JP6970438B2 - Ni-based superalloy - Google Patents
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本発明は、ジェットエンジンやガスタービンの高温下で使用される部材に好適に用いられるＮｉ基超合金に関する。 The present invention relates to a Ni-based superalloy that is suitably used for members used in jet engines and gas turbines at high temperatures.
Ｎｉ基超合金は普通鋳造（ＣＣ：Conventional Casting）合金、一方向凝固（ＤＳ：Directional Solidification）合金、単結晶（ＳＣ：Single Crystal）合金と製造方法が変わり、それにつれて高温強度が改善され耐用温度が向上した。このうちの単結晶合金であるＮｉ基単結晶合金だけでも、初期の第１世代からＲｅを３重量％程度含む第２世代、Ｒｅを５重量％程度含む第３世代、さらにＲｅと白金族元素のＲｕを含む第４世代、第５世代、最新の第６世代と開発が進み耐用温度が向上している。最近ではＮｉ基超合金粉末を用いた３Ｄ加工技術による製造方法が新たに加わった。 The manufacturing method of Ni-based superalloys has changed from ordinary casting (CC: Conventional Casting) alloys, unidirectional solidification (DS: Directional Solidification) alloys, and single crystal (SC: Single Crystal) alloys. Has improved. Of these, the Ni-based single crystal alloy, which is a single crystal alloy, is the second generation containing about 3% by weight of Re from the initial first generation, the third generation containing about 5% by weight of Re, and Re and platinum group elements. Development is progressing with the 4th generation, 5th generation, and the latest 6th generation including Ru, and the durable temperature is improving. Recently, a new manufacturing method using 3D processing technology using Ni-based superalloy powder has been added.
ガスタービン機関の効率を向上させる目的でタービンガス入り口温度の高温化がなされている。これに伴い、ガスタービン機関のタービンブレードやタービンベーンとして使用されるＮｉ基超合金に、より高温に耐える強度が要求される。Ｎｉ基超合金に要求されるのは強度ばかりではない。従来硫化腐食が問題にならなかった部位も温度上昇とともに次第に硫化腐食温度域に入りつつある。第１世代から第６世代までのＮｉ基単結晶超合金の硫化腐食についての研究（非特許文献１参照）によると、第１世代のＮｉ基単結晶超合金の耐硫化腐食は他世代のＮｉ基単結晶超合金より特に劣ることが明らかとなっている。講演論文集には特に硫化腐食が問題となる温度域は低温側のタイプIIといわれる約７００℃と高温側のタイプIといわれる約９００℃の二つの温度域があり、これら温度域での硫化腐食挙動が記されている。 The temperature of the turbine gas inlet has been raised for the purpose of improving the efficiency of the gas turbine engine. Along with this, Ni-based superalloys used as turbine blades and turbine vanes of gas turbine engines are required to have strength to withstand higher temperatures. Strength is not the only requirement for Ni-based superalloys. The parts where sulfurization corrosion has not been a problem in the past are gradually entering the sulfurization corrosion temperature range as the temperature rises. According to the study on sulfide corrosion of Ni-based single crystal superalloys from the 1st generation to the 6th generation (see Non-Patent Document 1), the sulfide corrosion resistance of the 1st generation Ni-based single crystal superalloys is the Ni of other generations. It has been shown to be particularly inferior to the basic single crystal superalloy. In the collection of lecture papers, there are two temperature ranges in which sulfurization corrosion is particularly problematic: about 700 ° C, which is called type II on the low temperature side, and about 900 ° C, which is called type I on the high temperature side. Corrosion behavior is noted.
第１世代に相当するＮｉ基単結晶超合金として、ＲｅｎeＮ４（商標、特許文献１参照）、ＰＷＡ１４８０（商標、非特許文献２の参考文献１０参照）、ＴＭＳ−１７００（商標、特許文献２参照）が知られている。 As Ni-based single crystal superalloys corresponding to the first generation, ReneN4 (trademark, see Patent Document 1), PWA1480 (trademark, see Reference 10 of Non-Patent Document 2), TMS-1700 (trademark, see Patent Document 2). It has been known.
これらＲｅｎeＮ４（商標）、ＰＷＡ１４８０（商標）およびＴＭＳ−１７００（商標）の第１世代Ｎｉ基単結晶超合金は耐腐食性に対して効果があると一般に言われるＣｒ量が多いにもかかわらず第２世代のＣｒ量が少ないＮｉ基単結晶超合金より耐硫化腐食性が良くないことから改善が求められている。また、一般に耐硫化腐食性は合金組成で決定づけられ、製造方法により大差がつくことはない。 These ReneN4 ™, PWA1480 ™ and TMS-1700 ™ first generation Ni-based single crystal superalloys are generally said to be effective for corrosion resistance, despite the large amount of Cr. Since the sulfide corrosion resistance is not as good as that of the Ni-based single crystal superalloy having a small amount of Cr in the second generation, improvement is required. Further, the sulfurization corrosion resistance is generally determined by the alloy composition, and does not make a big difference depending on the manufacturing method.
本発明は、従来の第１世代Ｎｉ基超合金に比べ高温でのクリープ特性および耐硫化腐食に優れており、製造コストは従来の第２世代より低いコストでのＮｉ基超合金を提供することを課題としている。 INDUSTRIAL APPLICABILITY The present invention provides a Ni-based superalloy that is superior in creep characteristics and sulfide corrosion resistance at high temperatures as compared with the conventional first-generation Ni-based superalloy, and has a lower manufacturing cost than the conventional second-generation Ni-based superalloy. Is an issue.
上記のとおりの課題を解決するために、本発明は、以下のとおりの特徴を有している。 In order to solve the above-mentioned problems, the present invention has the following features.
すなわち、本発明のＮｉ基超合金は、
Ｃｒ：６質量％以上１２質量％以下、
Ｍｏ：０．４質量％以上３．０質量％以下、
Ｗ：６質量％以上１０質量％以下、
Ａｌ：４．０質量％以上６．５質量％以下、
Ｔａ：８質量％以上１２質量％以下、
Ｒｅ：０．０１質量％以上１．０質量％以下、および
Ｓｉ：０．０１質量％以上０．２質量％以下、
を必須組成元素として含有し、残部がＮｉおよび不可避的不純物からなるＮｉ基超合金であって、任意的組成元素として下記の元素を含有する。
Ｃｏ：０質量％以上３質量％以下、
Ｔｉ：０質量％以上１質量％以下、
Ｎｂ：０質量％以上１質量％以下、
Ｈｆ：０質量％以上０．１５質量％以下、
Ｚｒ：０質量％以上０．０４質量％以下、
Ｂ：０質量％以上０．０３質量％以下、
Ｃ：０質量％以上０．３質量％以下。
That is, the Ni-based superalloy of the present invention is
Cr: 6% by mass or more and 12% by mass or less,
Mo: 0.4% by mass or more and 3.0% by mass or less,
W: 6% by mass or more and 10% by mass or less,
Al: 4.0% by mass or more and 6.5% by mass or less,
Ta: 8% by mass or more and 12% by mass or less,
Re: 0.01% by mass or more and 1.0% by mass or less, and Si: 0.01% by mass or more and 0.2% by mass or less,
Is a Ni-based superalloy consisting of Ni and unavoidable impurities as the balance, and contains the following elements as optional composition elements.
Co: 0% by mass or more and 3% by mass or less,
Ti: 0% by mass or more and 1% by mass or less,
Nb: 0% by mass or more and 1% by mass or less,
Hf: 0% by mass or more and 0.15% by mass or less,
Zr: 0% by mass or more and 0.04% by mass or less,
B: 0% by mass or more and 0.03% by mass or less,
C: 0% by mass or more and 0.3% by mass or less.
また、本発明のＮｉ基超合金は、
Ｃｒ：７質量％以上１２質量％以下、
Ｍｏ：０．４質量％以上２．５質量％以下、
Ｗ：７質量％以上１０質量％以下、
Ａｌ：４．０質量％以上６．５質量％以下、
Ｔａ：９質量％以上１１質量％以下、
Ｒｅ：０．０８質量％以上０．９５質量％以下、および
Ｓｉ：０．０１質量％以上０．２質量％以下、
を必須組成元素として含有し、残部がＮｉおよび不可避的不純物からなるＮｉ基超合金であって、任意的組成元素として下記の元素を含有する。
Ｃｏ：０質量％以上３質量％以下、
Ｔｉ：０質量％以上１質量％以下、
Ｎｂ：０質量％以上１質量％以下、
Ｈｆ：０質量％以上０．１５質量％以下、
Ｚｒ：０質量％以上０．０４質量％以下、
Ｂ：０質量％以上０．０３質量％以下、
Ｃ：０質量％以上０．３質量％以下。
Further, the Ni-based superalloy of the present invention is used.
Cr: 7% by mass or more and 12% by mass or less,
Mo: 0.4% by mass or more and 2.5% by mass or less,
W: 7% by mass or more and 10% by mass or less,
Al: 4.0% by mass or more and 6.5% by mass or less,
Ta: 9% by mass or more and 11% by mass or less,
Re: 0.08% by mass or more and 0.95% by mass or less, and Si: 0.01% by mass or more and 0.2% by mass or less,
Is a Ni-based superalloy consisting of Ni and unavoidable impurities as the balance, and contains the following elements as optional composition elements.
Co: 0% by mass or more and 3% by mass or less,
Ti: 0% by mass or more and 1% by mass or less,
Nb: 0% by mass or more and 1% by mass or less,
Hf: 0% by mass or more and 0.15% by mass or less,
Zr: 0% by mass or more and 0.04% by mass or less,
B: 0% by mass or more and 0.03% by mass or less,
C: 0% by mass or more and 0.3% by mass or less.
また、本発明のＮｉ基超合金は、
Ｃｒ：８質量％以上１０質量％以下、
Ｍｏ：０．４質量％以上２．０質量％以下、
Ｗ：７質量％以上９質量％以下、
Ａｌ：４．０質量％以上６．５質量％以下、
Ｔａ：１０質量％以上１１質量％以下、
Ｒｅ：０．１質量％以上０．９質量％以下、および
Ｓｉ：０．０１質量％以上０．２質量％以下、
を必須組成元素として含有し、残部がＮｉおよび不可避的不純物からなるＮｉ基超合金であって、任意的組成元素として下記の元素を含有する。
Ｃｏ：０質量％以上３質量％以下、
Ｔｉ：０質量％以上１質量％以下、
Ｎｂ：０質量％以上１質量％以下、
Ｈｆ：０質量％以上０．１５質量％以下、
Ｚｒ：０質量％以上０．０４質量％以下、
Ｂ：０質量％以上０．０３質量％以下、
Ｃ：０質量％以上０．３質量％以下。
Further, the Ni-based superalloy of the present invention is used.
Cr: 8% by mass or more and 10% by mass or less,
Mo: 0.4% by mass or more and 2.0% by mass or less,
W: 7% by mass or more and 9% by mass or less,
Al: 4.0% by mass or more and 6.5% by mass or less,
Ta: 10% by mass or more and 11% by mass or less,
Re: 0.1% by mass or more and 0.9% by mass or less, and Si: 0.01% by mass or more and 0.2% by mass or less,
Is a Ni-based superalloy consisting of Ni and unavoidable impurities as the balance, and contains the following elements as optional composition elements.
Co: 0% by mass or more and 3% by mass or less,
Ti: 0% by mass or more and 1% by mass or less,
Nb: 0% by mass or more and 1% by mass or less,
Hf: 0% by mass or more and 0.15% by mass or less,
Zr: 0% by mass or more and 0.04% by mass or less,
B: 0% by mass or more and 0.03% by mass or less,
C: 0% by mass or more and 0.3% by mass or less.
本発明のＮｉ基超合金において、温度８００℃で応力７３５ＭＰａにおけるクリープ寿命が１９６時間以上である。 In the Ni-based superalloy of the present invention, the creep life at a temperature of 800 ° C. and a stress of 735 MPa is 196 hours or more.
本発明のＮｉ基超合金において、温度９００℃で応力３９２ＭＰａにおけるクリープ寿命が２６７時間以上である。 In the Ni-based superalloy of the present invention, the creep life at a temperature of 900 ° C. and a stress of 392 MPa is 267 hours or more.
本発明のＮｉ基超合金において、温度１０００℃で応力２４５ＭＰａにおけるクリープ寿命が８１時間以上である。 In the Ni-based superalloy of the present invention, the creep life at a temperature of 1000 ° C. and a stress of 245 MPa is 81 hours or more.
本発明のＮｉ基超合金において、温度１１００℃で応力１３７ＭＰａにおけるクリープ寿命が２３７時間以上である。 In the Ni-based superalloy of the present invention, the creep life at a temperature of 1100 ° C. and a stress of 137 MPa is 237 hours or more.
本発明のＮｉ基超合金において、所定条件のるつぼ試験において温度７００℃で５０時間保持の腐食表面積割合が９０％以下であり９００℃で２０時間保持のメタルロスが２．０ｍｍ以下であるＮｉ基超合金。 In the Ni-based superalloy of the present invention, the corrosion surface area ratio of holding at a temperature of 700 ° C. for 50 hours is 90% or less and the metal loss of holding at 900 ° C. for 20 hours is 2.0 mm or less in a crucible test under predetermined conditions. alloy.
本発明のＮｉ基超合金を用いて、普通鋳造法、一方向凝固法、単結晶凝固法、粉末を用いた焼結および３Ｄ造形法の何れかにより作成したタービン部材。 A turbine member produced by any of the ordinary casting method, the one-way solidification method, the single crystal solidification method, the sintering using powder, and the 3D modeling method using the Ni-based superalloy of the present invention.
本発明のＮｉ基超合金は、従来の第１世代Ｎｉ基超合金に比べ高温でのクリープ特性および耐硫化腐食に優れており、製造コストは従来の第２世代より低いコストで提供できる。 The Ni-based superalloy of the present invention is superior in creep characteristics and sulfide corrosion resistance at high temperatures as compared with the conventional first-generation Ni-based superalloy, and can be provided at a lower manufacturing cost than the conventional second-generation.
上記のとおりの特徴を有するＮｉ基超合金における組成成分およびその組成比は、以下の観点に基づいている。
Ｃｒ（クロム）は、Ｎｉ基超合金の高温耐食性および高温耐酸化性を向上させる。Ｃｒの組成比は、６質量％以上１２質量％以下である。組成比が、６質量％未満であると、高温耐食性および高温耐酸化性を確保することが難しく、１２質量％を超えると、σ相やμ相の有害相が生成して高温強度が低下する。Ｃｒの組成比は、好ましくは７質量％以上１２質量％以下であり、より好ましくは８質量％以上１０質量％以下である。
The compositional components and composition ratios thereof in the Ni-based superalloy having the above-mentioned characteristics are based on the following viewpoints.
Cr (chromium) improves the high temperature corrosion resistance and high temperature oxidation resistance of Ni-based superalloys. The composition ratio of Cr is 6% by mass or more and 12% by mass or less. If the composition ratio is less than 6% by mass, it is difficult to secure high-temperature corrosion resistance and high-temperature oxidation resistance, and if it exceeds 12% by mass, harmful phases of σ phase and μ phase are generated and the high temperature strength is lowered. .. The composition ratio of Cr is preferably 7% by mass or more and 12% by mass or less, and more preferably 8% by mass or more and 10% by mass or less.
Ｍｏ（モリブデン）は、素地中に固溶し、かつ析出硬化により高温強度の上昇に寄与する。Ｍｏの組成比は、０．４質量％以上３．０質量％以下である。組成比が、０．４質量％未満であると、高温強度が低下し、３．０質量％を超えると、有害相が生成して高温強度が低下する。Ｍｏの組成比は、好ましくは０．４質量％以上２．５質量％以下であり、より好ましくは０．４質量％以上２．０質量％以下である。 Mo (molybdenum) dissolves in the substrate and contributes to an increase in high-temperature strength by precipitation hardening. The composition ratio of Mo is 0.4% by mass or more and 3.0% by mass or less. If the composition ratio is less than 0.4% by mass, the high temperature intensity is lowered, and if it exceeds 3.0% by mass, a harmful phase is generated and the high temperature strength is lowered. The composition ratio of Mo is preferably 0.4% by mass or more and 2.5% by mass or less, and more preferably 0.4% by mass or more and 2.0% by mass or less.
Ｗ（タングステン）は、Ｍｏと同様に、固溶強化および析出硬化の作用があり、Ｎｉ基超合金の高温強度を向上させる。Ｗの組成比は、６質量％以上１０質量％以下である。組成比が、６質量％未満であると、ＴＭＦ特性およびクリープ特性が低下し、１０質量％を超えると、有害相が生成してＴＭＦ特性およびクリープ特性が低下する。Ｗの組成比は、好ましくは７質量％以上１０質量％以下であり、より好ましくは７質量％以上９質量％以下である。
ここで、ＴＭＦ特性とは、熱疲労（Thermo-mechanical fatigue）特性をいい、例えばタービン動翼における多軸熱疲労条件下でのき裂発生寿命（深さ２ｍｍ程度のき裂）を指す。クリープ特性とは、材料のクリープ強さであり、クリープ試験又はクリープ破断試験が用いられる。クリープ破断試験は、ある応力のもとで破断するまでの時間を求めることを目的とし、試験機にはマルチプル型（１試験機あたり多数の試験片）が多く使用されるが、シングル型（１試験機あたり単一の試験片）でもよい。
Like Mo, W (tungsten) has the effects of solid solution strengthening and precipitation hardening, and improves the high-temperature strength of Ni-based superalloys. The composition ratio of W is 6% by mass or more and 10% by mass or less. If the composition ratio is less than 6% by mass, the TMF characteristics and creep characteristics are deteriorated, and if it exceeds 10% by mass, a harmful phase is generated and the TMF characteristics and creep characteristics are deteriorated. The composition ratio of W is preferably 7% by mass or more and 10% by mass or less, and more preferably 7% by mass or more and 9% by mass or less.
Here, the TMF characteristic refers to a thermal fatigue characteristic, for example, a crack generation life (crack having a depth of about 2 mm) under multiaxial thermal fatigue conditions in a turbine blade. The creep property is the creep strength of a material, and a creep test or a creep rupture test is used. The creep rupture test aims to determine the time until rupture under a certain stress, and the multiple type (many test pieces per tester) is often used for the testing machine, but the single type (1). It may be a single test piece per tester).
Ａｌ（アルミニウム）は、Ｎｉと化合して、ガンマ母相中に析出するガンマプライム相を構成するＮｉ３Ａｌで示される金属間化合物を形成し、特に１０００℃以下の低温側のＴＭＦ特性およびクリープ特性を向上させる。Ａｌの組成比は、４．０質量％以上６．５質量％以下である。組成比が、４質量％未満であると、ガンマプライム相量が少なく、要求されるＴＭＦ特性およびクリープ特性が得られず、６．５質量％を超えると、要求されるＴＭＦ特性およびクリープ特性が得られない。 Al (aluminum) combines with Ni to form an intermetallic compound represented by Ni 3 Al that constitutes the gamma prime phase that precipitates in the gamma matrix, and in particular, TMF characteristics and creep on the low temperature side of 1000 ° C. or lower. Improve characteristics. The composition ratio of Al is 4.0% by mass or more and 6.5% by mass or less. When the composition ratio is less than 4% by mass, the amount of gamma prime phase is small and the required TMF characteristics and creep characteristics cannot be obtained, and when it exceeds 6.5% by mass, the required TMF characteristics and creep characteristics are obtained. I can't get it.
Ｔａ（タンタル）は、ガンマプライム相を強化してクリープ特性を向上させる。Ｔａの組成比は、８質量％以上１２質量％以下である。組成比が、８質量％未満であると、要求されるＴＭＦ特性およびクリープ特性が得られず、１２質量％を超えると、共晶ガンマプライム相の生成を促し、溶体化熱処理が困難となる。Ｔａの組成比は、好ましくは９質量％以上１１質量％以下であり、より好ましくは１０質量％以上１１質量％以下である。 Ta enhances the gamma prime phase and improves creep properties. The composition ratio of Ta is 8% by mass or more and 12% by mass or less. If the composition ratio is less than 8% by mass, the required TMF characteristics and creep characteristics cannot be obtained, and if it exceeds 12% by mass, the formation of a eutectic gamma prime phase is promoted, and solution heat treatment becomes difficult. The composition ratio of Ta is preferably 9% by mass or more and 11% by mass or less, and more preferably 10% by mass or more and 11% by mass or less.
Ｒｅ（レニウム）は、ガンマ相に固溶して固溶強化により高温強度を向上させるだけでなく耐食性を向上させる効果もある。ただ、Ｒｅを多量に含有すると、高温時にＴＣＰ相が析出して高温強度を低下させるおそれがある。また、Ｒｅは高価でありコストパフォーマンスの点から少量で高温強度と耐食性に効果が発揮されることが望ましい。ＴＣＰ相の析出を抑制し有害相の生成しないＲｅの範囲を絞り込む必要がある。そのためには他の添加元素とのバランスが必要であり、本発明の各元素の請求範囲でのＲｅは、０．０１質量％以上１．０質量％以下である。さらに好ましくは０．０８質量％以上０．９５質量％以下である。より好ましくは０．１質量％以上０．９質量％以下である。
ここで、ＴＣＰ相とは、topological close-packed phaseの略称であり、Frank-Kasper (FK) phasesともいい、Ｎｉ基超合金の場合はσ相やμ相をいう。
Re (rhenium) not only improves high-temperature strength by solid-solving in the gamma phase and strengthening the solid solution, but also has the effect of improving corrosion resistance. However, if a large amount of Re is contained, the TCP phase may precipitate at high temperatures to reduce the high temperature intensity. Further, Re is expensive, and it is desirable that a small amount of Re is effective in high temperature strength and corrosion resistance from the viewpoint of cost performance. It is necessary to suppress the precipitation of the TCP phase and narrow down the range of Re that does not generate a harmful phase. For that purpose, a balance with other additive elements is required, and Re in the claims of each element of the present invention is 0.01% by mass or more and 1.0% by mass or less. More preferably, it is 0.08% by mass or more and 0.95% by mass or less. More preferably, it is 0.1% by mass or more and 0.9% by mass or less.
Here, the TCP phase is an abbreviation for a topological close-packed phase, also referred to as a Frank-Kasper (FK) phase, and in the case of a Ni-based superalloy, it means a σ phase or a μ phase.
Ｓｉ（ケイ素）は、合金表面にＳｉＯ２皮膜を生成させて保護被膜として耐酸化性を向上させ、かつ合金表面からの微少クラックの発生を抑制してＴＭＦ特性を改善する可能性がある。Ｓｉの組成比は、０．０１質量％以上０．２質量％以下である。組成比が０．０１質量％未満であると、耐酸化性の向上、ＴＭＦ特性の改善の効果が得られない。また、組成比が０．２質量％を超えると、他の元素の固溶限を低下させることになるため、要求されるＴＭＦ特性およびクリープ特性が得られない。 Si (silicon) may form a SiO 2 film on the alloy surface to improve oxidation resistance as a protective film, and may suppress the generation of minute cracks from the alloy surface to improve TMF characteristics. The composition ratio of Si is 0.01% by mass or more and 0.2% by mass or less. If the composition ratio is less than 0.01% by mass, the effects of improving the oxidation resistance and the TMF characteristics cannot be obtained. Further, if the composition ratio exceeds 0.2% by mass, the solid solution limit of other elements is lowered, so that the required TMF characteristics and creep characteristics cannot be obtained.
Ｃｏ（コバルト）は、Ａｌ、Ｔａ等の母相に対する高温下での固溶限度を大きくし、熱処理によって微細なγ’相を分散析出させ、高温強度を向上させる。Ｃｏの組成比は、任意的組成元素とし、０質量％以上３質量％以下である。組成比が、３質量％を超えると、所望の高温強度を確保できないので好ましくない。 Co (cobalt) increases the solid solution limit of the matrix phase such as Al and Ta at high temperature, disperses and precipitates fine γ'phase by heat treatment, and improves the high temperature strength. The composition ratio of Co is an arbitrary composition element, and is 0% by mass or more and 3% by mass or less. If the composition ratio exceeds 3% by mass, the desired high-temperature strength cannot be secured, which is not preferable.
Ｔｉ（チタン）は、ガンマプライム相を強化してクリープ特性を向上させる。Ｔｉの組成比は、任意的組成元素とし、０質量％以上１質量％以下である。組成比が、１質量％を超えると、所望の高温強度を確保できないので好ましくない。 Ti (titanium) enhances the gamma prime phase and improves creep characteristics. The composition ratio of Ti is an arbitrary composition element, and is 0% by mass or more and 1% by mass or less. If the composition ratio exceeds 1% by mass, the desired high-temperature strength cannot be secured, which is not preferable.
Ｎｂ（ニオブ）の組成比は、任意的組成元素とし、０質量％以上１質量％以下である。組成比が、１質量％を超えると、高温において有害相が生成し、ＴＭＦ特性およびクリープ特性が低下する。 The composition ratio of Nb (niobium) is an arbitrary composition element, and is 0% by mass or more and 1% by mass or less. When the composition ratio exceeds 1% by mass, a harmful phase is generated at a high temperature, and TMF characteristics and creep characteristics are deteriorated.
Ｈｆ（ハフニウム）は、普通凝固および一方向凝固による柱状結晶化の際、粒界強化に寄与するものであり、かつ耐酸化性を向上させ、そのうえＴＭＦ特性を改善する可能性がある。また、単結晶で用いる場合も何らかの理由で、再結晶してしまっても粒界が弱くなるのを防ぐことが可能である。Ｈｆの組成比は、任意的組成元素とし、０質量％以上０．１５質量％以下である。組成比が、０．１５質量％を超えると、有害相の生成が助長され、ＴＭＦ特性およびクリープ特性が低下する。 Hf (hafnium) contributes to the strengthening of grain boundaries during columnar crystallization by normal solidification and unidirectional solidification, and has the potential to improve oxidation resistance and TMF characteristics. Further, even when it is used as a single crystal, it is possible to prevent the grain boundaries from becoming weak even if it is recrystallized for some reason. The composition ratio of Hf is an arbitrary composition element, and is 0% by mass or more and 0.15% by mass or less. When the composition ratio exceeds 0.15% by mass, the formation of harmful phases is promoted, and the TMF characteristics and creep characteristics are deteriorated.
Ｚｒ（ジルコニウム）は、普通凝固および一方向凝固による柱状結晶化の際、結晶粒界に偏析し、粒界強度を高める効果があるが、ほとんどは合金の主成分であるニッケルと金属間化合物Ｎｉ３Ｚｒを形成する。この化合物は合金の延性を低下させ、また著しく低融点であるため、合金の溶体化処理を困難にするなど、有害な作用が多い。そのため、Ｚｒの組成比は、任意的組成元素とし、０質量％以上０．０４質量％以下である。 Zr (zirconium) has the effect of segregating at grain boundaries and increasing grain boundary strength during columnar crystallization by normal solidification and unidirectional solidification, but most of them are nickel, which is the main component of the alloy, and the intermetallic compound Ni. Form 3 Zr. Since this compound lowers the ductility of the alloy and has a remarkably low melting point, it has many harmful effects such as making it difficult to dissolve the alloy. Therefore, the composition ratio of Zr is 0% by mass or more and 0.04% by mass or less, with an arbitrary composition element.
Ｂ（ホウ素）は普通凝固および一方向凝固による柱状結晶化の際、結晶粒界に偏析して粒界強度を向上させるとともに、一部は（Ｃｒ、Ｎｉ、Ｍｏ）３Ｂ２等のホウ化物を形成し、合金の粒界に析出する。粒界強化の効果が得られるには０．０１％以上の添加が必要であるが、生成するホウ化物は融点が合金の融点よりも低く、合金の融点温度を低下させ、溶体化処理温度範囲を狭くする。そのため、任意的組成元素とし、Ｂの組成比は０質量％以上０．０３質量％以下である。 B (boron) segregates at grain boundaries during columnar crystallization by normal solidification and unidirectional solidification to improve grain boundary strength, and some are boroforms such as (Cr, Ni, Mo) 3 B 2. Is formed and precipitates at the grain boundaries of the alloy. Although it is necessary to add 0.01% or more to obtain the effect of strengthening the grain boundary, the boride produced has a melting point lower than the melting point of the alloy, lowers the melting point temperature of the alloy, and has a solution treatment temperature range. Narrow. Therefore, it is an arbitrary composition element, and the composition ratio of B is 0% by mass or more and 0.03% by mass or less.
Ｃ（炭素）は結晶粒界に偏析して粒界強度を向上させ、一部はＴａＣ等の炭化物を形成して塊状に析出する。結晶粒界に偏析して粒界強度を上げる場合には、０．０８％以上の添加をするとよい。しかし、０．３％を超えて添加すると過剰の炭化物が形成され、高温強度や延性が低下し、耐食性も低下する。また、凝固時における炭化物の晶出温度が高くなることから、デンドライト間に炭化物がピニングされ、鋳造欠陥であるポロシティの生成を招きうる。そのため、任意的組成元素とし、Ｃの組成比は０質量％以上０．３質量％以下である。 C (carbon) segregates at the grain boundaries to improve the grain boundary strength, and a part of it forms carbides such as TaC and precipitates in a lump form. When segregating at the grain boundaries to increase the grain boundary strength, it is advisable to add 0.08% or more. However, if it is added in excess of 0.3%, excess carbide is formed, the high temperature strength and ductility are lowered, and the corrosion resistance is also lowered. In addition, since the crystallization temperature of the carbide during solidification becomes high, the carbide is pinned between the dendrites, which may lead to the formation of porosity, which is a casting defect. Therefore, it is an arbitrary composition element, and the composition ratio of C is 0% by mass or more and 0.3% by mass or less.
なお、単結晶凝固法により作成するタービンブレードやタービンベーン部品では以下のような熱処理を施して製造することができる。すなわち、熱処理は、１２８０℃〜１３００℃で２時間〜４０時間保持後に２００℃／ｍｉｎ〜４００℃／ｍｉｎで空冷または不活性ガス雰囲気中で冷却する溶体化処理、１０００℃〜１１５０℃で２時間〜５時間保持後に空冷または不活性ガス雰囲気中で冷却する１次時効処理、そして８５０℃〜９５０℃で１０時間〜３０時間保持後に空冷または不活性ガス雰囲気中で冷却する２次時効処理という一連のものである。 Turbine blades and turbine vane parts produced by the single crystal solidification method can be manufactured by subjecting the following heat treatments. That is, the heat treatment is a solution treatment in which the mixture is held at 1280 ° C to 1300 ° C for 2 hours to 40 hours and then cooled by air cooling at 200 ° C / min to 400 ° C / min or in an inert gas atmosphere, and is cooled at 1000 ° C to 1150 ° C for 2 hours. A series of primary aging treatments in which air cooling or cooling in an inert gas atmosphere is performed after holding for ~ 5 hours, and secondary aging treatment in which cooling is performed in an air cooling or inert gas atmosphere after holding at 850 ° C. to 950 ° C. for 10 hours to 30 hours. belongs to.
また、普通鋳造法により作成するタービンブレードやタービンベーン部品では以下のような熱処理を施して製造することができる。すなわち、熱処理は、１２００℃〜１３００℃で２時間〜４０時間保持後に１５０℃／ｍｉｎ〜４００℃／ｍｉｎで空冷または不活性ガス雰囲気中で冷却する溶体化処理、１０００℃〜１１５０℃で２時間〜５時間保持後に空冷または不活性ガス雰囲気中で冷却する１次時効処理、そして８００℃〜９５０℃で１０時間〜３０時間保持後に空冷または不活性ガス雰囲気中で冷却する２次時効処理という一連のものである。 In addition, turbine blades and turbine vane parts produced by the ordinary casting method can be manufactured by subjecting the following heat treatments. That is, the heat treatment is a solution treatment in which the mixture is held at 1200 ° C. to 1300 ° C. for 2 hours to 40 hours and then air-cooled at 150 ° C./min to 400 ° C./min or cooled in an inert gas atmosphere, and is cooled at 1000 ° C. to 1150 ° C. for 2 hours. A series of primary aging treatments in which air cooling or cooling in an inert gas atmosphere is performed after holding for ~ 5 hours, and secondary aging treatment in which cooling is performed in an air cooling or inert gas atmosphere after holding at 800 ° C. to 950 ° C. for 10 hours to 30 hours. belongs to.
また、一方向凝固法により作成するタービンブレードやタービンベーン部品では以下のような熱処理を施して製造することができる。すなわち、熱処理は、１２００℃〜１３００℃で２時間〜４０時間保持後に２００℃／ｍｉｎ〜４００℃／ｍｉｎで空冷または不活性ガス雰囲気中で冷却する溶体化処理、１０００℃〜１１５０℃で２時間〜５時間保持後に空冷または不活性ガス雰囲気中で冷却する１次時効処理、そして８００℃〜９５０℃で１０時間〜３０時間保持後に空冷または不活性ガス雰囲気中で冷却する２次時効処理という一連のものである。 In addition, turbine blades and turbine vane parts produced by the one-way solidification method can be manufactured by subjecting the following heat treatments. That is, the heat treatment is a solution treatment in which the mixture is held at 1200 ° C. to 1300 ° C. for 2 hours to 40 hours and then air-cooled at 200 ° C./min to 400 ° C./min or cooled in an inert gas atmosphere, and is cooled at 1000 ° C. to 1150 ° C. for 2 hours. A series of primary aging treatments in which air cooling or cooling in an inert gas atmosphere is performed after holding for ~ 5 hours, and secondary aging treatment in which cooling is performed in an air cooling or inert gas atmosphere after holding at 800 ° C. to 950 ° C. for 10 hours to 30 hours. belongs to.
さらに、本発明のＮｉ基超合金粉末を用いて焼結または３Ｄ造形で作成されたタービンブレードやタービンベーン部品では以下のような熱処理を施して製造することができる。すなわち、熱処理は、１２００℃〜１３００℃で２時間〜４０時間保持後に２００℃／ｍｉｎ〜４００℃／ｍｉｎで空冷または不活性ガス雰囲気中で冷却する溶体化処理、１０００℃〜１１５０℃で２時間〜５時間保持後に空冷または不活性ガス雰囲気中で冷却する１次時効処理、そして８５０℃〜９５０℃で１０時間〜３０時間保持後に空冷または不活性ガス雰囲気中で冷却する２次時効処理という一連のものである。 Further, turbine blades and turbine vane parts produced by sintering or 3D modeling using the Ni-based superalloy powder of the present invention can be manufactured by subjecting the following heat treatments. That is, the heat treatment is a solution treatment in which the mixture is held at 1200 ° C. to 1300 ° C. for 2 hours to 40 hours and then air-cooled at 200 ° C./min to 400 ° C./min or cooled in an inert gas atmosphere, and is cooled at 1000 ° C. to 1150 ° C. for 2 hours. A series of primary aging treatments in which air cooling or cooling in an inert gas atmosphere is performed after holding for ~ 5 hours, and secondary aging treatment in which cooling is performed in an air cooling or inert gas atmosphere after holding at 850 ° C. to 950 ° C. for 10 hours to 30 hours. belongs to.
このような一連の所定温度で所定時間の保持は、すべて真空中または不活性ガス雰囲気中で行うことが、高温酸化の影響を受けないという観点からも好ましい。 It is preferable to hold the series at a predetermined temperature for a predetermined time in a vacuum or in an atmosphere of an inert gas from the viewpoint of not being affected by high temperature oxidation.
以下、実施例を示し、本発明のＮｉ基超合金についてさらに詳しく説明する。 Hereinafter, examples will be shown and the Ni-based superalloy of the present invention will be described in more detail.
表１に示した組成（質量％）を有するＮｉ基単結晶超合金を、真空溶解炉を用いて溶解し、加熱保持されたロストワックス鋳型で鋳造し、鋳型を２００ｍｍ／ｈの凝固速度で引き下げて単結晶凝固鋳造物を得た。次に、得られた単結晶凝固鋳造物を真空中において１３２０℃で５時間保持してから約３００℃／ｍｉｎで空冷する溶体化処理を行った。その後、真空中において１１００℃で２時間保持してから空冷する１次時効処理と、真空中において８７０℃で２４時間保持してから空冷する２次時効処理とを行った。 The Ni-based single crystal superalloy having the composition (% by mass) shown in Table 1 was melted using a vacuum melting furnace, cast in a heat-held lost wax mold, and the mold was pulled down at a solidification rate of 200 mm / h. A single crystal solidified casting was obtained. Next, the obtained single crystal solidified casting was held in vacuum at 1320 ° C. for 5 hours and then air-cooled at about 300 ° C./min for solution treatment. Then, a primary aging treatment in which the product was held at 1100 ° C. for 2 hours in a vacuum and then air-cooled, and a secondary aging treatment in which the product was held in a vacuum at 870 ° C. for 24 hours and then air-cooled were performed.
実施例Ｎｏ．１および実施例Ｎｏ．２のＮｉ基単結晶超合金の溶体化処理の温度範囲は１２８０℃〜１３４０℃であり、１次時効処理の温度範囲は１０００℃〜１１５０℃である。比較合金Ｎｏ．３および比較合金Ｎｏ．４は、１２８０℃で１時間保持してから１３２０℃に昇温し５時間保持後に空冷した。次いで１１００℃に４時間保持してから空冷し、この後、８７０℃に２０時間保持して空冷する熱処理を施した。比較合金Ｎｏ．５の熱処理は、１１３０℃で１時間保持してから１１８０℃に昇温し２時間保持後に空冷し、その後１０５０℃に４時間保持してから空冷し、この後、８７０℃に２０時間保持して空冷する熱処理を施した。 Example No. 1 and Example No. The temperature range of the solution treatment of the Ni-based single crystal superalloy of No. 2 is 1280 ° C to 1340 ° C, and the temperature range of the primary aging treatment is 1000 ° C to 1150 ° C. Comparative Alloy No. 3 and Comparative Alloy No. No. 4 was held at 1280 ° C. for 1 hour, then heated to 1320 ° C., held for 5 hours, and then air-cooled. Then, it was held at 1100 ° C. for 4 hours and then air-cooled, and then it was held at 870 ° C. for 20 hours and air-cooled. Comparative Alloy No. The heat treatment of No. 5 was carried out at 1130 ° C. for 1 hour, then heated to 1180 ° C., held for 2 hours and then air-cooled, then held at 1050 ° C. for 4 hours and then air-cooled, and then held at 870 ° C. for 20 hours. It was heat-treated to be air-cooled.
硫化腐食が問題となる低温側のタイプIIといわれる約７００℃での耐硫化腐食性については、るつぼ試験法による加速試験を実施し検討した。
るつぼ試験に用いた溶融塩組成は、通常最もよく用いられる７５％Ｎａ２ＳＯ４＋２５％ＮａＣｌとした。この組成の混合塩１２ｇを容量１５ｍｌのアルミナ磁製るつぼ中で７００℃に溶融させ、試験片（φ９ｍｍ×５ｍｍ）を全浸漬させた。なお、試験片表面はあらかじめエメリー紙＃６００まで研磨した後、試験片をアセトンで洗浄して腐食試験に供した。腐食試験時間は５０ｈとし、試験終了後の腐食表面積を求めて試験結果とした。図1に結果を示す。実施例Ｎｏ．１および実施例Ｎｏ．２は比較合金Ｎｏ．３、比較合金Ｎｏ．４および比較合金Ｎｏ．５のいずれより腐食面積率が少なく耐硫化性の良いことが明らかである。
The resistance to sulfurization at about 700 ° C, which is called type II on the low temperature side where sulfurization corrosion is a problem, was examined by conducting an accelerated test using the crucible test method.
The molten salt composition used in the crucible test was 75% Na 2 SO 4 + 25% NaCl, which is usually the most commonly used. 12 g of the mixed salt having this composition was melted at 700 ° C. in an alumina porcelain crucible having a capacity of 15 ml, and the test piece (φ9 mm × 5 mm) was completely immersed. The surface of the test piece was polished to emery paper # 600 in advance, and then the test piece was washed with acetone and subjected to a corrosion test. The corrosion test time was 50 hours, and the corroded surface area after the end of the test was obtained and used as the test result. Figure 1 shows the results. Example No. 1 and Example No. 2 is the comparative alloy No. 3. Comparative alloy No. 4 and Comparative Alloy No. It is clear that the corrosion area ratio is smaller than that of any of 5 and the sulfurization resistance is good.
高温側のタイプIといわれる約９００℃での耐硫化腐食性については供試合金、溶融塩組成、るつぼ容量、試験形状は低温側の試験条件と同様である。高温側（タイプI）の硫化腐食試験は試験温度９００℃、試験時間を２０ｈとした。試験終了後スケールをワイヤブラシでおとして重量減（％）を測定し、これを表面からの金属の消耗量に換算して試験結果とし図２に示す。実施例Ｎｏ．１および実施例Ｎｏ．２は比較合金Ｎｏ．３、比較合金Ｎｏ．４および比較合金Ｎｏ．５のいずれよりメタルロスが少なく耐硫化腐食性の良いことが明らかである。
表２に、図１及び図２に示す耐硫化腐食性の試験結果の数値を表す。７００℃の試料表面部腐食割合が２段で記載してあるのは、実験回数が２回あって、その試験結果に対応している。
Table 2 shows the numerical values of the sulfurization corrosion resistance test results shown in FIGS. 1 and 2. The fact that the corrosion rate of the sample surface at 700 ° C. is described in two stages corresponds to the test results because the number of experiments was two.
高温でのクリープ試験は、熱処理後の単結晶凝固合金鋳造物を平行部の直径が４ｍｍで、長さが２０ｍｍのクリープ試験片に加工し、８００℃で７３５ＭＰａ、９００℃で３９２ＭＰａ、１０００℃で２４５ＭＰａおよび１１００℃で１３７ＭＰaの条件でクリープ試験を行った。 In the creep test at high temperature, the heat-treated single crystal solidified alloy casting is processed into a creep test piece having a parallel portion having a diameter of 4 mm and a length of 20 mm, and processed at 800 ° C. at 735 MPa, 900 ° C. at 392 MPa, and 1000 ° C. Creep tests were performed at 245 MPa and 1100 ° C. under the conditions of 137 MPa.
実施例Ｎｏ．１、実施例Ｎｏ．２、比較合金Ｎｏ．３、比較合金Ｎｏ．４および比較合金Ｎｏ．５の８００℃で７３５ＭＰａ条件でのクリープ試験の結果を図３に示す。発明合金のクリープ寿命が比較例より優れていることが図３からも確認される。 Example No. 1. Example No. 2. Comparative alloy No. 3. Comparative alloy No. 4 and Comparative Alloy No. The results of the creep test at 800 ° C. and 735 MPa condition of No. 5 are shown in FIG. It is also confirmed from FIG. 3 that the creep life of the invented alloy is superior to that of the comparative example.
実施例Ｎｏ．１、実施例Ｎｏ．２、比較合金Ｎｏ．３、比較合金Ｎｏ．４および比較合金Ｎｏ．５の９００℃で３９２ＭＰａ条件でのクリープ試験の結果を図４に示す。発明合金のクリープ寿命が比較例より優れていることが図４からも確認される。 Example No. 1. Example No. 2. Comparative alloy No. 3. Comparative alloy No. 4 and Comparative Alloy No. The results of the creep test at 900 ° C. and 392 MPa condition of No. 5 are shown in FIG. It is also confirmed from FIG. 4 that the creep life of the invented alloy is superior to that of the comparative example.
実施例Ｎｏ．１、実施例Ｎｏ．２、比較合金Ｎｏ．３、比較合金Ｎｏ．４および比較合金Ｎｏ．５の１０００℃で２４５ＭＰａ条件でのクリープ試験の結果を図５に示す。発明合金のクリープ寿命が比較例より優れていることが図５からも確認される。 Example No. 1. Example No. 2. Comparative alloy No. 3. Comparative alloy No. 4 and Comparative Alloy No. The results of the creep test at 1000 ° C. and 245 MPa condition of 5 are shown in FIG. It is also confirmed from FIG. 5 that the creep life of the invented alloy is superior to that of the comparative example.
実施例Ｎｏ．１、実施例Ｎｏ．２、比較合金Ｎｏ．３、比較合金Ｎｏ．４および比較合金Ｎｏ．５の１１００℃で１３７ＭＰａ条件でのクリープ試験の結果を図６に示す。発明合金のクリープ寿命が比較例より優れていることが図６からも確認される。
表３に、図３〜図６に示すクリープ破断試験結果の数値（単位：ｈ）を表す。
Table 3 shows the numerical values (unit: h) of the creep rupture test results shown in FIGS. 3 to 6.
比較合金Ｎｏ．３の７５％Ｎａ２ＳＯ４＋２５％ＮａＣｌの混合塩中で７００℃、５０時間全浸漬のるつぼ試験後の走査型電子顕微鏡写真を図7に示す。酸化被膜が４００μｍと厚く、縦方向に酸化物が形成されており基材の酸化を防ぎにくい組織である。 Comparative Alloy No. FIG. 7 shows a scanning electron micrograph after a crucible test in which the product is completely immersed in a mixed salt of 75% Na 2 SO 4 + 25% NaCl at 700 ° C. for 50 hours. The oxide film is as thick as 400 μm, and oxides are formed in the vertical direction, making it difficult to prevent oxidation of the substrate.
実施例Ｎｏ．１の７５％Ｎａ２ＳＯ４＋２５％ＮａＣｌの混合塩中で７００℃、５０時間全浸漬のるつぼ試験後の走査型電子顕微鏡写真を図８に示す。酸化被膜が２００μｍと薄く、層状に重なるように酸化物が形成されており基材の酸化を防ぐ組織である。実施例Ｎｏ．２も同様の酸化被膜を形成していた。 Example No. FIG. 8 shows a scanning electron micrograph after a crucible test in which the product is completely immersed in a mixed salt of 75% Na 2 SO 4 + 25% NaCl at 700 ° C. for 50 hours. The oxide film is as thin as 200 μm, and oxides are formed so as to overlap in layers, which is a structure that prevents oxidation of the base material. Example No. 2 also formed a similar oxide film.
本発明のＮｉ基超合金は、耐硫化腐食性、クリープ特性に優れ、実用面においてコストパフォーマンスに優れている。したがって、ジェットエンジンやガスタービンのタービンブレードやタービンベーンの高温かつ高応力下で使用される部材に有効である。 The Ni-based superalloy of the present invention is excellent in sulfurization corrosion resistance and creep characteristics, and is excellent in cost performance in practical use. Therefore, it is effective for members used under high temperature and high stress of turbine blades and turbine vanes of jet engines and gas turbines.
１ 酸化被膜
２ 基材
1
Claims (6)
Ｍｏ：０．４質量％以上３．０質量％以下、
Ｗ：６質量％以上１０質量％以下、
Ａｌ：４．０質量％以上６．５質量％以下、
Ｔａ：８質量％以上１２質量％以下、
Ｒｅ：０．０１質量％以上１．０質量％以下、
Ｓｉ：０．０１質量％以上０．２質量％以下、
を必須組成元素として含有し、残部がＮｉおよび不可避的不純物からなるＮｉ基超合金であって、任意的組成元素として下記の元素を含有することを特徴とするＮｉ基超合金。
Ｃｏ：０質量％以上３質量％以下、
Ｔｉ：０質量％以上１質量％以下、
Ｎｂ：０質量％以上１質量％以下、
Ｈｆ：０質量％以上０．１５質量％以下、
Ｚｒ：０質量％以上０．０４質量％以下、
Ｂ：０質量％以上０．０３質量％以下、
Ｃ：０質量％以上０．３質量％以下。 Cr: 6% by mass or more and 12% by mass or less,
Mo: 0.4% by mass or more and 3.0% by mass or less,
W: 6% by mass or more and 10% by mass or less,
Al: 4.0% by mass or more and 6.5% by mass or less,
Ta: 8% by mass or more and 12% by mass or less,
Re: 0.01% by mass or more and 1.0% by mass or less,
Si: 0.01% by mass or more and 0.2% by mass or less,
Is a Ni-based superalloy containing Ni as an essential composition element and the balance being Ni and unavoidable impurities, and the Ni-based superalloy is characterized by containing the following elements as optional composition elements.
Co: 0% by mass or more and 3% by mass or less,
Ti: 0% by mass or more and 1% by mass or less,
Nb: 0% by mass or more and 1% by mass or less,
Hf: 0% by mass or more and 0.15% by mass or less,
Zr: 0% by mass or more and 0.04% by mass or less,
B: 0% by mass or more and 0.03% by mass or less,
C: 0% by mass or more and 0.3% by mass or less.
Ｍｏ：０．４質量％以上２．５質量％以下、
Ｗ：７質量％以上１０質量％以下、
Ａｌ：４．０質量％以上６．５質量％以下、
Ｔａ：９質量％以上１１質量％以下、
Ｒｅ：０．０８質量％以上０．９５質量％以下、および
Ｓｉ：０．０１質量％以上０．２質量％以下、
を必須組成元素として含有し、残部がＮｉおよび不可避的不純物からなるＮｉ基超合金であって、任意的組成元素として下記の元素を含有することを特徴とするＮｉ基超合金。
Ｃｏ：０質量％以上３質量％以下、
Ｔｉ：０質量％以上１質量％以下、
Ｎｂ：０質量％以上１質量％以下、
Ｈｆ：０質量％以上０．１５質量％以下、
Ｚｒ：０質量％以上０．０４質量％以下、
Ｂ：０質量％以上０．０３質量％以下、
Ｃ：０質量％以上０．３質量％以下。 Cr: 7% by mass or more and 12% by mass or less,
Mo: 0.4% by mass or more and 2.5% by mass or less,
W: 7% by mass or more and 10% by mass or less,
Al: 4.0% by mass or more and 6.5% by mass or less,
Ta: 9% by mass or more and 11% by mass or less,
Re: 0.08% by mass or more and 0.95% by mass or less, and Si: 0.01% by mass or more and 0.2% by mass or less,
Is a Ni-based superalloy containing Ni as an essential composition element and the balance being Ni and unavoidable impurities, and the Ni-based superalloy is characterized by containing the following elements as optional composition elements.
Co: 0% by mass or more and 3% by mass or less,
Ti: 0% by mass or more and 1% by mass or less,
Nb: 0% by mass or more and 1% by mass or less,
Hf: 0% by mass or more and 0.15% by mass or less,
Zr: 0% by mass or more and 0.04% by mass or less,
B: 0% by mass or more and 0.03% by mass or less,
C: 0% by mass or more and 0.3% by mass or less.
Ｍｏ：０．４質量％以上２．０質量％以下、
Ｗ：７質量％以上９質量％以下、
Ａｌ：４．０質量％以上６．５質量％以下、
Ｔａ：１０質量％以上１１質量％以下、
Ｒｅ：０．１質量％以上０．９質量％以下、および
Ｓｉ：０．０１質量％以上０．２質量％以下、
を必須組成元素として含有し、残部がＮｉおよび不可避的不純物からなるＮｉ基超合金であって、任意的組成元素として下記の元素を含有することを特徴とするＮｉ基超合金。
Ｃｏ：０質量％以上３質量％以下、
Ｔｉ：０質量％以上１質量％以下、
Ｎｂ：０質量％以上１質量％以下、
Ｈｆ：０質量％以上０．１５質量％以下、
Ｚｒ：０質量％以上０．０４質量％以下、
Ｂ：０質量％以上０．０３質量％以下、
Ｃ：０質量％以上０．３質量％以下。 Cr: 8% by mass or more and 10% by mass or less,
Mo: 0.4% by mass or more and 2.0% by mass or less,
W: 7% by mass or more and 9% by mass or less,
Al: 4.0% by mass or more and 6.5% by mass or less,
Ta: 10% by mass or more and 11% by mass or less,
Re: 0.1% by mass or more and 0.9% by mass or less, and Si: 0.01% by mass or more and 0.2% by mass or less,
Is a Ni-based superalloy containing Ni as an essential composition element and the balance being Ni and unavoidable impurities, and the Ni-based superalloy is characterized by containing the following elements as optional composition elements.
Co: 0% by mass or more and 3% by mass or less,
Ti: 0% by mass or more and 1% by mass or less,
Nb: 0% by mass or more and 1% by mass or less,
Hf: 0% by mass or more and 0.15% by mass or less,
Zr: 0% by mass or more and 0.04% by mass or less,
B: 0% by mass or more and 0.03% by mass or less,
C: 0% by mass or more and 0.3% by mass or less.
温度８００℃で応力７３５ＭＰａにおけるクリープ寿命が１９６時間以上であり、温度９００℃で応力３９２ＭＰａにおけるクリープ寿命が２６７時間以上であり、温度１０００℃で応力２４５ＭＰａにおけるクリープ寿命が８０時間以上であり、温度１１００℃で応力１３７ＭＰａにおけるクリープ寿命が２３７時間以上であるＮｉ基超合金。 The Ni-based superalloy according to any one of claims 1 to 3.
The creep life at a temperature of 800 ° C. and a stress of 735 MPa is 196 hours or more, the creep life at a temperature of 900 ° C. and a stress of 392 MPa is 267 hours or more, the creep life at a temperature of 1000 ° C. and a stress of 245 MPa is 80 hours or more, and the temperature is 1100. A Ni-based superalloy having a creep life of 237 hours or more at a temperature of 137 MPa at a temperature of 137 MPa.
所定条件のるつぼ試験において温度７００℃で５０時間保持の腐食表面積割合が９０％以下であり、９００℃で２０時間保持のメタルロスが２．０ｍｍ以下であるＮｉ基超合金。 The Ni-based superalloy according to any one of claims 1 to 3.
A Ni-based superalloy having a corrosion surface area ratio of 90% or less at a temperature of 700 ° C. for 50 hours and a metal loss of 2.0 mm or less at 900 ° C. for 20 hours in a crucible test under predetermined conditions.
A turbine member produced by any of the ordinary casting method, the one-way solidification method, the single crystal solidification method, the sintering using powder, and the 3D modeling method using the Ni-based superalloy according to any one of claims 1 to 3.
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