JP2000328162A - Nickel base single crystal heat resistant superalloy, its production and turbine blade using nickel base single crystal heat resistant superalloy - Google Patents
Nickel base single crystal heat resistant superalloy, its production and turbine blade using nickel base single crystal heat resistant superalloyInfo
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- JP2000328162A JP2000328162A JP11143670A JP14367099A JP2000328162A JP 2000328162 A JP2000328162 A JP 2000328162A JP 11143670 A JP11143670 A JP 11143670A JP 14367099 A JP14367099 A JP 14367099A JP 2000328162 A JP2000328162 A JP 2000328162A
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- single crystal
- nickel
- alloy
- resistant superalloy
- crystal heat
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Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、産業用ガスタービ
ンや航空機エンジン等に用いられるタービン翼に有用な
ニッケル基単結晶耐熱超合金とその製造方法並びにニッ
ケル基単結晶耐熱超合金を用いたタービン翼に関するも
のである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a nickel-based single crystal heat-resistant superalloy useful for turbine blades used in industrial gas turbines and aircraft engines, a method for producing the same, and a turbine using the nickel-based single crystal heat-resistant superalloy. It is about wings.
【０００２】[0002]
【従来の技術】産業用ガスタービンや航空機エンジン用
タービンは高効率化、高出力化が求められており、その
入口温度は、高くなる傾向にある。2. Description of the Related Art Industrial gas turbines and aircraft engine turbines are required to have higher efficiency and higher output, and the inlet temperature thereof tends to be higher.
【０００３】タービン翼材料には一般的に、ニッケル基
鍛造合金が用いられてきた。このようなニッケル基鍛造
合金は、主強化相であるΝｉ3 （Ａｌ、Ｔｉ）の組成か
らなるγ' （ガンマプライム）析出物の体積率を増やす
ことにより、強度を改善することができる。そのため、
主強化相の形成元素であるＡｌとＴｉの添加量を増加さ
せ、さらに固溶強化のためにＷ、Ｍｏ、Ｔａ等も多量に
添加することも行われている。[0003] Nickel-based forged alloys have generally been used for turbine blade materials. The strength of such a nickel-based forged alloy can be improved by increasing the volume ratio of γ ′ (gamma prime) precipitates having the composition of 強化 i 3 (Al, Ti) as the main strengthening phase. for that reason,
The addition amount of Al and Ti, which are the elements forming the main strengthening phase, is increased, and a large amount of W, Mo, Ta, etc. is also added for solid solution strengthening.
【０００４】しかしながら、このような固溶強化により
強度を改善したニッケル基鍛造合金は、鍛造により所定
の形状に成形することが困難であるという問題があっ
た。[0004] However, such a nickel-based forged alloy having improved strength by solid solution strengthening has a problem that it is difficult to form it into a predetermined shape by forging.
【０００５】さらに、タービン翼自体の高温化を抑制す
るため、タービン翼内部に冷媒を流すための複雑な冷却
構造を設けることも行われるようになったが、このよう
な複雑な内部冷却構造を鍛造によって製作するのは非常
に困難であった。[0005] Further, in order to suppress the temperature rise of the turbine blade itself, a complicated cooling structure for flowing a refrigerant inside the turbine blade has been provided. However, such a complicated internal cooling structure is required. It was very difficult to produce by forging.
【０００６】一方、鋳造法では、合金の種類によらず容
易に所定の形状のタービン翼を製作可能であり、内部冷
却通路も形成することができるところから、タービン翼
の形成に鋳造法が採用され、特に、ニッケル基単結晶耐
熱超合金を用いた方向凝固プロセス（例えば、米国特許
第3,260,505 号公報）によるタービン翼の製作が行われ
るようになってきている。On the other hand, in the casting method, a turbine blade having a predetermined shape can be easily manufactured irrespective of the type of alloy, and an internal cooling passage can be formed. In particular, turbine blades are being manufactured by a directional solidification process (for example, US Pat. No. 3,260,505) using a nickel-base single crystal heat-resistant superalloy.
【０００７】ニッケル基単結晶耐熱超合金を用いて方向
凝固プロセスにより作製されたタービン翼には、高温破
壊の起点となる遠心応力軸方向に垂直な結晶粒界がな
く、これによって従来の鋳造合金タービン翼よりもクリ
ープ強度等に優れたタービン翼が得られるようになって
いる。A turbine blade manufactured by a directional solidification process using a nickel-base single crystal heat-resistant superalloy does not have a crystal grain boundary perpendicular to the centrifugal stress axis direction, which is a starting point of high-temperature fracture. Turbine blades having better creep strength and the like than turbine blades can be obtained.
【０００８】このような方向凝固プロセスによる単結晶
タービン翼は、チルプレート（冷却板）上に構築した鋳
型を加熱炉内に設置し、高温に保持した鋳型中へニッケ
ル基単結晶耐熱超合金の溶湯を注ぎ込んだ後、加熱炉か
ら鋳型をチルプレートとともに一方向（翼長手方向）に
沿って徐々に引抜くことにより溶湯をチルプレート側か
ら凝固させることによって作製される。A single-crystal turbine blade obtained by such a directional solidification process installs a mold constructed on a chill plate (cooling plate) in a heating furnace, and places a nickel-based single-crystal heat-resistant superalloy in a mold maintained at a high temperature. After pouring the molten metal, the mold is produced by solidifying the molten metal from the chill plate side by gradually pulling out the mold together with the chill plate from the heating furnace along one direction (blade longitudinal direction).
【０００９】この方法によれば、凝固開始部の単結晶セ
レクターと呼ばれる堰により一つの結晶のみが成長し、
この結晶は鋳型内を一方向に整列しながら成長して柱状
晶となり単結晶タービン翼が形成される。According to this method, only one crystal is grown by a weir called a single crystal selector at the solidification start portion,
This crystal grows while being aligned in one direction in the mold and becomes a columnar crystal to form a single crystal turbine blade.
【００１０】方向凝固プロセスにおいては、化学的安定
性、強度に優れるセラミックス製の鋳型や中子が用いら
れるが、鋳型や中子は１５００℃の溶湯と長時間接触す
るためタービン翼表面や冷却通路面に硬くて脆い反応硬
化層が形成されるが、このような反応硬化層の形成され
たタービン翼ではこの反応硬化層を起点として破壊が進
行するという問題がある。In the directional solidification process, a ceramic mold and core having excellent chemical stability and strength are used. Although a hard and brittle reaction hardened layer is formed on the road surface, there is a problem that the turbine blade having such a reaction hardened layer is broken starting from the reaction hardened layer.
【００１１】特に、反応硬化層の生成量は、溶湯との接
触時間が長くなるほど多くなるため、大型翼ほど反応硬
化層が生成され易く、従って、長尺タービン翼をニッケ
ル基単結晶耐熱超合金による鋳造で製作する場合に大き
な問題となる。In particular, the amount of the reaction hardened layer increases as the contact time with the molten metal becomes longer, so that the larger the blade, the more easily the reaction hardened layer is generated. This is a major problem when manufacturing by casting.
【００１２】このような反応硬化層を除去するため、ケ
ミカルあるいはメカニカルミーリングにより研削、研磨
等が行われているが、このような機械的研削・研磨工程
で反応硬化層を除去したのでは、高い寸法精度が得られ
ず、歩留まりも低下してしまうという問題があった。In order to remove such a reaction-hardened layer, grinding or polishing is performed by chemical or mechanical milling. However, if the reaction-hardened layer is removed by such a mechanical grinding / polishing step, it is expensive. There has been a problem that the dimensional accuracy cannot be obtained and the yield decreases.
【００１３】したがって、ニッケル基単結晶耐熱超合金
の鋳造でタービン翼を製作する際の反応硬化層を抑制す
ることが望まれていた。Therefore, it has been desired to suppress a reaction hardened layer when a turbine blade is manufactured by casting a nickel-base single crystal heat-resistant superalloy.
【００１４】[0014]
【発明が解決しようとする課題】上述した通り、従来の
ニッケル基単結晶耐熱超合金の鋳造によるタービン翼の
製作においては、破壊の起点となる反応硬化層をいかに
抑制するかが大きい課題となっていた。As described above, in the production of a turbine blade by casting a conventional nickel-base single crystal heat-resistant superalloy, it is a major problem how to suppress a reaction hardened layer which is a starting point of destruction. I was
【００１５】従って、本発明の目的は、従来の単結晶合
金と同程度の高温強度を保持しつつ、反応硬化層を除去
したニッケル基単結晶耐熱超合金を提供することにあ
る。Accordingly, it is an object of the present invention to provide a nickel-base single crystal heat-resistant superalloy from which a reaction hardened layer has been removed while maintaining high-temperature strength comparable to that of a conventional single crystal alloy.
【００１６】また本発明の他の目的は、上記のニッケル
基単結晶耐熱超合金の製法を提供することにある。Another object of the present invention is to provide a method for producing the above-mentioned nickel-based single crystal heat-resistant superalloy.
【００１７】本発明のさらに他の目的は、上記ニッケル
基単結晶耐熱超合金の鋳造により製作されるタービン翼
を提供することにある。Still another object of the present invention is to provide a turbine blade manufactured by casting the above-mentioned nickel-base single crystal heat-resistant superalloy.
【００１８】[0018]
【課題を解決するための手段】本発明のニッケル基単結
晶耐熱超合金は、Ｐｒ、Νｄ、Ｓｍ、Ｄｙ、Ｅｒ及びＴ
ｈからなる群から選ばれた少なくとも１種の元素を重量
で、０．５〜５ｐｐｍ、好ましくは０．７〜４．８ｐｐ
ｍ含有することを特徴とするものである。The nickel-base single crystal heat-resistant superalloy of the present invention comprises Pr, Δd, Sm, Dy, Er and T.
h, at least one element selected from the group consisting of 0.5 to 5 ppm, preferably 0.7 to 4.8 pp, by weight.
m is contained.
【００１９】上記元素を上記の範囲で添加することによ
って、溶湯と鋳型および中子との反応を抑制し、高温強
度の低下を招く反応硬化層の生成を抑制することができ
る。本発明のニッケル基単結晶耐熱超合金において、Ｐ
ｒ、Ｎｄ、Ｓｍ、Ｄｙ、Ｅｒ及びＴｈの含有量を重量で
０．５〜５ｐｐｍとしたのは、次のような理由によるも
のである。By adding the above elements in the above range, the reaction between the molten metal and the mold and the core can be suppressed, and the formation of a reaction hardened layer which causes a decrease in high-temperature strength can be suppressed. In the nickel-based single crystal heat-resistant superalloy of the present invention, P
The contents of r, Nd, Sm, Dy, Er and Th are set to 0.5 to 5 ppm by weight for the following reason.
【００２０】すなわち、Ｐｒ、Ｎｄ、Ｓｍ、Ｄｙ、Ｅｒ
及びＴｈの含有量が０．５ｐｐｍ未満の場合、これらの
元素は溶湯と鋳型あるいは中子の界面に吸着し、両者の
界面自由エネルギーを低下させて濡れ性を向上させるた
め、反応硬化層の生成を促進してしまう。一方、Ｐｒ、
Ｎｄ、Ｓｍ、Ｄｙ、Ｅｒ及びＴｈの含有量が、５ｐｐｍ
を越える場合、Ｍ2 Ｎｉ17の金属間化合物を生成するた
め、高温強度が低下する原因となる。That is, Pr, Nd, Sm, Dy, Er
And when the content of Th is less than 0.5 ppm, these elements are adsorbed on the interface between the molten metal and the mold or the core to reduce the free energy at the interface between them and improve the wettability. Promotes. On the other hand, Pr,
The content of Nd, Sm, Dy, Er and Th is 5 ppm
In the case where it exceeds, an intermetallic compound of M 2 Ni 17 is generated, which causes a decrease in high-temperature strength.
【００２１】これらＰｒ、Ｎｄ、Ｓｍ、Ｄｙ、Ｅｒ及び
Ｔｈは、合計量が０．５〜５ｐｐｍの範囲内であれば、
複数の元素を添加してもよい。These Pr, Nd, Sm, Dy, Er and Th can be used as long as their total amount is in the range of 0.5 to 5 ppm.
A plurality of elements may be added.
【００２２】本発明のニッケル基単結晶耐熱超合金に
は、上記のＰｒ、Νｄ、Ｓｍ、Ｄｙ、Ｅｒ又はＴｈの他
に、Ｃｒ、Ｃｏ、Ｗ、Ｔａ、Ｍｏ、Ａｌ及びＴｉからな
る群から選ばれた少なくとも１種の元素が含まれていて
もよい。The nickel-base single crystal heat-resistant superalloy of the present invention includes, in addition to the above Pr, Δd, Sm, Dy, Er or Th, a group consisting of Cr, Co, W, Ta, Mo, Al and Ti. At least one selected element may be contained.
【００２３】これらの元素の含有量は次の範囲であるこ
とが望ましい。It is desirable that the contents of these elements fall within the following ranges.
【００２４】Ｃｒ １．５〜１４ｗｔ％、Ｃｏ ２〜１
０ｗｔ％、Ｗ ４〜９ｗｔ％、Ｔａ４〜１０ｗｔ％、Ｍ
ｏ ０．２５〜２ｗｔ％、Ａｌ ３〜７ｗｔ％、Ｔｉ
０．１〜５ｗｔ％。Cr 1.5-14 wt%, Co 2-1
0 wt%, W 4-9 wt%, Ta4-10 wt%, M
o 0.25 to 2 wt%, Al 3 to 7 wt%, Ti
0.1-5 wt%.
【００２５】Ｃｒ、Ｃｏ、Ｗ、Ｔａ、Ｍｏ、Ａｌ及びＴ
ｉの添加量を上記のように限定したのは次の理由によ
る。Cr, Co, W, Ta, Mo, Al and T
The reason for limiting the amount of i added as described above is as follows.
【００２６】Ｃｒは耐食性を向上させる成分であり、Ｃ
ｒをニッケル基単結晶耐熱超合金に添加することによっ
て、反応硬化層の生成を抑制するだけでなく耐食性も向
上させることができる。しかし、Ｃｒは過剰に添加する
と高温強度の低下を引き起こし、添加量が足りない場合
には所定の耐食性を得ることができないため、添加量
は、重量％で１．５〜１４％の範囲で含有させることが
好ましい。Cr is a component that improves corrosion resistance.
By adding r to the nickel-based single crystal heat-resistant superalloy, not only the formation of the reaction hardened layer can be suppressed, but also the corrosion resistance can be improved. However, excessive addition of Cr causes a decrease in high-temperature strength, and if the amount is insufficient, it is not possible to obtain a predetermined corrosion resistance. Therefore, the amount of Cr added is 1.5 to 14% by weight. Preferably.
【００２７】Ｃｏは基地であるγ層中に固溶して高温強
度を向上させる効果がある。しかし、過剰に添加すると
主強化層であるγ' 層の析出を抑制し、添加量が足りな
い場合には強度の向上が図れないため、２〜１０％の範
囲で含有させることが好ましい。 Ｗ、Ｍｏはγ層を固
溶強化する元素である。しかし、過剰に添加すると金属
間化合物やＷ、Ｍｏの一次固溶体を析出して高温強度を
低下させ、添加量が足りない場合には固溶強化の向上が
図れない。従って、Ｗ ４〜９％、Ｍｏ ０．２５〜２
％の範囲で含有させることが好ましい。Co has the effect of improving the high-temperature strength by forming a solid solution in the γ-layer serving as the matrix. However, if added excessively, the precipitation of the γ ′ layer as the main reinforcing layer is suppressed, and if the amount is insufficient, the strength cannot be improved. W and Mo are elements for solid solution strengthening of the γ layer. However, if it is added excessively, it precipitates an intermetallic compound or a primary solid solution of W or Mo, lowering the high-temperature strength. If the amount is insufficient, improvement of solid solution strengthening cannot be achieved. Therefore, W 4-9%, Mo 0.25-2
% Is preferably contained.
【００２８】Ｔａは主として、γ' 層を固溶強化して高
温強度を向上させる。しかし、過剰な添加は共晶γ' 層
の固溶を困難にし、かえって高温強度を低下させてしま
う。また、添加量が足りない場合にはγ' 層の固溶強化
を図れない。従って、Ｔａの含有量は４〜１０％である
ことが好ましい。Ta mainly improves the high temperature strength by solid solution strengthening of the γ ′ layer. However, excessive addition makes it difficult to form a solid solution of the eutectic γ 'layer, and rather lowers the high-temperature strength. On the other hand, if the amount of addition is insufficient, solid solution strengthening of the γ 'layer cannot be achieved. Therefore, the content of Ta is preferably 4 to 10%.
【００２９】ＡｌとＴｉは主強化層であるγ' 層を生成
するための主要合金元素であり、タービン翼等に必要な
高温強度の向上に寄与するものである。しかし、添加量
が少ないと主強化層であるγ' 層の生成が少なく、所定
の強度が得られず、添加量が多すぎると高温強度の低下
をもたらす。従って、Ａｌ ３〜７％、Ｔｉ ０．１〜
５％の範囲で含有することが好ましい。Al and Ti are the main alloying elements for forming the γ 'layer, which is the main reinforcing layer, and contribute to the improvement of the high-temperature strength required for turbine blades and the like. However, when the addition amount is small, the formation of the γ ′ layer as the main reinforcing layer is small, and a predetermined strength cannot be obtained. When the addition amount is too large, the high-temperature strength decreases. Therefore, Al 3-7%, Ti 0.1-
It is preferable to contain it in the range of 5%.
【００３０】本発明のニッケル基単結晶耐熱超合金に
は、さらにＲｅ、Ｎｂ及びＨｆからなる群から選ばれた
少なくとも１種の元素が含まれていてもよい。The nickel-base single crystal heat-resistant superalloy of the present invention may further contain at least one element selected from the group consisting of Re, Nb and Hf.
【００３１】これらの元素の含有量は次の範囲であるこ
とが望ましい。It is desirable that the contents of these elements fall within the following ranges.
【００３２】Ｒｅ ２．５〜７ｗｔ％、Ｎｂ ０．０４
〜０．２ｗｔ％、Ηｆ ０．０１〜０．１５ｗｔ％。Re 2.5-7 wt%, Nb 0.04
０．２0.2 wt%, Δf 0.01 to 0.15 wt%.
【００３３】上記Ｒｅ、Ｎｂ及びＨｆの添加量を上記の
範囲としたのは次の理由による。The reason why the amounts of Re, Nb and Hf are set in the above ranges is as follows.
【００３４】Ｒｅはγ層を固溶強化する元素である。し
かし、過剰に添加すると金属間化合物やＲｅの一次固溶
体を析出して高温強度を低下させ、添加量が足りない場
合にはγ層の固溶強化が図れないため、含有量は２．５
〜７％であることが好ましい。 Ｎｂは主にγ' 層を固
溶強化して高温強度を向上させるものである。しかし、
過剰な添加は共晶γ' 層の固溶を困難にし高温強度をか
えって低下させてしまい、添加量が少ない場合にはγ'
層の固溶強化が図れないため、含有量は０．０４〜０．
２％が好ましい。Re is an element for solid solution strengthening the γ layer. However, if it is added excessively, it precipitates a primary solid solution of an intermetallic compound or Re, lowering the high-temperature strength. If the amount is insufficient, solid solution strengthening of the γ layer cannot be achieved.
It is preferably about 7%. Nb enhances the high temperature strength mainly by solid solution strengthening of the γ 'layer. But,
Excessive addition makes it difficult to form a solid solution of the eutectic γ 'layer and lowers the high-temperature strength.
Since the solid solution strengthening of the layer cannot be achieved, the content is 0.04 to 0.5.
2% is preferred.
【００３５】Ｈｆは耐酸化性および耐食保護被膜の密着
性を向上させるものである。しかし、過剰な添加は合金
の融点を下げてγ' 層の固溶を困難にして高温強度低下
の原因となり、添加量が足りない場合には上記効果を向
上させることができないため、０．０１〜０．１５％の
範囲とすることが好ましい。Hf improves the oxidation resistance and the adhesion of the corrosion-resistant protective film. However, excessive addition lowers the melting point of the alloy and makes it difficult to form a solid solution in the γ 'layer, causing a decrease in high-temperature strength. If the addition amount is insufficient, the above effect cannot be improved. It is preferable to set the range of 0.15% to 0.15%.
【００３６】本発明のニッケル基単結晶耐熱超合金は、
ニッケル基単結晶合金を形成可能な基準合金に、Ｐｒ、
Νｄ、Ｓｍ、Ｄｙ、Ｅｒ及びＴｈからなる群から選ばれ
た少なくとも１種の元素を重量で、０．５〜５ｐｐｍ添
加して合金化する工程と、前記所定の組成の合金を再溶
解する工程と、前記再溶解した所定の組成の溶湯を方向
凝固させる工程を含む製造方法により製作することがで
きる。The nickel-base single crystal heat-resistant superalloy of the present invention
Pr, as a reference alloy capable of forming a nickel-based single crystal alloy,
工程 a step of adding 0.5 to 5 ppm by weight of at least one element selected from the group consisting of d, Sm, Dy, Er and Th to form an alloy, and a step of remelting the alloy having the predetermined composition And a step of directional solidification of the re-melted melt having a predetermined composition.
【００３７】また、本発明のニッケル基単結晶耐熱超合
金は、ニッケル基単結晶合金を形成可能な基準合金を溶
解する工程と、前記溶解した基準合金からなる溶湯にＰ
ｒ、Ｎｄ、Ｓｍ、Ｄｙ、Ｅｒ及びＴｈからなる群から選
ばれた少なくとも１種の元素を重量で、０．５〜５ｐｐ
ｍ添加する工程と、前記元素の添加された溶湯を方向凝
固させる工程とを含む製造方法によっても製造すること
ができる。Further, the nickel-base single crystal heat-resistant superalloy of the present invention comprises a step of melting a reference alloy capable of forming a nickel-base single crystal alloy;
at least one element selected from the group consisting of r, Nd, Sm, Dy, Er, and Th, by weight, from 0.5 to 5 pp
It can also be manufactured by a manufacturing method including a step of adding m and a step of directionally solidifying the molten metal to which the element has been added.
【００３８】具体的には、本発明のタービン翼は、チル
プレート（冷却板）上に構築した鋳型を加熱炉内に設置
し、高温に保持した前記鋳型中へニッケル基単結晶耐熱
超合金の溶湯を注ぎ込み、加熱炉から鋳型をチルプレー
トとともに一方向（翼長手方向）に沿って徐々に引抜く
ことにより溶湯をチルプレート側から凝固させる方向凝
固プロセスによって製造することができる。Specifically, in the turbine blade of the present invention, a mold constructed on a chill plate (cooling plate) is placed in a heating furnace, and a nickel-based single crystal heat-resistant superalloy is placed in the mold maintained at a high temperature. It can be manufactured by a directional solidification process in which the molten metal is solidified from the chill plate side by pouring the molten metal and gradually pulling out the mold from the heating furnace along with the chill plate along one direction (blade longitudinal direction).
【００３９】本発明のニッケル基単結晶耐熱超合金に添
加される、Ｐｒ、Νｄ、Ｓｍ、Ｄｙ、Ｅｒ及びＴｈから
なる群から選ばれた少なくとも１種の元素は、所定の範
囲の量を含有させることにより、溶湯と鋳型又は中子と
の反応により生じる反応硬化層の生成を抑制する作用を
する。At least one element selected from the group consisting of Pr, Δd, Sm, Dy, Er and Th added to the nickel-base single crystal heat-resistant superalloy of the present invention contains an amount in a predetermined range. This has the effect of suppressing the formation of a reaction hardened layer generated by the reaction between the molten metal and the mold or the core.
【００４０】本発明における上記の添加元素による、反
応硬化層の抑制原理は、以下のように考えられる。The principle of suppressing the reaction hardened layer by the above-mentioned additional element in the present invention is considered as follows.
【００４１】すなわち、Ｐｒ、Ｎｄ、Ｓｍ、Ｄｙ、Ｅ
ｒ、Ｔｈは、Νｉ中にほとんど固溶限を持っていない。
従って、これらの元素は溶湯中では液相領域よりも固液
界面に逃れ、単一相として合金溶湯と鋳型あるいは中子
間の界面で相分離し、溶湯と鋳型あるいは中子との接触
を遮断する。このように、溶湯と鋳型等が接触しないた
め、これらが反応することもなく、このため反応硬化層
の生成が抑制され、本発明のニッケル基単結晶耐熱超合
金により製作されたタービン翼は高温強度が改善される
のである。That is, Pr, Nd, Sm, Dy, E
r and Th have almost no solid solubility limit in Δi.
Therefore, these elements escape to the solid-liquid interface rather than the liquid phase region in the molten metal, separate as a single phase at the interface between the molten alloy and the mold or core, and block contact between the molten metal and the mold or core. I do. As described above, since the molten metal does not come into contact with the mold and the like, they do not react with each other, thereby suppressing the formation of a reaction hardened layer, and the turbine blade made of the nickel-based single crystal heat-resistant superalloy of the present invention has a high temperature. The strength is improved.
【００４２】本発明のタービン翼は、鋳造によって表面
に反応硬化層が形成されないので、高温強度に優れた特
性を有している。The turbine blade of the present invention does not form a reaction hardened layer on the surface by casting, and thus has excellent high-temperature strength characteristics.
【００４３】[0043]
【発明の実施の形態】以下、本発明を実施するための形
態について説明する。Embodiments of the present invention will be described below.
【００４４】まず、本発明のニッケル基単結晶耐熱超合
金を用いたタービン翼について説明する。First, a turbine blade using the nickel-base single crystal heat-resistant superalloy of the present invention will be described.
【００４５】本発明のタービン翼は、図９に示されるよ
うに、一般に、シュラウド部分１、ブレード部分２、及
び根元部分３から構成されている。As shown in FIG. 9, the turbine blade of the present invention generally comprises a shroud portion 1, a blade portion 2, and a root portion 3.
【００４６】このような本発明のタービン翼において、
単結晶はブレード部分２の縦軸線方向に［００１］配向
を有することが好ましい。しかし、単結晶の［００１］
配向とブレード部分２の縦軸線方向とは必ずしも正確に
一致する必要はなく、２０°程度のずれが許容できる。In such a turbine blade of the present invention,
The single crystal preferably has a [001] orientation in the direction of the longitudinal axis of the blade portion 2. However, single crystal [001]
The orientation and the direction of the longitudinal axis of the blade portion 2 do not necessarily need to exactly match, and a deviation of about 20 ° is acceptable.
【００４７】このような本発明のタービン翼は、公知技
術である方向凝固プロセス等を用いて本発明のニッケル
基単結晶耐熱超合金で製造することができる。Such a turbine blade of the present invention can be manufactured from the nickel-base single crystal heat-resistant superalloy of the present invention by using a known technique such as a directional solidification process.
【００４８】本発明のタービン翼は、発電用タービン等
のタービン翼に用いることによって、タービンの高温で
の運用を可能にして発電効率を一層向上させることがで
きる。 また、従来は高温強度に課題があった長尺ター
ビン翼の作製も、本発明のニッケル基単結晶耐熱超合金
を用いることにより可能となる。By using the turbine blade of the present invention for a turbine blade such as a power generation turbine, the turbine can be operated at a high temperature, and the power generation efficiency can be further improved. In addition, it is possible to produce a long turbine blade, which conventionally has a problem in high-temperature strength, by using the nickel-based single crystal heat-resistant superalloy of the present invention.
【００４９】[0049]
【実施例】次に、本発明の具体的な実施例について述べ
る。Next, specific examples of the present invention will be described.
【００５０】実施例１ 米国特許第 4,582,548において開示されたＣＭＳＸ−２
合金（Ｃｒ ８ｗｔ％，Ｃｏ ５ｗｔ％，Ｍｏ ０．６
ｗｔ％，Ｗ ８ｗｔ％，Ｔａ ６ｗｔ％，Ａｌ５．６ｗ
ｔ％，Ｔｉ １ｗｔ％，残部はＮｉ）を基準合金として
用い、所定の量のＰｒ、Νｄ、Ｓｍ、Ｄｙ、Ｅｒ及びＴ
ｈからなる群から選ばれた少なくとも１種の元素（以
下、溶湯反応抑制元素という。）を添加してニッケル基
単結晶耐熱超合金を作製し評価を行った。Example 1 CMSX-2 disclosed in US Pat. No. 4,582,548
Alloy (Cr 8 wt%, Co 5 wt%, Mo 0.6
wt%, W 8 wt%, Ta 6 wt%, Al 5.6 w
t, 1 wt% of Ti, and the balance of Ni) were used as reference alloys, and predetermined amounts of Pr, Δd, Sm, Dy, Er and T were used.
h, at least one element selected from the group consisting of h (hereinafter, referred to as a molten metal reaction suppressing element) was added to produce a nickel-based single crystal heat-resistant superalloy, which was evaluated.
【００５１】基準合金の組成ならびにこの基準合金に所
定の量の添加元素を添加した、本発明の実施例及び比較
例の化学組成を表１に示す。Table 1 shows the composition of the reference alloy and the chemical compositions of Examples and Comparative Examples of the present invention in which a predetermined amount of an additional element was added to the reference alloy.
【００５２】[0052]
【表１】 表１に示すように、本発明の実施例は基準合金に溶湯反
応抑制元素を０．５〜５ｐｐｍの範囲で添加した。比較
例は、前記範囲外で溶湯反応抑制元素を添加したもので
本発明との比較のために示したものである。[Table 1] As shown in Table 1, in Examples of the present invention, a molten metal reaction inhibiting element was added to a reference alloy in a range of 0.5 to 5 ppm. The comparative example is one in which a molten metal reaction-inhibiting element is added outside the above range and is shown for comparison with the present invention.
【００５３】次に本発明の実施例、比較例の製造につい
て説明する。Next, the production of Examples and Comparative Examples of the present invention will be described.
【００５４】基準合金ＣＭＳＸ−２を溶解し、溶湯反応
抑制元素を添加した後、冷却して所定の組成の合金を作
製した。さらに、この合金を再溶解して溶湯を作製し、
この溶湯を、中空部を形成するための中子を設置した鋳
型に注湯し、［００１］の結晶方位に方向凝固させた。
鋳型は合金と接する第１層をジルコン（ＺｒＳｉ
Ｏ4）、バックアップ層をアルミナ（Ａｌ2 Ｏ3 ）、中
子をジルコニア（ＺｒＯ2 ）とした。The reference alloy CMSX-2 was melted, and a molten metal reaction suppressing element was added. After cooling, an alloy having a predetermined composition was produced. Furthermore, this alloy is re-melted to produce a molten metal,
This molten metal was poured into a mold provided with a core for forming a hollow portion, and was directionally solidified in the [001] crystal orientation.
The mold has a first layer in contact with the alloy, zircon (ZrSi).
O 4 ), the backup layer was alumina (Al 2 O 3 ), and the core was zirconia (ZrO 2 ).
【００５５】表２、図１に反応硬化層厚さの測定結果を
示す。反応硬化層厚さとは、鋳造時に鋳型あるいは中子
のいずれかに生成した反応硬化層の最大厚さのことであ
る。Table 2 and FIG. 1 show the measurement results of the thickness of the reaction hardened layer. The reaction hardened layer thickness refers to the maximum thickness of the reaction hardened layer formed on either the mold or the core during casting.
【表２】 溶湯反応抑制元素の添加量が０．５ｐｐｍ未満の比較例
（ＣＰｒ１、ＣＮｄ１、ＣＳｍ１、ＣＤｙ１、ＣＥｒ
１、ＣＴｈ１）には添加元素が溶湯と鋳型又は中子の界
面に吸着して、濡れ性が向上したため、基準合金ＣＭＳ
Ｘ−２だけの場合よりも厚い反応硬化層を生成した。こ
れに対して、溶湯反応抑制元素を０．５ｐｐｍ以上添加
した本発明の実施例、比較例（ＣＰｒ２、ＣＮｄ２、Ｃ
Ｓｍ２、ＣＤｙ２、ＣＥｒ２、ＣＴｈ２）では、反応硬
化層はほとんど生成されなかった。[Table 2] Comparative examples (CPr1, CNd1, CSm1, CDy1, CEr) in which the addition amount of the molten metal reaction-inhibiting element is less than 0.5 ppm
1, CTh1), the added element was adsorbed on the interface between the molten metal and the mold or the core, and the wettability was improved.
A thicker reaction hardened layer was produced than when only X-2 was used. In contrast, Examples and Comparative Examples (CPr2, CNd2, C
(Sm2, CDy2, CEr2, CTh2), the reaction hardened layer was hardly formed.
【００５６】続いて、反応硬化層がほとんど生成されな
かった本発明の実施例、比較例（ＣＰｒ２、ＣＮｄ２、
ＣＳｍ２、ＣＤｙ２、ＣＥｒ２、ＣＴｈ２）について、
試験温度 １０５０℃、負荷応力 １３６ＭＰａでクリ
ープ破断試験を行った。Subsequently, Examples of the present invention and Comparative Examples (CPr2, CNd2,
CSm2, CDy2, CEr2, CTh2)
A creep rupture test was performed at a test temperature of 1050 ° C. and a load stress of 136 MPa.
【００５７】試験結果を表２、図２に示す。なお、基準
合金ＣＭＳＸ−２については、純粋に材料自身の高温強
度を比較するため、反応硬化層を除去した試験材で試験
を行った。溶湯反応抑制元素の添加量が５ｐｐｍ以上の
比較例（ＣＰｒ２、ＣＮｄ２、ＣＳｍ２、ＣＤｙ２、Ｃ
Ｅｒ２、ＣＴｈ２）では、添加元素と基材のニッケルが
Ｍ2 Ｎｉ17の金属間化合物を生成するためにクリープ破
断時間が基準合金よりも低下した。一方、溶湯反応抑制
元素の添加量が５ｐｐｍ以下である本発明の実施例は基
準合金ＣＭＳＸ−２と同等の破断時間を有していた。The test results are shown in Table 2 and FIG. In addition, about the reference alloy CMSX-2, in order to compare purely the high temperature strength of the material itself, the test was performed using the test material from which the reaction hardened layer was removed. Comparative examples (CPr2, CNd2, CSm2, CDy2, C
In Er2, CTh2), the creep rupture time was shorter than that of the reference alloy because the additive element and the nickel of the base material formed an intermetallic compound of M 2 Ni 17 . On the other hand, Examples of the present invention in which the amount of the molten metal reaction-inhibiting element added was 5 ppm or less had a rupture time equivalent to that of the reference alloy CMSX-2.
【００５８】これらの結果より、溶湯反応抑制元素を重
量％で０．５〜５ｐｐｍで添加することにより、合金の
高温強度を維持したまま溶湯反応を抑制することができ
ることが分かる。From these results, it can be seen that the addition of the molten metal reaction-inhibiting element at 0.5 to 5 ppm by weight can suppress the molten metal reaction while maintaining the high-temperature strength of the alloy.
【００５９】実施例２ 米国特許第 5,489,346において開示されたＣＭＳＸ−１
１Ｂ（Ｃｒ １２．５ｗｔ％，Ｃｏ ７ｗｔ％，Ｍｏ
０．５ｗｔ％，Ｗ ５ｗｔ％，Ｔａ ５ｗｔ％，Ｒｅ
０．１ｗｔ％，Ａｌ ３．６ｗｔ％，Ｔｉ ４．２ｗｔ
％，Ｈｆ ０．０４，残部はＮｉ）を基準合金として用
い、本発明の実施例、比較例を作製し評価を行った。Example 2 CMSX-1 disclosed in US Pat. No. 5,489,346
1B (Cr 12.5 wt%, Co 7 wt%, Mo
0.5 wt%, W 5 wt%, Ta 5 wt%, Re
0.1 wt%, Al 3.6 wt%, Ti 4.2 wt
%, Hf 0.04, and the balance of Ni) were used as reference alloys to evaluate and evaluate examples of the present invention and comparative examples.
【００６０】本発明の実施例、比較例及び基準合金の化
学組成を表３に示す。Table 3 shows the chemical compositions of the examples, comparative examples and reference alloys of the present invention.
【００６１】[0061]
【表３】 本発明の実施例、比較例は、溶湯を作製するため基準合
金を再溶解した際に、溶湯反応抑制元素を添加し、この
溶湯を鋳型に注湯し、［００１］結晶方位の単結晶中空
丸棒の形状に方向凝固させて作製した。[Table 3] In Examples and Comparative Examples of the present invention, when a reference alloy was re-melted to produce a molten metal, a molten metal reaction inhibiting element was added, the molten metal was poured into a mold, and a single crystal hollow having a [001] crystal orientation was formed. It was produced by directional solidification into the shape of a round bar.
【００６２】表４、図３に反応硬化層厚さの測定結果を
示す。Table 4 and FIG. 3 show the measurement results of the thickness of the reaction hardened layer.
【００６３】[0063]
【表４】 溶湯反応抑制元素を０．５ｐｐｍ以上添加した本発明の
実施例、比較例（ＣＰｒ４、ＣＮｄ４、ＣＳｍ４、ＣＤ
ｙ４、ＣＥｒ４、ＣＴｈ４）は基準合金と比較して、ほ
とんど反応硬化層を生成していなかった。[Table 4] Examples and Comparative Examples (CPr4, CNd4, CSm4, CD
y4, CEr4, CTh4) hardly produced a reaction hardened layer as compared with the reference alloy.
【００６４】続いて、反応硬化層が生成していない本発
明の実施例と比較例（ＣＰｒ４、ＣＮｄ４、ＣＳｍ４、
ＣＤｙ４、ＣＥｒ４、ＣＴｈ４）から得た試験片で実施
例１と同条件でクリープ破断試験を行った。ＣＭＳＸ−
１１のクリープ破断寿命は実施例１と同じく反応硬化層
を除去した試験材で評価した。Subsequently, the examples of the present invention and the comparative examples (CPr4, CNd4, CSm4,
A creep rupture test was performed on the test pieces obtained from CDy4, CEr4, and CTh4) under the same conditions as in Example 1. CMSX-
The creep rupture life of No. 11 was evaluated using the test material from which the reaction hardened layer was removed as in Example 1.
【００６５】クリープ破断試験の結果を表４、図４に示
す。The results of the creep rupture test are shown in Table 4 and FIG.
【００６６】溶湯反応抑制元素を５ｐｐｍ以上添加した
比較例（ＣＰｒ４、ＣＮｄ４、ＣＳｍ４、ＣＤｙ４、Ｃ
Ｅｒ４、ＣＴｈ４）は全て金属間化合物Ｍ2 Ｎｉ17を形
成し、クリープ破断寿命が低下した。これに対して、溶
湯反応抑制元素Ｐｒ、Ｎｄ、Ｓｍ、Ｄｙ、Ｅｒ及びＴｈ
の含有量が０．５〜５ｐｐｍの本発明の実施例では基準
合金の高温強度を変化させることなく、反応硬化層を抑
制していた。Comparative Examples (CPr4, CNd4, CSm4, CDy4, C
Er4, CTh4) all formed the intermetallic compound M 2 Ni 17 and the creep rupture life was reduced. On the other hand, the molten metal reaction inhibiting elements Pr, Nd, Sm, Dy, Er and Th
In the examples of the present invention having a content of 0.5 to 5 ppm, the reaction hardened layer was suppressed without changing the high-temperature strength of the reference alloy.
【００６７】実施例３ 米国特許第 4,643,782において開示されたＣＭＳＸ−４
Ｂ（Ｃｒ ６．５ｗｔ％，Ｃｏ ９ｗｔ％，Ｍｏ ０．
６ｗｔ％，Ｗ ６ｗｔ％，Ｔａ ６．５ｗｔ％，Ｒｅ
３ｗｔ％，Ａｌ ５．６ｗｔ％，Ｔｉ １ｗｔ％，Ｈｆ
０．１，残部はＮｉ）を基準合金として用い、本発明
の実施例、比較例を作製し評価を行った。Example 3 CMSX-4 disclosed in US Pat. No. 4,643,782
B (Cr 6.5 wt%, Co 9 wt%, Mo 0.
6 wt%, W 6 wt%, Ta 6.5 wt%, Re
3 wt%, Al 5.6 wt%, Ti 1 wt%, Hf
Examples of the present invention and comparative examples were prepared and evaluated using 0.1 as a reference alloy and the rest as Ni.
【００６８】本発明の実施例、比較例及び基準合金の化
学組成を表５に示す。Table 5 shows the chemical compositions of the examples, comparative examples and reference alloys of the present invention.
【００６９】[0069]
【表５】 次に本発明の実施例、比較例の作製について説明する。[Table 5] Next, production of examples and comparative examples of the present invention will be described.
【００７０】基準合金ＣＭＳＸ−４Ｂを溶解し、溶湯反
応抑制元素を添加した後、冷却して所定の組成の合金を
作製した。さらに、この合金を再溶解して溶湯を作製
し、この溶湯を、初層イットリアの鋳型に注湯して、結
晶方位［００１］の中空翼に方向凝固させた。After the reference alloy CMSX-4B was melted, and a molten metal reaction suppressing element was added, the alloy was cooled to produce an alloy having a predetermined composition. Further, the alloy was remelted to prepare a molten metal, and the molten metal was poured into a mold of the first layer yttria and directionally solidified into hollow blades having a crystal orientation of [001].
【００７１】表６、図５に反応硬化層厚さの測定結果を
示す。Table 6 and FIG. 5 show the measurement results of the thickness of the reaction hardened layer.
【００７２】[0072]
【表６】 溶湯反応抑制元素を０．５ｐｐｍ以下添加した比較例
（ＣＰｒ５、ＣＮｄ５、ＣＳｍ５、ＣＤｙ５、ＣＥｒ
５、ＣＴｈ５）では反応硬化層の生成を抑制することは
できなかった。溶湯反応抑制元素を５ｐｐｍ以上添加し
た比較例（ＣＰｒ６、ＣＮｄ６、ＣＳｍ６、ＣＤｙ６、
ＣＥｒ６、ＣＴｈ６）は、表６、図６のクリープ破断試
験結果（試験条件：１０５０℃、１３６ＭＰａ）に示さ
れるように、金属間化合物Ｍ2 Ｎｉ17の生成により、ク
リープ破断寿命が低下していた。これに対して、溶湯反
応抑制元素を０．５〜５ｐｐｍの範囲で含有する本発明
の実施例では、反応硬化層の生成もほとんどなく、高温
強度も基準合金並に確保されていることが分かる。[Table 6] Comparative examples in which a molten metal reaction-inhibiting element is added in an amount of 0.5 ppm or less (CPr5, CNd5, CSm5, CDy5, CEr
5, CTh5), the formation of a reaction hardened layer could not be suppressed. Comparative examples in which a molten metal reaction-inhibiting element was added at 5 ppm or more (CPr6, CNd6, CSm6, CDy6,
CEr6, CTh6), as shown in the creep rupture test results in Table 6 and FIG. 6 (test conditions: 1050 ° C., 136 MPa), the creep rupture life was reduced due to the formation of the intermetallic compound M 2 Ni 17 . . On the other hand, in the example of the present invention containing the element for suppressing the reaction of the molten metal in the range of 0.5 to 5 ppm, it is understood that the reaction hardened layer is hardly generated, and the high temperature strength is secured as high as the reference alloy. .
【００７３】実施例４ 米国特許第 5,366,695において開示されたＣＭＳＸ−１
０（Ｃｒ ２ｗｔ％，Ｃｏ ３ｗｔ％，Ｍｏ ０．４ｗ
ｔ％，Ｗ ５ｗｔ％，Ｔａ ８ｗｔ％，Ｒｅ６ｗｔ％，
Ｎｂ ０．１ｗｔ％，Ａｌ ５．７ｗｔ％，Ｔｉ ０．
２ｗｔ％，Ｈｆ ０．０３，残部はＮｉ）を基準合金と
して用い、本発明の実施例、比較例を作製し評価を行っ
た。Example 4 CMSX-1 disclosed in US Pat. No. 5,366,695
0 (Cr 2 wt%, Co 3 wt%, Mo 0.4 w
t%, W 5wt%, Ta 8wt%, Re6wt%,
Nb 0.1 wt%, Al 5.7 wt%, Ti 0.
Using 2 wt%, Hf 0.03, and the balance of Ni) as reference alloys, Examples of the present invention and Comparative Examples were prepared and evaluated.
【００７４】本発明の実施例、比較例及び基準合金の化
学組成を表７に示す。Table 7 shows the chemical compositions of the examples, comparative examples, and reference alloys of the present invention.
【００７５】[0075]
【表７】 本発明の実施例及び比較例は、溶湯を作製するため基準
合金を再溶解した際に、溶湯反応抑制元素のうちいずれ
か１種を添加して溶湯を作製し、この溶湯を実施例３と
同様の鋳型を用いて、中空丸棒の形状に形成することに
よって作製した。[Table 7] In Examples and Comparative Examples of the present invention, when the reference alloy was re-melted to produce a molten metal, one of the molten metal reaction-suppressing elements was added to produce a molten metal. It was produced by using a similar mold to form a hollow round bar.
【００７６】本発明の実施例、比較例の反応硬化層厚さ
の測定結果及びクリープ破断試験（試験条件：１０５０
℃、１３６ＭＰａ）の試験結果をそれぞれ図７、図８そ
して表８に示す。The measurement results of the thickness of the reaction hardened layer and the creep rupture test (test conditions: 1050) of the examples and comparative examples of the present invention
7, 136 MPa) are shown in FIGS. 7, 8 and Table 8, respectively.
【００７７】[0077]
【表８】 溶湯反応抑制元素を０．５〜５ｐｐｍで添加した本発明
の実施例、比較例は、基準合金が有する高温強度を低下
させることなく、反応硬化層の生成を抑制していたのに
対し、その範囲以外の含有量を有する比較合金は反応硬
化層の生成や高温強度の低下が生じていた。[Table 8] In Examples and Comparative Examples of the present invention in which the molten metal reaction inhibiting element was added at 0.5 to 5 ppm, the formation of the reaction hardened layer was suppressed without lowering the high-temperature strength of the reference alloy. The comparative alloys having a content outside the range had a reaction hardened layer and reduced high-temperature strength.
【００７８】[0078]
【発明の効果】ニッケル基単結晶耐熱超合金にΡｒ、Ｎ
ｄ、Ｓｍ、Ｄｙ、Ｅｒ及びＴｈのうち少なくとも１種以
上を重量で０．５〜５ｐｐｍの範囲内で添加することに
より、基材合金の高温強度特性を損なうことなく、鋳造
時の反応硬化層の生成を防止し、健全な単結晶鋳物を提
供することができる。EFFECTS OF THE INVENTION Δr, N
By adding at least one of d, Sm, Dy, Er and Th in the range of 0.5 to 5 ppm by weight, the reaction hardened layer at the time of casting can be obtained without impairing the high temperature strength characteristics of the base alloy. Can be prevented, and a sound single crystal casting can be provided.
【００７９】また、このようなニッケル基単結晶耐熱超
合金を用いてタービン翼を作製することによって、高温
・高効率ガスタービンでの運用が可能となり、発電等の
効率向上に大きく寄与することができる。Further, by manufacturing a turbine blade using such a nickel-base single crystal heat-resistant superalloy, it is possible to operate a high-temperature and high-efficiency gas turbine, which greatly contributes to the improvement of efficiency of power generation and the like. it can.
【図面の簡単な説明】[Brief description of the drawings]
【図１】 実施例１の反応硬化層の最大厚さの計測結果
を示す図である。FIG. 1 is a view showing a measurement result of a maximum thickness of a reaction hardened layer of Example 1.
【図２】 実施例１のクリープ破断試験結果の破断寿命
を示す図である。FIG. 2 is a view showing a rupture life as a result of a creep rupture test of Example 1.
【図３】 実施例２の反応硬化層の最大厚さの計測結果
を示す図である。FIG. 3 is a view showing a measurement result of a maximum thickness of a reaction hardened layer of Example 2.
【図４】 実施例２のクリープ破断試験結果の破断寿命
を示す図である。FIG. 4 is a view showing a rupture life as a result of a creep rupture test of Example 2.
【図５】 実施例３の反応硬化層の最大厚さの計測結果
を示す図である。FIG. 5 is a view showing a measurement result of a maximum thickness of a reaction hardened layer of Example 3.
【図６】 実施例３のクリープ破断試験結果の破断寿命
を示す図である。FIG. 6 is a diagram showing a rupture life of a creep rupture test result of Example 3.
【図７】 実施例４の反応硬化層の最大厚さの計測結果
を示す図である。FIG. 7 is a view showing a measurement result of a maximum thickness of a reaction hardened layer of Example 4.
【図８】 実施例４のクリープ破断試験結果の破断寿命
を示す図である。FIG. 8 is a view showing a rupture life of a creep rupture test result of Example 4.
【図９】 本発明のタービン翼の一例を示す図である。FIG. 9 is a diagram showing an example of a turbine blade of the present invention.
Claims (6)
からなる群から選ばれた少なくとも１種の元素を重量
で、０．５〜５ｐｐｍ含有することを特徴とするニッケ
ル基単結晶耐熱超合金。1. Pr, Νd, Sm, Dy, Er and Th
A nickel-based single crystal heat-resistant superalloy comprising at least one element selected from the group consisting of: 0.5 to 5 ppm by weight.
Ｔｉからなる群から選ばれた少なくとも１種の元素を、
各元素に応じ下記の範囲で含有し、 Ｃｒ １．５〜１４ｗｔ％、Ｃｏ ２〜１０ｗｔ％、Ｗ
４〜９ｗｔ％、Ｔａ４〜１０ｗｔ％、Ｍｏ ０．２５
〜２ｗｔ％、Ａｌ ３〜７ｗｔ％、Ｔｉ ０．１〜５ｗ
ｔ％ さらに、Ｐｒ、Νｄ、Ｓｍ、Ｄｙ、Ｅｒ及びＴｈからな
る群から選ばれた少なくとも１種の元素を重量で、０．
５〜５ｐｐｍ含有することを特徴とするニッケル基単結
晶耐熱超合金。2. At least one element selected from the group consisting of Cr, Co, W, Ta, Mo, Al and Ti,
Depending on each element, it is contained in the following range, Cr: 1.5 to 14 wt%, Co: 2 to 10 wt%, W
4 to 9 wt%, Ta4 to 10 wt%, Mo 0.25
~ 2wt%, Al 3 ~ 7wt%, Ti 0.1 ~ 5w
t% Further, at least one element selected from the group consisting of Pr, Νd, Sm, Dy, Er and Th is added in an amount of 0.1% by weight.
A nickel-based single crystal heat-resistant superalloy characterized by containing 5 to 5 ppm.
れた少なくとも１種の元素を、各元素に応じ下記の範囲
で含有すること Ｒｅ ２．５〜７ｗｔ％、Ｎｂ ０．０４〜０．２ｗｔ
％、Ηｆ ０．０１〜０．１５ｗｔ％ を特徴とする請求項２記載のニッケル基単結晶耐熱超合
金。3. An alloy containing at least one element selected from the group consisting of Re, Nb and Hf in the following range according to each element: Re 2.5 to 7 wt%, Nb 0.04 to 0.4%. 2wt
%, Δf 0.01 to 0.15 wt%.
合金に、Ｐｒ、Νｄ、Ｓｍ、Ｄｙ、Ｅｒ及びＴｈからな
る群から選ばれた少なくとも１種の元素を重量で、０．
５〜５ｐｐｍ添加して合金化する工程と、 前記所定の組成の合金を再溶解する工程と、 前記再溶解した所定の組成の溶湯を方向凝固させる工程
とを具備することを特徴とするニッケル基単結晶耐熱超
合金の製造方法。4. A reference alloy capable of forming a nickel-based single crystal alloy, wherein at least one element selected from the group consisting of Pr, Δd, Sm, Dy, Er and Th is added in an amount of 0.1 wt.
A nickel-based alloy comprising: a step of alloying by adding 5 to 5 ppm; a step of remelting the alloy having the predetermined composition; and a step of directionally solidifying the remelted molten metal having the predetermined composition. Manufacturing method of single crystal heat resistant superalloy.
合金を溶解する工程と、 前記溶解した基準合金からなる溶湯にＰｒ、Ｎｄ、Ｓ
ｍ、Ｄｙ、Ｅｒ及びＴｈからなる群から選ばれた少なく
とも１種の元素を重量で、０．５〜５ｐｐｍ添加する工
程と、 前記元素の添加された溶湯を所定形状の鋳型に注湯して
方向凝固させる工程とを具備することを特徴とするニッ
ケル基単結晶耐熱超合金の製造方法。5. A step of melting a reference alloy capable of forming a nickel-based single crystal alloy, wherein Pr, Nd, S
adding 0.5 to 5 ppm by weight of at least one element selected from the group consisting of m, Dy, Er, and Th; and pouring the molten metal with the element added into a mold having a predetermined shape. And a step of directional solidification.
ッケル基単結晶耐熱超合金から成るタービン翼。6. A turbine blade made of the nickel-based single crystal heat-resistant superalloy according to claim 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14367099A JP4223627B2 (en) | 1999-05-24 | 1999-05-24 | Nickel-based single crystal heat-resistant superalloy, manufacturing method thereof, and turbine blade using nickel-based single crystal heat-resistant superalloy |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14367099A JP4223627B2 (en) | 1999-05-24 | 1999-05-24 | Nickel-based single crystal heat-resistant superalloy, manufacturing method thereof, and turbine blade using nickel-based single crystal heat-resistant superalloy |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2000328162A true JP2000328162A (en) | 2000-11-28 |
| JP4223627B2 JP4223627B2 (en) | 2009-02-12 |
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ID=15344216
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
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| Country | Link |
|---|---|
| JP (1) | JP4223627B2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005274124A (en) * | 2004-02-12 | 2005-10-06 | General Electric Co <Ge> | Combustor member for manufacturing combuster assembly, and method thereof |
| RU2610577C1 (en) * | 2015-12-02 | 2017-02-13 | Федеральное государственное бюджетное учреждение науки Институт металлургии и материаловедения им. А.А. Байкова Российской академии наук (ИМЕТ РАН) | CASTING ALLOY BASED ON INTERMETALLIC COMPOUND Ni3Al, AND ARTICLE OUT OF IT |
-
1999
- 1999-05-24 JP JP14367099A patent/JP4223627B2/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005274124A (en) * | 2004-02-12 | 2005-10-06 | General Electric Co <Ge> | Combustor member for manufacturing combuster assembly, and method thereof |
| RU2610577C1 (en) * | 2015-12-02 | 2017-02-13 | Федеральное государственное бюджетное учреждение науки Институт металлургии и материаловедения им. А.А. Байкова Российской академии наук (ИМЕТ РАН) | CASTING ALLOY BASED ON INTERMETALLIC COMPOUND Ni3Al, AND ARTICLE OUT OF IT |
Also Published As
| Publication number | Publication date |
|---|---|
| JP4223627B2 (en) | 2009-02-12 |
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