JP2019532174A - タービンエンジン部品の金属基板上の熱バリアシステムを生成するための方法 - Google Patents
タービンエンジン部品の金属基板上の熱バリアシステムを生成するための方法 Download PDFInfo
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Abstract
Description
酸化の増大に起因する、ボンディング層の粗さの増大が、熱バリアの分離に繋がることと、
CMAS酸化物の、セラミックの柱間の空間への浸透により、そのセラミックが弱くなることと、
セラミック材料の粘着性が低いことに起因して、外部の物体の衝撃に対する耐性が低いことと、が生成される。
−球状のマイクロビーズ(ショットブラストは、対象の表面構造を変更し、また、圧縮応力を導入するための、ショットブラストマシンを使用して、マイクロビーズを、対象の表面上に射出することから成る技術である)であること、
−WC、ZrO2、SiO2、Al2O3、鋼の、マイクロビーズの材料であること、
−ビーズのサイズが、ノズルでのショットブラストに関しては、300μmから1mmの間であり、超音波でのショットブラストに関しては0.8mmから3mmの間であり、振動ショットブラストに関しては1mmから6mmの間であること、
−ノズルでのショットブラストの入射角が、60度から90度の間であること、
が単独で、または、好ましくは組み合わせて使用され得る。
金属基板上にボンディング層を形成することであって、このボンディング層が、圧縮され得る、ボンディング層を形成することと、
ボンディング層上に、1つまたは複数のセラミック層を形成することであって、前記セラミック層または複数の層の少なくとも1つが、圧縮され得る、1つまたは複数のセラミック層を形成することと、を連続して含むことができる。
1つまたは複数のレアアース酸化物でドープされたジルコニア、
たとえば、Gd2Zr2O7、Sm2Zr2O7、またはYb4Zr3O12などの、レアアースのジルコン酸塩、
たとえば、Ba(Mg1/3Ta2/3)O3、La(Al1/4Mg1/2Ta1/4)O3などの灰チタン石、
たとえば、REが周期表のLaからGdまでの範囲の元素を示し、Mが、Mg、MnからZn、Cr、およびSmから選択される元素を示す、REMAl11O19の一般式のヘキサアルミン酸塩、
ランタニドオルトリン酸塩である。
CMAS酸化物の浸透の制限、
熱バリアシステムの耐用年数の増大、
表面硬さなどの機械的特性の向上、
腐食に対する耐性の増大、および、
熱バリアシステムのテナシティ(tenacity)の増大の効果がある。
CMAS酸化物の浸透の制限、
熱バリアシステムの耐用年数の増大、および、
熱バリアシステムのテナシティの増大をもたらす。
熱サイクル中のこの層の変形動力学における低下の利益を伴う、ボンディング層2の部分的または全体的な高密度化、および、その粗さの制御、
層2の硬度の増大の効果を有する、残留応力の発生が可能になる。
Claims (15)
- 高圧タービンブレードなどのタービンエンジン部品の金属基板(1)上に熱バリアシステムを生成するための方法にして、熱バリアシステムが、少なくとも1つの柱状のセラミック層(3;31、...、3i、...、3n)を備える、方法であって、本方法が、前記少なくとも1つの柱状のセラミック層(3;31、...、3i、...、3n)の少なくとも1つを圧縮するステップを含んでいることを特徴とする、方法。
- 圧縮により、圧縮された柱状のセラミック層または複数の層(3;31、...、3i、...、3n)の柱間の空間を低減することが可能であることを特徴とする、請求項1に記載の方法。
- 圧縮が、ショットブラスト、ショットピーニング、または、レーザショックピーニングによる圧縮であることを特徴とする、請求項1または請求項2に記載の方法。
- 前記柱状のセラミック層(3;31、...、3i、...、3n)の少なくとも1つの圧縮が、ショットブラストであることと、前記ショットブラストのアルメン強度が、F10AからF42Aの間であることとを特徴とする、請求項3に記載の方法。
- 前記基板(1)が、ニッケルまたはコバルトベースの超合金の基板であることを特徴とする、請求項1から請求項4のいずれか一項に記載の方法。
- 前記少なくとも1つの柱状のセラミック層(3;31、...、3i、...、3n)が、イットリア化されたジルコニアの層であることを特徴とする、請求項1から請求項5のいずれか一項に記載の方法。
- 前記少なくとも1つの柱状のセラミック層(3;31、...、3i、...、3n)が、物理蒸着法によって得られることを特徴とする、請求項1から請求項6のいずれか一項に記載の方法。
- 蒸着法が、電子ビーム物理蒸着法(EBPVD)であることを特徴とする、請求項7に記載の方法。
- 熱バリアシステムが、いくつかの柱状のセラミック層(31、...、3i、...、3n)を備えていることと、本方法が、柱状のセラミック層(31、...、3i、...、3n)の1つまたはすべてを圧縮することを含んでいることとを特徴とする、請求項1から請求項8のいずれか一項に記載の方法。
- 本方法が、上方セラミック層(3n)の圧縮、または、前記上層(3n)の真下に位置するセラミック層(3(n−1))の圧縮を含んでいることを特徴とする、請求項9に記載の方法。
- 熱バリアシステムが、前記金属基板(1)と、前記少なくとも1つの柱状のセラミック層(3;31、...、3i、...、3n)との間に配置されたボンディング層(2)をさらに備えていることを特徴とする、請求項1から請求項10のいずれか一項に記載の方法。
- 前記ボンディング層(2)が、表面上にアルミナ層を備えた、アルミニウムを形成する材料の層であることを特徴とする、請求項11に記載の方法。
- 本方法が、前記ボンディング層(2)を圧縮するステップを含んでいることを特徴とする、請求項11または請求項12に記載の方法。
- 前記ボンディング層(2)の圧縮が、ショットブラストであることと、前記ショットブラストのアルメン強度が、F9NからF30Aの間であることとを特徴とする、請求項13に記載の方法。
- 請求項1から請求項13のいずれか一項に記載の方法によって生成された熱バリアシステムを備えていることを特徴とする、高圧タービンブレードなどのタービンエンジン部品。
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FR1657941 | 2016-08-25 | ||
FR1657941A FR3055351B1 (fr) | 2016-08-25 | 2016-08-25 | Procede de realisation d'un systeme barriere thermique sur un substrat metallique d'une piece de turbomachine |
PCT/FR2017/052284 WO2018037196A1 (fr) | 2016-08-25 | 2017-08-25 | Procede de realisation d'un systeme barriere thermique sur un substrat metallique d'une piece de turbomachine |
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JP2021000825A (ja) * | 2019-06-24 | 2021-01-07 | ▲華▼中科技大学Huazhong University Of Science And Technology | セラミック及びその複合材料に適した積層造形法及び装置 |
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DE102007043791A1 (de) * | 2007-09-13 | 2009-04-02 | Mtu Aero Engines Gmbh | Verfahren zur Herstellung einer Wärmedämmschicht und Wärmedämmschicht |
FR2928664B1 (fr) | 2008-03-14 | 2010-04-16 | Snecma | Procede pour former un revetement protecteur contenant de l'aluminium et du zirconium sur une piece metallique. |
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CN105369202A (zh) * | 2015-11-20 | 2016-03-02 | 沈阳黎明航空发动机(集团)有限责任公司 | 一种重型燃机涡轮叶片热障涂层的制备方法 |
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US5350599A (en) * | 1992-10-27 | 1994-09-27 | General Electric Company | Erosion-resistant thermal barrier coating |
JP2000192256A (ja) * | 1998-12-15 | 2000-07-11 | United Technol Corp <Utc> | 熱防御膜の塗布方法 |
JP2010043351A (ja) * | 2008-07-29 | 2010-02-25 | General Electric Co <Ge> | 遮熱コーティング及びその製造法 |
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FR3055351A1 (fr) | 2018-03-02 |
EP3504358A1 (fr) | 2019-07-03 |
WO2018037196A1 (fr) | 2018-03-01 |
RU2019106347A (ru) | 2020-09-25 |
FR3055351B1 (fr) | 2019-11-08 |
US20190211438A1 (en) | 2019-07-11 |
CN109689934A (zh) | 2019-04-26 |
CA3034760A1 (fr) | 2018-03-01 |
RU2019106347A3 (ja) | 2020-09-25 |
RU2742862C2 (ru) | 2021-02-11 |
US11060178B2 (en) | 2021-07-13 |
JP7030106B2 (ja) | 2022-03-04 |
BR112019003445A2 (pt) | 2019-05-21 |
EP3504358B1 (fr) | 2023-09-27 |
CN109689934B (zh) | 2021-09-21 |
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