JP5166797B2 - 拡散制御変性された白金族ボンドコート - Google Patents
拡散制御変性された白金族ボンドコート Download PDFInfo
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- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/14—Metallic material, boron or silicon
- C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
- C23C14/165—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon by cathodic sputtering
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- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
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- Y10T428/12618—Plural oxides
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- Y10T428/12771—Transition metal-base component
- Y10T428/12861—Group VIII or IB metal-base component
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- Y10T428/12972—Containing 0.01-1.7% carbon [i.e., steel]
- Y10T428/12979—Containing more than 10% nonferrous elements [e.g., high alloy, stainless]
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Description
スパッタ堆積法を用いてRene N5のタービンブレードに変性PGM皮膜を形成した。変性PGM皮膜の組成は、10原子%のRh、40原子%のPt、25原子%のNi、20原子%のAl及び5原子%のCrであった。低レベルのCr、Ni及びAlは白金リッチな表面での酸化物の形成を抑制する。堆積後、被覆タービンブレードを真空中約1800oFで約1時間熱処理した。
米国特許第6933052号(本発明の先行技術として援用する)に示されているような拡散障壁として、酸化物、窒化物、炭化物皮膜をRene N6タービンブレードに設けた。この拡散障壁を約2μmの厚さに形成した。その後、イオンプラズマ堆積により拡散障壁上に変性PGM皮膜を約50μmの厚さに形成した。変性PGM皮膜の組成は50原子%のRh、20原子%のPt、15原子%のNi、10原子%のAl及び5原子%のCrであった。堆積後、被覆タービンブレードを真空中約2000oFで約2時間熱処理した。
イオンプラズマ堆積によりRene N5試料に変性PGM皮膜を設けた。この皮膜を真空中1800oFで約1時間熱処理した。熱処理後の皮膜の組成をマイクロプローブにより測定したところ、原子%で表して、約15.85%のNi、約2.27%のCr、約5.76%のAl、約27.21%のPt及び約48.36%のRhであった。他の元素は存在するかもしれないが、測定器の検出限界以下の量である。この組成物が含有するNi及びAlの量はβ相NiAl金属間化合物を形成するには不十分な量であった。その後、温度を2000oFに上げて約2時間熱曝露を行った。微細組織を図8に示す。皮膜82と基材84、即ちRene N5との間にボンドライン80が認められるが、剥離はなく、カーケンドールボイド形成もほとんど観察できない。その後、試料を2200oFの温度に約24時間熱曝露した。図9に示した微細組織は2相の微細組織である。皮膜90中に、特定すると皮膜表面及び基材94との界面に生成しているブロック状部分92は、ロジウムアルミナイド(RhAl)であり、変性PGM系皮膜のfccマトリックス中に散在している。
Rene N5試料に約26.96原子%のAl、約19.11原子%のNi、約7.22原子%のCr、約25.73原子%のRh及び残部のPtをスパッタ堆積した。この被覆試料を約2000oFの温度で約2時間真空熱処理し、その後、約2150oFでサイクル酸化試験を施した。サイクル酸化試験は1時間当たり20サイクルを含む。サイクル酸化試験での試験は著しい酸化が起こるのを確認するまで続ける。これは目視で確認できる。実施例3に記載した、図9と同様な2相構造が形成された。本発明に従って被覆した試料の平均寿命は2000時間を上回ったが、同様に処理したPtAl被覆基準試料の平均寿命は約460時間であった。
4 β相NiAl
12 Pt−Alの2元相図
14 γ相
22 Pt−Niの2元相図
50 剥離
60 カーケンドールボイドライン
80 ボンドライン
82 変性PGM皮膜
84 基材
90 変性PGM皮膜
92 RhAl
94 基材
Claims (10)
- 超合金基材と、
変性白金族金属皮膜であって、該変性白金族金属皮膜が、原子%で表して、5〜30原子%のAlと、10〜45原子%のNiと、20原子%以下のCr、Co、Ta、W、Re、Ru、Mo、Nb、Ti及びこれらの組合せからなる群から選択される元素と、2原子%以下のZr、Hf、Y、希土類元素及びこれらの組合せからなる群から選択される元素と、残部の白金族金属とを含有し、この残部が40原子%以上85原子%以下を構成し、白金族金属がPt、Rh、Pd及びIrからなる群から選択される1種以上の元素からなり、NiとCr、Co、Ta、W、Re、Ru、Mo、Nb、Ti及びこれらの組合せからなる群から選択される元素との合計量が皮膜の50原子%以下であり、前記皮膜が実質的に面心立方固溶体構造として形成された変性白金族金属皮膜と、
超合金基材と変性白金族皮膜との間に位置する、酸化物系皮膜の拡散障壁層と
を含む物品。 - 前記超合金基材の母材がNi、Fe、Co及びこれらの組合せからなる群から選択される、請求項1記載の物品。
- 前記超合金基材がNi基超合金基材である、請求項1記載の物品。
- 前記Zr、Hf、Y、希土類元素及びこれらの組合せからなる群から選択される元素が、セリウム(Ce)、ランタン(La)を含有する、請求項1乃至請求項3のいずれか1項記載の物品。
- さらに、遮熱コーティングを含み、変性白金族金属皮膜が前記超合金基材と遮熱コーティングの間に介在する、請求項1乃至請求項4のいずれか1項記載の物品。
- 前記超合金基材が、重量%で、7.5%のCo、7%のCr、6.2%のAl、6.5%のTa、5%のW、3%のRe、1.5%のMo、0.15%のHf、0.05%のC、0.004%のB、残部のNi及び不可避的不純物からなる公称組成を有する、請求項1記載の物品。
- 前記超合金基材が、重量%で、12.5%のCo、4.5%のCr、5.7%のW、6.1%のAl、7%のTa、5.6%のW、6.2%のRe、0.95%のMo、0.15%のHf、0.05%のC、0.004%のB、残部の本質的にNi及び不可避的不純物からなる公称組成を有し、さらに優れた耐環境性及び耐応力破断性を特徴とする、請求項1記載の物品。
- 前記白金族金属皮膜が5〜60μmの厚さに形成されている、請求項1乃至請求項7のいずれか1項記載の物品。
- 当該物品がガスタービンエンジンの部品である、請求項1乃至請求項8のいずれか1項記載の物品。
- 当該物品がタービンブレードである、請求項9記載の物品。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/553,515 US7527877B2 (en) | 2006-10-27 | 2006-10-27 | Platinum group bond coat modified for diffusion control |
US11/553,515 | 2006-10-27 |
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JP2008156744A JP2008156744A (ja) | 2008-07-10 |
JP2008156744A5 JP2008156744A5 (ja) | 2012-10-18 |
JP5166797B2 true JP5166797B2 (ja) | 2013-03-21 |
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JP2007217014A Expired - Fee Related JP5166797B2 (ja) | 2006-10-27 | 2007-08-23 | 拡散制御変性された白金族ボンドコート |
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US (1) | US7527877B2 (ja) |
EP (1) | EP1916319A3 (ja) |
JP (1) | JP5166797B2 (ja) |
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DE102007008278A1 (de) * | 2007-02-20 | 2008-08-21 | Mtu Aero Engines Gmbh | Beschichtung für Gasturbinenbauteile sowie Verfahren und Vorrichtung zur Bereitstellung einer Beschichtung |
AU2008275181B2 (en) | 2007-07-10 | 2014-06-26 | The Regents Of The University Of California | Materials and methods for delivering compositions to selected tissues |
ES2704138T3 (es) * | 2009-05-20 | 2019-03-14 | Howmet Corp | Recubrimiento de Pt-Al-Hf/Zr y método |
JP5660428B2 (ja) | 2010-04-20 | 2015-01-28 | 独立行政法人物質・材料研究機構 | 耐熱コーティング材 |
EP2631324A4 (en) | 2010-10-19 | 2014-04-16 | Nat Inst For Materials Science | NICKEL-BASED SUPER-LUBRICATING ELEMENT COMPRISING A HAZARD-RESISTANT LAYER COATING THEREIN |
JP5226846B2 (ja) * | 2011-11-04 | 2013-07-03 | 田中貴金属工業株式会社 | 高耐熱性、高強度Rh基合金及びその製造方法 |
US9337624B2 (en) | 2012-10-12 | 2016-05-10 | Federal-Mogul Ignition Company | Electrode material for a spark plug and method of making the same |
JP6054731B2 (ja) * | 2012-12-12 | 2016-12-27 | 日東紡績株式会社 | 合金製耐熱構造部材 |
GB2511768A (en) * | 2013-03-12 | 2014-09-17 | Rolls Royce Plc | Erosion Resistant Coating |
JP6226231B2 (ja) | 2013-09-18 | 2017-11-08 | 株式会社Ihi | 熱遮蔽コーティングしたNi合金部品及びその製造方法 |
US9790587B2 (en) | 2014-10-28 | 2017-10-17 | General Electric Company | Article and method of making thereof |
FR3058164B1 (fr) * | 2016-10-27 | 2020-02-07 | Safran | Piece comprenant un substrat en superalliage monocristallin a base de nickel et son procede de fabrication. |
US10454114B2 (en) | 2016-12-22 | 2019-10-22 | The Research Foundation For The State University Of New York | Method of producing stable, active and mass-producible Pt3Ni catalysts through preferential co etching |
JP7082799B2 (ja) * | 2018-03-30 | 2022-06-09 | 国立研究開発法人物質・材料研究機構 | 合金構造体 |
WO2021052704A1 (en) * | 2019-09-19 | 2021-03-25 | Basf Se | High temperature protective coatings, especially for use in petrochemical processes |
FR3101642B1 (fr) * | 2019-10-03 | 2021-12-17 | Safran Ceram | Etanchéité d’une turbine |
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US6333121B1 (en) * | 1992-10-13 | 2001-12-25 | General Electric Company | Low-sulfur article having a platinum-aluminide protective layer and its preparation |
EP0718420B1 (en) | 1994-12-24 | 1999-04-21 | Rolls Royce Plc | A method of applying a thermal barrier coating to a superalloy article and a thermal barrier coating |
GB9426257D0 (en) * | 1994-12-24 | 1995-03-01 | Rolls Royce Plc | Thermal barrier coating for a superalloy article and method of application |
US5716720A (en) * | 1995-03-21 | 1998-02-10 | Howmet Corporation | Thermal barrier coating system with intermediate phase bondcoat |
GB9612811D0 (en) * | 1996-06-19 | 1996-08-21 | Rolls Royce Plc | A thermal barrier coating for a superalloy article and a method of application thereof |
JP2903105B2 (ja) * | 1996-11-08 | 1999-06-07 | 株式会社日立製作所 | 耐酸化被覆層の製造方法 |
US6458473B1 (en) * | 1997-01-21 | 2002-10-01 | General Electric Company | Diffusion aluminide bond coat for a thermal barrier coating system and method therefor |
FR2768750B1 (fr) | 1997-09-25 | 1999-11-05 | Snecma | Procede pour ameliorer la resistance a l'oxydation et a la corrosion d'une piece en superalliage et piece en superalliage obtenue par ce procede |
US6168874B1 (en) * | 1998-02-02 | 2001-01-02 | General Electric Company | Diffusion aluminide bond coat for a thermal barrier coating system and method therefor |
FR2814473B1 (fr) * | 2000-09-25 | 2003-06-27 | Snecma Moteurs | Procede de realisation d'un revetement de protection formant barriere thermique avec sous-couche de liaison sur un substrat en superalliage et piece obtenue |
US6461107B1 (en) * | 2001-03-27 | 2002-10-08 | General Electric Company | Turbine blade tip having thermal barrier coating-formed micro cooling channels |
US6881452B2 (en) * | 2001-07-06 | 2005-04-19 | General Electric Company | Method for improving the TBC life of a single phase platinum aluminide bond coat by preoxidation heat treatment |
US6933062B2 (en) * | 2001-08-16 | 2005-08-23 | General Electric Company | Article having an improved platinum-aluminum-hafnium protective coating |
US6582534B2 (en) * | 2001-10-24 | 2003-06-24 | General Electric Company | High-temperature alloy and articles made therefrom |
US6921586B2 (en) * | 2002-02-05 | 2005-07-26 | General Electric Company | Ni-Base superalloy having a coating system containing a diffusion barrier layer |
US7157151B2 (en) * | 2002-09-11 | 2007-01-02 | Rolls-Royce Corporation | Corrosion-resistant layered coatings |
US6974636B2 (en) * | 2003-09-22 | 2005-12-13 | General Electric Company | Protective coating for turbine engine component |
US6933052B2 (en) * | 2003-10-08 | 2005-08-23 | General Electric Company | Diffusion barrier and protective coating for turbine engine component and method for forming |
FR2861423B1 (fr) * | 2003-10-28 | 2008-05-30 | Snecma Moteurs | Piece de turbine a gaz muni d'un revetement de protection et procede de realisation d'un revetement de protection sur un substrat metallique en superalliage |
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EP1916319A3 (en) | 2010-01-06 |
US20080102306A1 (en) | 2008-05-01 |
US7527877B2 (en) | 2009-05-05 |
EP1916319A2 (en) | 2008-04-30 |
JP2008156744A (ja) | 2008-07-10 |
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