JP5129303B2 - Single crystal nickel-based super heat-resistant alloy with excellent creep characteristics - Google Patents
Single crystal nickel-based super heat-resistant alloy with excellent creep characteristics Download PDFInfo
- Publication number
- JP5129303B2 JP5129303B2 JP2010168339A JP2010168339A JP5129303B2 JP 5129303 B2 JP5129303 B2 JP 5129303B2 JP 2010168339 A JP2010168339 A JP 2010168339A JP 2010168339 A JP2010168339 A JP 2010168339A JP 5129303 B2 JP5129303 B2 JP 5129303B2
- Authority
- JP
- Japan
- Prior art keywords
- creep
- single crystal
- alloy
- super heat
- added
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 229910045601 alloy Inorganic materials 0.000 title claims description 43
- 239000000956 alloy Substances 0.000 title claims description 43
- 239000013078 crystal Substances 0.000 title claims description 24
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims description 19
- 229910052759 nickel Inorganic materials 0.000 title claims description 8
- 229910000601 superalloy Inorganic materials 0.000 claims description 17
- 229910052702 rhenium Inorganic materials 0.000 claims description 8
- 229910052707 ruthenium Inorganic materials 0.000 claims description 8
- 229910052721 tungsten Inorganic materials 0.000 claims description 8
- 229910052750 molybdenum Inorganic materials 0.000 claims description 7
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- 239000011159 matrix material Substances 0.000 claims description 5
- 229910052715 tantalum Inorganic materials 0.000 claims description 5
- 229910052719 titanium Inorganic materials 0.000 claims description 5
- 239000012535 impurity Substances 0.000 claims description 4
- 239000002244 precipitate Substances 0.000 claims description 2
- 238000012360 testing method Methods 0.000 description 22
- 239000012071 phase Substances 0.000 description 20
- 239000000463 material Substances 0.000 description 19
- 230000000052 comparative effect Effects 0.000 description 12
- 238000005728 strengthening Methods 0.000 description 11
- 238000000034 method Methods 0.000 description 7
- 239000010936 titanium Substances 0.000 description 7
- 239000011651 chromium Substances 0.000 description 6
- 239000006104 solid solution Substances 0.000 description 6
- 238000005275 alloying Methods 0.000 description 5
- 230000007797 corrosion Effects 0.000 description 5
- 238000005260 corrosion Methods 0.000 description 5
- 239000000203 mixture Substances 0.000 description 4
- KJTLSVCANCCWHF-UHFFFAOYSA-N Ruthenium Chemical compound [Ru] KJTLSVCANCCWHF-UHFFFAOYSA-N 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 229910052804 chromium Inorganic materials 0.000 description 3
- 230000007423 decrease Effects 0.000 description 3
- 238000010248 power generation Methods 0.000 description 3
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 description 3
- 238000007711 solidification Methods 0.000 description 3
- 230000008023 solidification Effects 0.000 description 3
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 3
- 239000010937 tungsten Substances 0.000 description 3
- 229910001011 CMSX-4 Inorganic materials 0.000 description 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 2
- 208000003351 Melanosis Diseases 0.000 description 2
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 239000000470 constituent Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000006698 induction Effects 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 239000011733 molybdenum Substances 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 239000007790 solid phase Substances 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 2
- -1 aluminum Chemical compound 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 210000001787 dendrite Anatomy 0.000 description 1
- 230000002542 deteriorative effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000010792 warming Methods 0.000 description 1
Images
Classifications
-
- 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
-
- 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
-
- 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
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
-
- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B11/00—Single-crystal growth by normal freezing or freezing under temperature gradient, e.g. Bridgman-Stockbarger method
-
- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B29/00—Single crystals or homogeneous polycrystalline material with defined structure characterised by the material or by their shape
- C30B29/10—Inorganic compounds or compositions
- C30B29/52—Alloys
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Mechanical Engineering (AREA)
- Crystallography & Structural Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
Description
本発明は、単結晶ニッケル基合金に関するものである。特に高温でクリープ(creep)により変形されることに対する抵抗性、及びクリープによる破断寿命を向上させた単結晶ニッケル基超耐熱合金に関するものである。 The present invention relates to a single crystal nickel base alloy. More particularly, the present invention relates to a single crystal nickel-based superalloy having improved resistance to deformation by creep at high temperatures and improved rupture life due to creep.
航空機のエンジンや発電に使用される産業用のガスタービンの主要な部品であるブレード（ｂｌａｄｅ）及びベーン（ｖａｎｅ）などにはニッケル基超耐熱合金が広く使用される。その超耐熱合金の中で単結晶状態の超耐熱合金は、多結晶及び一方向凝固の超耐熱合金に比べ、優れたクリープ特性を示し、また優れた耐熱性を有しているので、ガスタービンの極限の環境に置かれているブレード及びベーンの素材に使用されている。 Nickel-based superalloys are widely used for blades and vanes, which are the main parts of industrial gas turbines used for aircraft engines and power generation. Among the super heat-resistant alloys, the super heat-resistant alloy in a single crystal state exhibits excellent creep characteristics and excellent heat resistance compared to polycrystalline and unidirectionally solidified super heat-resistant alloys. It is used for blades and vanes that are placed in extreme environments.
そのような単結晶超耐熱合金は、Ａｌ、Ｔｉを添加して基地（ｍａｔｒｉｘ）内に規則格子の強化相であるγ′（Ｌ１2構造）を生成させ、高温強度を得て、Ｗ、Ｍｏ、Ｒｅなどの合金元素を添加して基地を強化させて使用する。一方、単結晶超耐熱合金は、合金元素であるＲｅの含有量により世代が分類されていて、Ｒｅの含有量がない場合は第1世代、３重量％である場合は第2世代、６重量％である場合は第３世代などに分類され、さらにＲｕが添加された第４世代の単結晶合金も開発されている。 Such single-crystal superalloy, Al, a strengthening phase of ordered lattice by the addition of Ti in the base (matrix) γ '(L1 2 structure) to generate, to obtain a high temperature strength, W, Mo , Re and other alloying elements are added to strengthen the base. On the other hand, generations of single crystal super heat-resistant alloys are classified according to the content of Re, which is an alloying element. If there is no Re content, the first generation is 3% by weight, the second generation is 6% by weight. % Is classified as the third generation, and a fourth generation single crystal alloy to which Ru is further added has also been developed.
技術進歩により、超耐熱合金が高温下で使用される際に、最も重要な特性といえるクリープ特性は向上したが、高価な元素の添加量が増加して合金の価格も上昇した。そのため、現在はＲｅ含有量が３％である第2世代の単結晶合金である米国のｃａｎｏｎ ｍｕｓｋｅｇｏｎ社が開発したＣＭＳＸ−４(米国登録特許第４,６４３,７８２号)が商用合金として最も広く使用されている。 The advancement of technology has improved the creep characteristics, which are the most important characteristics when superalloys are used at high temperatures, but the amount of expensive elements added has increased and the price of the alloys has also increased. Therefore, CMSX-4 (US Patent No. 4,643,782) developed by canon muskegone in the United States, which is a second generation single crystal alloy with a Re content of 3%, is the most widely used commercial alloy. It is used.
ところで、地球温暖化のような環境問題が台頭し、ＣＯ2の削減のために、新しい発電方案の研究と共に既存の発電方法の効率化の必要性が大きくなっている。このため、ガスタービンの場合作動温度が高まる傾向にある。このような理由で、ガスタービンの部品の中で最も極限の環境で使用されるブレード及びベーンの温度受容性及び高温でのクリープ寿命が重要になっている。したがって、従来より優れた高温クリープ特性を有する単結晶超耐熱合金の開発に対する必要性は高まっている。 By the way, environmental problems such as global warming have emerged, and in order to reduce CO 2 , the necessity of improving the efficiency of existing power generation methods as well as research on new power generation methods is increasing. For this reason, in the case of a gas turbine, the operating temperature tends to increase. For these reasons, the temperature acceptability and creep life at high temperatures of blades and vanes used in the most extreme environments of gas turbine components are important. Therefore, there is an increasing need for the development of a single crystal super heat-resistant alloy having high temperature creep characteristics superior to those of conventional ones.
また、高温で使用される部品の場合、先に説明したクリープ破断に到達するクリープ寿命も重要であるが、部品の形態が変わればその本来の用途に持続的な使用が不可能であったり、効率が低くなるために、クリープの変形に対する抵抗性も非常に重要な因子ということができる。言い換えれば、高価の合金元素の添加を最小限に減らした状態で、相対的に安価な他の合金元素量を調節して高温の特性、特にクリープ寿命だけではなく、クリープ変形に対する抵抗性に優れた単結晶超耐熱合金が要求されている。 In addition, in the case of parts used at high temperatures, the creep life that reaches the creep rupture described above is also important, but if the form of the part changes, it cannot be used continuously for its original purpose, Resistance to creep deformation is also a very important factor because of the low efficiency. In other words, with the addition of expensive alloying elements minimized, the amount of other relatively inexpensive alloying elements can be adjusted to provide high temperature characteristics, not only creep life, but also excellent resistance to creep deformation. A single crystal super heat resistant alloy is required.
したがって、本発明が解決しようとする技術的課題は、高価の合金元素の添加を最小限に減らした状態で、相対的に安価な他の合金元素量を調節して高温の特性、特にクリープ寿命だけではなく、クリープ変形に対する抵抗性に優れた単結晶ニッケル基超耐熱合金を提供することである。 Therefore, the technical problem to be solved by the present invention is to adjust the amount of other relatively inexpensive alloy elements while keeping the addition of expensive alloy elements to a minimum, and to improve the high temperature characteristics, particularly the creep life. In addition to this, it is to provide a single crystal nickel-base superalloy having excellent resistance to creep deformation.
前記課題を達成するため、本発明のクリープ特性に優れた単結晶ニッケル基超耐熱合金は、重量％でＣｏ:１１.５〜１３.５％、Ｃｒ:３.０〜５.０％、Ｍｏ:０.７〜２.０％、Ｗ:８.５〜１０.５％、Ａｌ:４.５〜６.５％、Ｔｉ:０.５〜２.０％、Ｔａ:６.０〜８.０％、Ｒｅ:２.０〜４.０％、Ｒｕ:０.１〜２.０％であり、残りはＮｉとその他の不可避不純物からなる。ここで、前記超耐熱合金はγ基地とγ′析出物の混合組織を有することができる。 In order to achieve the above object, the single crystal nickel-base superalloy having excellent creep characteristics according to the present invention is Co: 11.5 to 13.5% by weight, Cr: 3.0 to 5.0%, Mo : 0.7 to 2.0%, W: 8.5 to 10.5%, Al: 4.5 to 6.5%, Ti: 0.5 to 2.0%, Ta: 6.0 to 8 0.0%, Re: 2.0-4.0%, Ru: 0.1-2.0%, and the remainder consists of Ni and other inevitable impurities. Here, the super heat-resistant alloy may have a mixed structure of γ matrix and γ ′ precipitate.
本発明によるクリープ特性に優れた単結晶ニッケル基超耐熱合金によれば、重量％でＣｏ:１１.５〜１３.５％、Ｃｒ:３.０〜５.０％、Ｍｏ:０.７〜２.０％、Ｗ:８.５〜１０.５％、Ａｌ:４.５〜６.５％、Ｔｉ:０.５〜２.０％、Ｔａ:６.０〜８.０％、Ｒｅ:２.０〜４.０％、Ｒｕ:０.１〜２.０％であり、残りはＮｉとその他の不可避不純物からなる超耐熱合金を単結晶に製造することにより、クリープの破断寿命が増加するだけではなく、クリープの変形に対する抵抗性を示す１％のクリープ到達寿命が顕著に増加した合金を確保することができる。 According to the single crystal nickel-base superalloy having excellent creep characteristics according to the present invention, Co: 11.5 to 13.5%, Cr: 3.0 to 5.0%, Mo: 0.7 to 2.0%, W: 8.5 to 10.5%, Al: 4.5 to 6.5%, Ti: 0.5 to 2.0%, Ta: 6.0 to 8.0%, Re : 2.0 to 4.0%, Ru: 0.1 to 2.0%, and the remainder is made of a super heat-resistant alloy made of Ni and other inevitable impurities into a single crystal. In addition to an increase, it is possible to secure an alloy with a significantly increased 1% creep arrival life that exhibits resistance to creep deformation.
以下、添付図面を参照して、本発明の好ましい実施例を詳細に説明する。下記に説明する実施例は他の様々な形態に変形でき、本発明の範囲は下記に説明する実施例に限定されるものではない。本発明の実施例は当分野で通常の知識を有する者に、本発明をより完全に説明するため提供するものである。 Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. The embodiments described below can be modified in various other forms, and the scope of the present invention is not limited to the embodiments described below. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of the invention to those skilled in the art.
以下の実施例では、クリープ特性に優れた単結晶ニッケル基超耐熱合金を説明する。ここで、クリープ特性というのは、超耐熱合金を高温で使用するために必須のクリープ寿命だけではなく、クリープ変形に対する抵抗性を含むものとする。前記ニッケル基超耐熱合金は次のような主要な特徴を有する。 In the following examples, a single crystal nickel-based superalloy having excellent creep characteristics will be described. Here, the creep characteristics include not only the creep life essential for using the super-heat-resistant alloy at a high temperature but also resistance to creep deformation. The nickel-base superalloy has the following main features.
本発明によるクリープ特性に優れた単結晶ニッケル期超耐熱合金は、Ａｌ、Ｔｉを添加して規則格子の強化相であるγ′(Ｌ１2構造）を、γ相の基地（ｍａｔｒｉｘ）に生成させ、高温強度を得て、Ｗ、Ｍｏ、Ｒｅ、Ｒｕなどの合金元素を添加して基地を強化させて得る。このように、合金元素量を調節することによりクリープ特性を極大化させ、商用合金に比べて向上したクリープ特性を有することを特徴とする。 Single crystal nickel-life superalloy having excellent creep characteristics according to the present invention, Al, gamma is a strengthening phase of ordered lattice by the addition of Ti 'the (L1 2 structure), to generate the base of the gamma phase (matrix) Obtain high-temperature strength and strengthen the matrix by adding alloy elements such as W, Mo, Re, and Ru. Thus, the creep characteristics are maximized by adjusting the amount of alloying elements, and the creep characteristics are improved compared to commercial alloys.
本発明によるニッケル基超耐熱合金は、まず、通常の真空誘導溶解方法により母合金を製作する。その後、製作された母合金の各々に対し、一方向凝固炉を利用してブリッジマン（ｂｒｉｄｇｍａｎ）方法により単結晶の試料を製作する。その試料を熱処理してγとγ′の２つの相（ｐｈａｓｅ）からなる微細組織を得ることができる。 In the nickel-base superalloy according to the present invention, first, a mother alloy is manufactured by a normal vacuum induction melting method. Thereafter, a single crystal sample is manufactured for each of the manufactured master alloys by a bridgman method using a unidirectional solidification furnace. The sample can be heat-treated to obtain a microstructure composed of two phases γ and γ ′.
[合金の組成]
本発明のニッケル基超耐熱合金は、重量％で次のような組成を有していて、ここではそれぞれの組成による数値限定の理由を共に説明する。下記の重量％はニッケル基合金の全体を100とした時、添加される量を重量で換算したものである。説明の便宜のために、ニッケル基とその他の不可避不純物に対する説明は省略することにする。
[Alloy composition]
The nickel-base superalloy according to the present invention has the following composition in weight%, and here, the reason for numerical limitation by each composition will be explained together. The weight% below is calculated by converting the amount added to the nickel-base alloy as 100. For convenience of explanation, explanation of nickel base and other inevitable impurities will be omitted.
(１)コバルト（Ｃｏ）:１１.５〜１３.５％
Ｃｏは、固溶強化の役割をすると共にニッケル基超耐熱合金の主な強化相であるγ′の固相線と基地であるγの固相線を変化させ、溶体化処理が可能な温度に影響を与える。また、高温耐蝕性を向上させる。Ｃｏ含有量が１１.５％より低ければクリープ特性が低くなり、１３.５％以上を超えると溶体化処理が可能な温度領域が小さくなり、熱処理の条件を決定することが難しくなる。
(1) Cobalt (Co): 11.5 to 13.5%
Co plays a role in solid solution strengthening and changes the solid phase line of γ ′, which is the main strengthening phase of nickel-base superalloys, and the solid phase line of γ, which is the base, to a temperature at which solution treatment is possible. Influence. It also improves high temperature corrosion resistance. If the Co content is lower than 11.5%, the creep characteristics are lowered, and if it exceeds 13.5%, the temperature range in which the solution treatment can be performed becomes small, and it becomes difficult to determine the conditions for the heat treatment.
(２)クロム（Ｃｒ）:３.５〜５.０％
クロムは、超耐熱合金で耐蝕性を向上させる役割をする一方、炭化物やＴＣＰ（Ｔｏｐｏｌｏｇｉｃａｌｌｙ Ｃｌｏｓｅ Ｐａｃｋｅｄ）相を生成させることができるが、耐熱性には寄与できないために量が制限される。３.５％より少なく添加すれば耐蝕性に問題が発生し、５.０％以上添加すればクリープ特性が低下し、高温で長時間露出時、機械的な特性に悪い影響を与えるＴＣＰ相が生成され得る。
(2) Chromium (Cr): 3.5-5.0%
Chromium plays a role in improving corrosion resistance in a super heat-resistant alloy, while it can generate a carbide and TCP (Topologically Closed Packed) phase, but its amount is limited because it cannot contribute to heat resistance. Addition of less than 3.5% causes a problem in corrosion resistance, and addition of 5.0% or more degrades creep characteristics. When exposed at high temperatures for a long time, the TCP phase has a bad influence on mechanical characteristics. Can be generated.
(３)モリブデン(Ｍｏ):０.７〜２.０％
モリブデンは固溶強化の元素で、超耐熱合金の高温特性を向上させる役割をする。しかし、多量に添加すれば密度が高まってＴＣＰ相が生成され得る。０.７％以下では固溶強化の効果を期待することは難しく、２.０％以上添加すれば密度が増加する。
(3) Molybdenum (Mo): 0.7 to 2.0%
Molybdenum is a solid solution strengthening element that plays a role in improving the high temperature characteristics of superalloys. However, if added in a large amount, the density increases and a TCP phase can be generated. If it is 0.7% or less, it is difficult to expect the effect of solid solution strengthening, and if 2.0% or more is added, the density increases.
(４)タングステン(Ｗ):８.５〜１０.５％
タングステンは、固溶強化によりクリープ強度を高める元素である。しかし、多量に添加すれば密度が高くなり、靱性及び耐蝕性が低下し、相安全性が低下する。また、単結晶及び一方向凝固時、フレックル（ｆｒｅｃｋｌｅ）のような鋳造欠陥が発生する可能性が増加する。したがって、高温強度のために８.５％以上のタングステンが添加され、多量に添加する場合に生じる、上記の望ましくない効果を抑制するために、１０.５％に含有量を制限する。
(4) Tungsten (W): 8.5 to 10.5%
Tungsten is an element that increases the creep strength by solid solution strengthening. However, if added in a large amount, the density increases, the toughness and the corrosion resistance decrease, and the phase safety decreases. Also, during single crystal and unidirectional solidification, the likelihood of casting defects such as freckle increases. Therefore, 8.5% or more of tungsten is added for the high temperature strength, and the content is limited to 10.5% in order to suppress the above-mentioned undesirable effect that occurs when a large amount is added.
(５)アルミニウム（Ａｌ）:４.５〜６.５％
アルミニウムは、ニッケル基超耐熱合金の主な強化相であるγ′の構成元素であるから、高温のクリープ特性の向上に必ず必要な元素である。また、耐酸化性の向上にも寄与する。しかし、４.５％以下ではクリープ強度が低下し、６.５％以上添加する場合は過度なγ′相が析出されて機械的な特性を低下させる。
(5) Aluminum (Al): 4.5-6.5%
Since aluminum is a constituent element of γ ′, which is the main strengthening phase of nickel-base superalloys, it is an essential element for improving high temperature creep characteristics. It also contributes to the improvement of oxidation resistance. However, if it is 4.5% or less, the creep strength is lowered, and if it is added 6.5% or more, an excessive γ 'phase is precipitated and mechanical properties are lowered.
(６)チタニウム（Ｔｉ）:０.５〜２.０％
チタニウムはアルミニウムと同様にγ′相の構成元素で、クリープ強度の向上を助け、耐蝕性の向上にも寄与するので０.５％以上添加する。しかし、過度に添加する場合には耐酸化性が減少するため２.０％に制限する。
(6) Titanium (Ti): 0.5-2.0%
Titanium, like aluminum, is a constituent element of the γ 'phase and helps improve the creep strength and contributes to the improvement of corrosion resistance, so 0.5% or more is added. However, if it is added excessively, the oxidation resistance decreases, so it is limited to 2.0%.
(７)タンタル（Ｔａ）:６.０〜８.０％
タンタルは、主な強化相であるγ′相に固溶されてγ′相を強化させる役割をし、クリープ強度の向上に寄与する。また、樹枝状間領域に偏析されてこの領域の密度を高めるので、鋳造欠陥であるフレックル生成を抑制することもする。したがって、６.０％以上の含有量を必要とする。しかし、８.０％以上添加する場合、δ相が析出されることがあり特性を低下させる。
(7) Tantalum (Ta): 6.0-8.0%
Tantalum serves to strengthen the γ ′ phase by being dissolved in the γ ′ phase, which is the main strengthening phase, and contributes to the improvement of the creep strength. Moreover, since it is segregated in the region between dendrites and the density of this region is increased, the generation of freckle which is a casting defect is also suppressed. Therefore, a content of 6.0% or more is required. However, when added in an amount of 8.0% or more, the δ phase may be precipitated, deteriorating the characteristics.
(８)レニウム（Ｒｅ）:２.０〜４.０％
レニウムは固溶強化の元素で、拡散速度が非常に遅いために、クリープ特性の向上に大きく寄与する。換言すれば、レニウムを添加することにより、超耐熱合金は高温で使用するために必須のクリープ寿命だけではなく、クリープ変形に対する抵抗性が大きく向上される。しかし、多量に含有すれば、相安全性が低下して密度が大きくなり、価格も高いので、本発明では２.０〜４.０％の範囲を有するように制限する。
(8) Rhenium (Re): 2.0-4.0%
Rhenium is a solid solution strengthening element, and its diffusion rate is very slow, so it greatly contributes to the improvement of creep characteristics. In other words, the addition of rhenium greatly improves the resistance to creep deformation as well as the creep life essential for the super heat resistant alloy to be used at high temperatures. However, if it is contained in a large amount, the phase safety is lowered, the density is increased, and the price is high. Therefore, in the present invention, the content is limited to 2.0 to 4.0%.
(９)ルテニウム（Ｒｕ）:０.１〜２.０％
ルテニウムは固溶強化の元素で作用して基地を強化させる。γ′相が固溶され得る領域を広めて偏析の均質化に寄与し、ＴＣＰ相の生成を抑制するなど、高温特性を改善させる。これにより、本発明では超耐熱合金を高温で使用するために必須のクリープ寿命だけではなく、クリープ変形に対する抵抗性を高めるためにこれを添加する。しかし、ルテニウムが多量に含有すれば、合金の価格も高くなり、密度が増加するので０.１〜２.０％の範囲で添加する。
(9) Ruthenium (Ru): 0.1-2.0%
Ruthenium works with solid solution strengthening elements to strengthen the base. Widens the region where the γ ′ phase can be dissolved, contributes to homogenization of segregation, and improves high temperature characteristics such as suppressing the generation of TCP phase. Accordingly, in the present invention, not only the creep life essential for using the super heat-resistant alloy at a high temperature but also the resistance to creep deformation is added to increase the resistance. However, if a large amount of ruthenium is contained, the price of the alloy increases, and the density increases. Therefore, it is added in the range of 0.1 to 2.0%.
以下、実施例を通して本発明をより詳細に説明する。 Hereinafter, the present invention will be described in more detail through examples.
表１は、本発明の実施例が適用された単結晶超耐熱合金と、前記超耐熱合金と比較される合金の化学組成を提示したものである。 Table 1 presents the chemical composition of the single crystal super heat resistant alloy to which the examples of the present invention were applied and the alloy compared with the super heat resistant alloy.
表１によれば、試験材１はＲｕが１.０重量％添加されるニッケル基合金の造成を示したことであり、試験材２はＲｕが０.５重量％である場合を提示したものである。これに反して、比較試験材は全部Ｒｕが添加されていないものであり、比較試験材１はそこにＲｅを添加しない合金である。また、比較試験材２はＲｅを含んでいるが、Ｃｒの含有量を増加させた合金であり、比較試験材３はＣｏ含有量を減らした合金である。そして、比較試験材４は現在最も広く使用されている商用の単結晶合金のＣＭＳＸ-４である。 According to Table 1, test material 1 showed the formation of a nickel-base alloy to which 1.0% by weight of Ru was added, and test material 2 presented the case where Ru was 0.5% by weight. It is. On the other hand, all the comparative test materials are not added with Ru, and the comparative test material 1 is an alloy to which Re is not added. Moreover, although the comparative test material 2 contains Re, it is an alloy in which the Cr content is increased, and the comparative test material 3 is an alloy in which the Co content is reduced. The comparative test material 4 is CMSX-4, which is the most widely used commercial single crystal alloy.
前記試験材と比較試験材は、まず、通常の真空誘導溶解方法により母合金を製作した後、製作された母合金の各々に対し、一方向凝固炉を利用してブリッジマン方法により、一つのモールドに直径１５ｍｍ、長さ１８０ｍｍの棒状の試料が６個付いている単結晶のモールドを利用し、４.０ｍｍ／ｍｉｎの速度で引き出して単結晶の試料を製作した。その試料を熱処理によりγとγ′の２つの相（ｐｈａｓｅ）からなる微細組織を得た。 The test material and the comparative test material are first manufactured by a normal vacuum induction melting method, and then each of the manufactured master alloys is made one by a Bridgman method using a unidirectional solidification furnace. Using a single crystal mold in which six rod-shaped samples having a diameter of 15 mm and a length of 180 mm were attached to the mold, a single crystal sample was manufactured by pulling out at a speed of 4.0 mm / min. The sample was heat-treated to obtain a fine structure composed of two phases γ and γ ′.
表２は、前記合金を９５０℃で３５５ＭＰａの応力を加えてクリープ試験を遂行した時、クリープ寿命と１％のクリープ延伸に到達する時までの寿命を示したものである。図１は、表２で提示した条件でクリープ試験を行った場合、時間によるクリープ変形量の変化とクリープ寿命を示すグラフである。 Table 2 shows the creep life and the life until reaching the 1% creep extension when the alloy was subjected to a creep test by applying a stress of 355 MPa at 950 ° C. FIG. 1 is a graph showing a change in creep deformation amount with time and a creep life when a creep test is performed under the conditions presented in Table 2.
表２と図１から分かるように、ニッケル基合金のクリープ特性はReに大きく依存する。すなわち、Ｒｅを添加しない比較試験材１は、他の試験材や比較試験材よりクリープ破断時間と１％のクリープ変形到達時間が顕著に小さいことが分かる。また、ＲｅとＲｕを添加した試験材１及び試験材２と、Ｒｅは添加したが、Ｒｕは添加しない比較試験材２〜４を比較すると、ニッケル基合金でＲｕがクリープ特性を向上させるのに主要な役割をしているということが分かる。もちろん、このようなＲｕによるクリープ特性を向上させるためには、他の合金元素の含有量を最適化する過程を必要とする。 As can be seen from Table 2 and FIG. 1, the creep characteristics of the nickel-base alloy greatly depend on Re. That is, it can be seen that the comparative test material 1 to which no Re is added has a significantly shorter creep rupture time and 1% creep deformation arrival time than other test materials and comparative test materials. In addition, when the test materials 1 and 2 to which Re and Ru are added are compared with the comparative test materials 2 to 4 in which Re is added but Ru is not added, Ru is a nickel-based alloy and improves the creep characteristics. You can see that it plays a major role. Of course, in order to improve the creep characteristics by such Ru, the process of optimizing the content of other alloy elements is required.
具体的に、Ｒｕが添加された試験材１と試験材２のクリープ破断時間は１９２.３〜２１１.７時間であり、１％のクリープ変形到達時間は８７.０〜１１２.０時間であった。これに反して、Ｒｕが添加されていない比較試験材２〜４はクリープ破断時間が７１.０〜１２３.１時間であり、１％のクリープ変形到達時間は２９.０〜５７.０時間であった。相対的に、クリープ特性に優れた比較試験材４と本発明の試験材1を比較して見ても、本発明の試験材１は、比較試験材４より、約２倍程度でクリープ破断時間とクリープ変形到達時間が増加したことが分かった。 Specifically, the specimens 1 and 2 to which Ru was added had a creep rupture time of 192.3 to 211.7 hours, and a 1% creep deformation arrival time of 87.0 to 112.0 hours. It was. On the other hand, the comparative test materials 2 to 4 to which no Ru was added had a creep rupture time of 71.0 to 123.1 hours, and a 1% creep deformation arrival time of 29.0 to 57.0 hours. there were. In comparison with the comparative test material 4 having superior creep characteristics and the test material 1 of the present invention, the test material 1 of the present invention has a creep rupture time approximately twice as long as the comparative test material 4. And the creep deformation arrival time increased.
以上、本発明は好ましい実施例を挙げて詳細に説明したが、本発明は前記実施例に限定されず、本発明の技術思想の範囲内で当分野で通常の知識を有する者により様々な変形が可能である。 The present invention has been described in detail with reference to the preferred embodiments. However, the present invention is not limited to the above-described embodiments, and various modifications may be made by those having ordinary knowledge in the art within the scope of the technical idea of the present invention. Is possible.
Claims (2)
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR1020100034314A KR20110114928A (en) | 2010-04-14 | 2010-04-14 | Single Crystal Nickel-Based Super Heat-resistant Alloys with Excellent Creep Properties |
| KR10-2010-0034314 | 2010-04-14 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2011219853A JP2011219853A (en) | 2011-11-04 |
| JP5129303B2 true JP5129303B2 (en) | 2013-01-30 |
Family
ID=44788326
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2010168339A Expired - Fee Related JP5129303B2 (en) | 2010-04-14 | 2010-07-27 | Single crystal nickel-based super heat-resistant alloy with excellent creep characteristics |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US20110256018A1 (en) |
| JP (1) | JP5129303B2 (en) |
| KR (1) | KR20110114928A (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2536940A (en) | 2015-04-01 | 2016-10-05 | Isis Innovation | A nickel-based alloy |
| KR102114253B1 (en) * | 2018-02-26 | 2020-05-22 | 한국기계연구원 | Ni based superalloy with high creep strength and manufacturing method thereof |
| KR102139177B1 (en) | 2018-03-28 | 2020-07-30 | 한국기계연구원 | Wrought nickel base superalloys for forging having excellent creep property and method for manufacturing the same |
| CN116926383B (en) * | 2023-07-20 | 2025-11-04 | 北京工业大学 | A fifth-generation nickel-based single-crystal superalloy and its heat treatment method |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6007645A (en) * | 1996-12-11 | 1999-12-28 | United Technologies Corporation | Advanced high strength, highly oxidation resistant single crystal superalloy compositions having low chromium content |
| EP1184473B1 (en) * | 2000-08-30 | 2005-01-05 | Kabushiki Kaisha Toshiba | Nickel-base single-crystal superalloys, method of manufacturing same and gas turbine high temperature parts made thereof |
| US7473326B2 (en) * | 2002-03-27 | 2009-01-06 | National Institute For Materials Science | Ni-base directionally solidified superalloy and Ni-base single crystal superalloy |
| US7704332B2 (en) * | 2006-12-13 | 2010-04-27 | United Technologies Corporation | Moderate density, low density, and extremely low density single crystal alloys for high AN2 applications |
| CA2680650C (en) * | 2007-03-12 | 2012-07-03 | Ihi Corporation | Ni-based single crystal superalloy and turbine blade incorporating the same |
-
2010
- 2010-04-14 KR KR1020100034314A patent/KR20110114928A/en not_active Ceased
- 2010-07-27 JP JP2010168339A patent/JP5129303B2/en not_active Expired - Fee Related
- 2010-07-30 US US12/847,449 patent/US20110256018A1/en not_active Abandoned
Also Published As
| Publication number | Publication date |
|---|---|
| JP2011219853A (en) | 2011-11-04 |
| KR20110114928A (en) | 2011-10-20 |
| US20110256018A1 (en) | 2011-10-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5696995B2 (en) | Heat resistant superalloy | |
| JP2881626B2 (en) | Single crystal nickel-based superalloy | |
| JP5663530B2 (en) | Rhenium-free single crystal superalloy for turbine blade and vane applications | |
| JP2014214381A (en) | Cast nickel-base superalloys including iron | |
| JP2011074493A (en) | Nickel-based superalloy and article | |
| CN102803528B (en) | Nickel-base single-crystal superalloy and turbine wing using same | |
| JPWO2007122931A1 (en) | Ni-base superalloy and manufacturing method thereof | |
| JP5252348B2 (en) | Ni-base superalloy, manufacturing method thereof, and turbine blade or turbine vane component | |
| TWI248975B (en) | Nickel-base superalloy for high temperature, high strain application | |
| JP5323162B2 (en) | Polycrystalline nickel-based superalloy with excellent mechanical properties at high temperatures | |
| KR20170058065A (en) | Ni base superalloy and Method of manufacturing thereof | |
| CA2612815A1 (en) | Low-density directionally solidified single-crystal superalloys | |
| US9518311B2 (en) | High strength single crystal superalloy | |
| JP4222540B2 (en) | Nickel-based single crystal superalloy, manufacturing method thereof, and gas turbine high-temperature component | |
| JP5129303B2 (en) | Single crystal nickel-based super heat-resistant alloy with excellent creep characteristics | |
| JP5626920B2 (en) | Nickel-base alloy castings, gas turbine blades and gas turbines | |
| JP5393829B2 (en) | Single crystal nickel-base superalloy with improved creep properties | |
| JP5024797B2 (en) | Cobalt-free Ni-base superalloy | |
| JP5787535B2 (en) | Nickel-base superalloy with improved degradation behavior | |
| JP5595495B2 (en) | Nickel-base superalloy | |
| JP4911753B2 (en) | Ni-base superalloy and gas turbine component using the same | |
| CN103132148A (en) | Nickel base single crystal superalloy with low density, low cost and high strength | |
| CN115011844B (en) | Rhenium-containing tungsten-free low-specific gravity nickel-based single crystal superalloy and heat treatment process thereof | |
| JP2013053327A (en) | Ni-BASED SUPERALLOY | |
| KR101866833B1 (en) | Nickel-based heat-resistant material improved cyclic oxidation property and method of preparing the same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| TRDD | Decision of grant or rejection written | ||
| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20121023 |
|
| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 |
|
| A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20121101 |
|
| R150 | Certificate of patent or registration of utility model |
Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20151109 Year of fee payment: 3 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| LAPS | Cancellation because of no payment of annual fees |