結晶粒組織のFe-Ni基超耐熱合金を得るためには、930~1010℃の温度範囲にあるFe-Ni基超耐熱合金の素材を熱間加工する。この温度範囲の素材を用いることにより、熱間鍛造等の熱間加工中に再結晶を促進させることができるからである。熱間加工前の前記素材の温度が930℃未満の場合、熱間加工中の再結晶がほとんど発現しない。一方、熱間加工前の前記素材の温度が1010℃を超える場合、熱間加工中の再結晶は促進されるが、生成する再結晶粒のサイズが大きくなるため、微細粒を得るのが困難となる。熱間加工前の前記素材の温度を930~1010℃、好ましくは950~1000℃とすることにより、微細な結晶の再結晶化を促進させることができる。930~1010℃のFe-Ni基超耐熱合金の素材は、例えば、熱間加工前に前記素材を加熱することにより、得ることができる。
上述した熱間加工工程後、空冷等により冷却されたFe-Ni基超耐熱合金について、固溶化処理をする前の予備加熱として、600~930℃の範囲で5~60時間熱処理する工程である。この熱処理工程により、後に行う950~1000℃の固溶化処理でAGGが発現するリスクをより低減することができる。
熱間加工工程で得られた微細再結晶組織を維持させるためには、固溶化処理時の加熱温度も重要となる。固溶化処理の加熱温度が950℃未満では、固溶化処理中にデルタ相が過度に析出するため、その後の時効処理で析出させるガンマダブルプライムの量が減少し、全体的な強度低下を招く。一方、固溶化処理温度が1000℃を超えるとデルタ相のピンニング効果の低下に伴い、結晶粒が成長し引張や疲労強度が低下する。そのため、固溶化処理温度は950~1000℃とする。好ましくは950~990℃である。
また、固溶化処理の保持時間は0.5~10時間とする。0.5時間未満では、熱間加工終了後の冷却中に析出した化合物の固溶効果が低い。一方、10時間を超える処理は経済的に効率が悪い上、微細結晶粒の成長を招くおそれがある。好ましくは1~3時間である。
固溶化熱処理したFe-Ni基超耐熱合金を700~750℃で2~20時間保持した後、600~650℃まで冷却する第一時効処理と、次いで600~650℃で2~20時間保持する第二時効処理を行うことができる。
表1に示すFe-Ni基超耐熱合金(718合金)に相当する化学組成のビレットを用いて950~1000℃の温度範囲内で据え込み鍛造を行った後、950~1000℃の温度範囲内でリング圧延を行った。次いで、前記熱合金に残留する歪を除去するべく、当該熱合金を980℃で1時間保持した後、室温まで空冷し、図3に示す小型圧縮試験片を作製して熱間加工試験を行った。この小型圧縮試験片を供試材として、熱間加工試験を行いAGGの発生に及ぼす因子を調査した。供試材の結晶粒度は、ASTM-E112で規定される測定で平均結晶粒度番号10番であった。
加熱温度を980℃、圧下率を10~50%、圧縮前の試験片の高さに対する圧縮速度より算出される公称歪速度を0.005~0.5/秒、圧縮後の冷却速度を540℃/分とする条件で、圧縮試験を行った。
その後、試験片に対して980℃で1時間の固溶化処理を行い、縦断面を光学顕微鏡で組織観察した。組織観察した部位での相当歪および相当歪速度は、市販の鍛造解析ソフトウェアDEFORMを使用して熱間加工試験を再現して割り出した。固溶化処理後の結晶粒度番号が9未満のときAGGの発現と判定した。表2に、圧縮試験条件、結晶粒度番号(ASTM)、およびAGGの判定結果を示す。
図1に示すように、相当歪速度が小さいほど領域(B)の幅が広くなったことから、AGGが起こる相当歪の範囲は大きくなることがわかった。図1の結果から、AGGを回避できる、相当歪と相当歪速度の下記の関係式を得た。下記関係式を満たすのが図1の領域(A)であり、この領域(A)で熱間加工を行うと、AGGの発現が防止できることを確認した。
表1に示す組成のFe-Ni基超耐熱合金(718合金)からなる800kgの熱間加工用素材を用いて、熱間鍛造を行った。熱間鍛造は、980~1000℃の温度範囲内の熱間加工用素材を、熱間加工用素材の全域で、相当歪が下記式の関係を満足するように行った。
熱間鍛造後、固溶化処理中の結晶粒成長をできる限り抑制することを目的として、表3に示す(a)~(f)の6条件の予備加熱および固溶化処理を行い、その後、718℃で8時間の第一時効処理および621℃で8時間の第二時効処理を行った。
Claims (5)
- 0.08質量%以下のCと、0.35質量%以下のSiと、0.35質量%以下のMnと、0.015質量%以下のPと、0.015質量%以下のSと、50.0~55.0質量%のNiと、17.0~21.0質量%のCrと、2.8~3.3質量%のMoと、1.0質量%以下のCoと、0.30質量%以下のCuと、0.20~0.80質量%のAlと、0.65~1.15質量%のTiと、4.75~5.50質量%のNb+Taと、0.006質量%以下のBと、残部がFeおよび不可避的な不純物からなる組成を有するFe-Ni基超耐熱合金の製造方法において、
前記組成を有する素材を熱間加工する熱間加工工程を少なくとも含み、
前記熱間加工工程は、930~1010℃の前記素材を、当該素材の全域で、[相当歪]≧0.139×[相当歪速度(/sec)]-0.30の関係を満足するように熱間加工する工程を少なくとも含む、Fe-Ni基超耐熱合金の製造方法。 - 前記熱間加工工程後、950~1000℃の範囲で0.5~10時間の固溶化処理を行う固溶化処理工程を含む、請求項1に記載のFe-Ni基超耐熱合金の製造方法。
- 前記熱間加工工程の後であって、前記固溶化処理工程の前に、600~930℃の範囲で5~60時間熱処理する熱処理工程を含む請求項2に記載のFe-Ni基超耐熱合金の製造方法。
- 前記固溶化処理工程後、700~750℃の範囲で2~20時間の第一時効処理を行う第一時効処理工程を含む請求項2または請求項3に記載のFe-Ni基超耐熱合金の製造方法。
- 前記第一時効処理工程後、600~650℃の範囲で2~20時間の第二時効処理を行う第二時効処理工程を含む請求項2~請求項4のいずれかに記載のFe-Ni基超耐熱合金の製造方法。
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WO2017170433A1 (ja) * | 2016-03-31 | 2017-10-05 | 日立金属株式会社 | Ni基超耐熱合金の製造方法 |
WO2023074613A1 (ja) * | 2021-10-25 | 2023-05-04 | 山陽特殊製鋼株式会社 | 積層造形に適したNi系合金粉末及び該粉末を用いて得られた積層造形体 |
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WO2020059797A1 (ja) | 2018-09-19 | 2020-03-26 | 日立金属株式会社 | Fe-Ni基超耐熱合金のリング圧延材の製造方法 |
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CN111748720B (zh) * | 2019-03-27 | 2021-09-24 | 中国科学院金属研究所 | 一种镍铁基合金的热加工工艺及应用 |
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