JP2023515568A - 高破壊靭性かつ高強度の析出硬化型ステンレス鋼 - Google Patents
高破壊靭性かつ高強度の析出硬化型ステンレス鋼 Download PDFInfo
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- JP2023515568A JP2023515568A JP2022551277A JP2022551277A JP2023515568A JP 2023515568 A JP2023515568 A JP 2023515568A JP 2022551277 A JP2022551277 A JP 2022551277A JP 2022551277 A JP2022551277 A JP 2022551277A JP 2023515568 A JP2023515568 A JP 2023515568A
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Abstract
Description
(発明の属する技術分野)
本発明は、耐食性とともに非常に高い強度と破壊靭性を示すことのできる析出硬化型マルテンサイト系ステンレス鋼合金に関するものである。この合金は、破壊靭性及び強度と耐食性との優れた組み合わせにより、航空宇宙コンポーネント、特には航空機の着陸装置用として、特に適している。この合金は、この合金によって示される高強度と破壊靭性の組み合わせを必要とする他の物品の製造に使用されうる。
航空宇宙産業は、長年にわたり、航空機の着陸装置に使用するための高強度ステンレス鋼合金を探してきた。現在、民間航空機の着陸装置用途に使用されている合金として、300M合金が知られている。300M合金は、約280ksi(1930MPa)の極限引張強さと、10%よりも大きい伸びに代表される良好な延性とを発揮するため、焼入れ・焼戻しされうる。また、300M合金は、50~60ksi√in(55~66MPa√m)のKIc破壊靭性を有している。しかし、300M合金は有効な耐食性を有していない。そのため、着陸装置の構成部品(components)にカドミウムなどの耐食性金属をメッキする必要があった。カドミウムは毒性が強く、発がん性のある物質であるため、300M合金を使用した航空機の着陸装置やその他の露出した構成部品(components)の製造やメンテナンスにおいて、健康や環境に大きなリスクを及ぼしてきた。航空機用着陸装置の用途に求められる耐食性は、一般的な耐食性、耐孔食性、及び耐応力腐食割れ性などである。
本発明による合金は、ニッケルがオーステナイト相の安定化に寄与するため、少なくとも約10.50%のニッケルを含む。安定したオーステナイト相は、焼入れ中の転位緻密マルテンサイトへの変態を促進し、一方、合金中のデルタフェライトの形成を回避する。また、ニッケルは第一強化相であるNi3Tiの形成に関与するため、十分な濃度のニッケルが必要である。さらに、ニッケルは、合金の時効および焼入れ中に、逆変態オーステナイト、ラス間オーステナイトおよび残留オーステナイトを生成促進させることにより、良好な靭性を確保する。また、ニッケルは延性脆性遷移温度(DBTT)を室温より十分に低くして、合金の特徴である良好な衝撃靭性を付与する。好ましくは、合金は、少なくとも約11.0%のニッケルを含み、さらに好ましくは少なくとも約11.4%のニッケルを含む。ニッケルが多すぎると、マルテンサイト変態開始温度(Ms)が室温よりも好ましくないほど低く抑制され、所望の機械的特性を得るための十分な変態が阻害される。従って、この合金は約12.5%以下のニッケルを含む。好ましくは、合金は約12.2%以下のニッケルを含み、さらに好ましくは約12.0%以下のニッケルを含む。
この発明による合金が示す高強度と破壊靭性の新規な組み合わせを実証するため、この発明の合金を具体化した実施例1~13で、真空誘導溶解(VIM)を行った。実施例1~13の組成は、以下の表1に重量パーセントで示されている。
Claims (34)
- 破壊靭性、強度および耐食性の新規な組み合わせを有するマルテンサイト系析出硬化型ステンレス鋼合金であって、重量パーセントで、本質的に、
Ni:約10.5~約12.5、
Co:約1.0~約6.0、
Mo:約1.0~約4.0、
Ti:約1.5~約2.0、
Cr:約8.5~約11.5、
Al:約0.5以下、
Mn:約1.0以下、
Si:約0.75以下、
B:約0.01以下、および
合金の残部:本質的に鉄と、約0.03%以下の炭素、約0.03%以下の窒素、約0.04%以下のリン、および約0.020%以下の硫黄を含む通常の不純物
からなる、マルテンサイト系析出硬化型ステンレス鋼合金。 - 少なくとも約0.15%のアルミニウムを含有する、請求項1に記載の合金。
- 少なくとも約11.0%のニッケルを含む請求項1に記載の合金。
- 少なくとも約1.5%のコバルトを含む、請求項1に記載の合金。
- 約5.5%以下のコバルトを含む、請求項4に記載の合金。
- モリブデンを少なくとも約2.0%含有する、請求項1に記載の合金。
- モリブデンを約3.0%以下含む、請求項6に記載の合金。
- 少なくとも約1.55%のチタンを含む、請求項1に記載の合金。
- チタンを約1.8%以下含む、請求項8に記載の合金。
- 少なくとも約8.75%のクロムを含む、請求項1に記載の合金。
- 約10.5%以下のクロムを含む、請求項10に記載の合金。
- 破壊靭性、強度および耐食性の特性の新規な組み合わせを有するマルテンサイト系析出硬化型ステンレス鋼合金であって、重量パーセントで、本質的に、
Ni:約11.0~約12.2、
Co:約1.5~約5.5、
Mo:約2.0~約3.0、
Ti:約1.55~約1.8、
Cr:約8.75~約10.5、
Al:約0.3以下、
Mn:約0.25以下、
Si:約0.25以下、
B:0.001~0.005、および
合金の残部:本質的に鉄と、約0.02%以下の炭素、約0.015%以下の窒素、約0.015%以下のリン、および約0.01%以下の硫黄を含む通常の不純物
からなる、マルテンサイト系析出硬化型ステンレス鋼合金。 - 少なくとも約0.15%のアルミニウムを含む、請求項12に記載の合金。
- 少なくとも約11.4%のニッケルを含む、請求項12に記載の合金。
- 少なくとも約2.0%のコバルトを含む、請求項12に記載の合金。
- コバルトを約5.0%以下含む、請求項15に記載の合金。
- 少なくとも約2.25%のモリブデンを含む、請求項12に記載の合金。
- 約2.75%以下のモリブデンを含む、請求項17に記載の合金。
- 少なくとも約1.60%のチタンを含む、請求項12に記載の合金。
- 約1.75%以下のチタンを含む、請求項19に記載の合金。
- 少なくとも約9.0%のクロムを含む、請求項12に記載の合金。
- 約10.0%以下のクロムを含む、請求項21に記載の合金。
- 破壊靭性、強度および耐食性の特性の新規な組み合わせを有するマルテンサイト系析出硬化型ステンレス鋼合金であって、重量パーセントで、本質的に、
Ni:約11.4~約12.0、
Co:約2.0~約5.0、
Mo:約2.25~約2.75、
Ti:約1.60~約1.75、
Cr:約9.0~約10.0、
Al:約0.2以下、
Mn:約0.10以下、
Si:約0.10以下、
B:0.0015~0.0035、および
合金の残部:本質的に鉄と、約0.015%以下の炭素、約0.010%以下の窒素、約0.01%以下のリン、および約0.005%以下の硫黄を含む通常の不純物
からなる、マルテンサイト系析出硬化型ステンレス鋼合金。 - 少なくとも約0.15%のアルミニウムを含む、請求項23に記載の合金。
- 請求項1に記載のマルテンサイト系析出硬化型ステンレス鋼合金から作られ、それによって耐食性、高強度および高破壊靭性の新規な組み合わせを示す、金属の部品またはコンポーネントの製造方法であって、前記方法は、以下のステップを含む製造方法。
請求項1に記載のマルテンサイト系析出硬化型ステンレス鋼合金の組成を有するインゴットを、前記合金を溶解し鋳造することにより得ること、
前記インゴットを、約2000°F(1093℃)~約2400°F(1315℃)の温度で、前記インゴットを均質化するのに十分な時間、加熱すること、
均質化されたインゴットを熱間加工して、ニアネットシェイプ部品を得ること、
前記部品を、約1700°F(927℃)~約1900°Fの温度で、あらかじめ選択された時間、加熱することによって、ニアネットシェイプ部品を焼鈍すること、
焼鈍された部品を焼鈍温度から約-100°F(-73℃)未満まで焼入れし、合金マトリックスの完全なマルテンサイト変態を確保すること、および、
焼入れた部品を、引張強さ、破壊靭性および耐食性の組み合わせを得るために選択した時間、900°F(482℃)~約1150°F(621℃)の温度で加熱することにより時効硬化を行うこと。 - 前記圧密ステップ(consolidation step)は粉末冶金圧密プロセスによって実施される、請求項25に記載の方法。
- 前記圧密ステップ(consolidation step)はアディティブマニュファクチャリング(additive manufacturing)プロセスによって実施される、請求項25に記載の方法。
- 請求項1に記載の合金から製造された製造物品であって、前記製造物品は、少なくとも280ksi(1930MPa)の引張強さ、少なくとも60ksi√in(66MPa√m)の平面ひずみ破壊靭性、およびASTM標準試験手順B117に従って試験したときに約1の評価によって特徴付けられる一般耐食性を有する、製造物品。
- 前記物品が航空機用の構造部材である、請求項28に記載の製造物品。
- 前記構造部材は、着陸装置、着陸装置部品、フラップトラック、およびファスナーよりなる群から選択される、請求項29に記載の製造物品。
- 前記物品は医療用及び歯科用のデバイスである、請求項28に記載の製造物品。
- 前記医療用または歯科用のデバイスが、歯科用工具、医療用スクレーパー、およびカッター、ならびに縫合針よりなる群から選択される、請求項31に記載の製造物品。
- 前記物品はスポーツ用具を含む、請求項28に記載の製造物品。
- 前記スポーツ用具はゴルフクラブヘッドを含む、請求項33に記載の製造物品。
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