JP6908973B2 - 遮熱コーティング、タービン部材、ガスタービン、ならびに遮熱コーティングの製造方法 - Google Patents
遮熱コーティング、タービン部材、ガスタービン、ならびに遮熱コーティングの製造方法 Download PDFInfo
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- JP6908973B2 JP6908973B2 JP2016114261A JP2016114261A JP6908973B2 JP 6908973 B2 JP6908973 B2 JP 6908973B2 JP 2016114261 A JP2016114261 A JP 2016114261A JP 2016114261 A JP2016114261 A JP 2016114261A JP 6908973 B2 JP6908973 B2 JP 6908973B2
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- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Metallurgy (AREA)
- Ceramic Engineering (AREA)
- Inorganic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- General Engineering & Computer Science (AREA)
- Structural Engineering (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Coating By Spraying Or Casting (AREA)
Description
11 空気取入口
12 圧縮機ケーシング
13 圧縮機静翼
14 圧縮機動翼
2 燃焼器
21 内筒
22 尾筒
23 外筒
24 燃焼器ケーシング
25 空気通路
3 タービン
31 タービンケーシング
32 タービン静翼
33 タービン動翼
34 排気室
34a 排気ディフューザ
4 タービン軸
41,42 軸受部
5 金属結合層
5a 表面
6 高気孔層
6a 気孔
6b 表面
7 緻密層
7a 気孔
7b 表面
8 溶融層
10 ガスタービン
100 耐熱基材
R 軸心
Claims (8)
- 耐熱基材上に形成されたセラミックスからなる気孔を含む層であって、層厚さが0.3mm以上1.0mm以下であり、気孔率が1体積%以上30体積%以下であり、ビッカース硬さが800Hv以上である、イッテルビア安定化ジルコニア材料にて構成された高気孔層と、
前記高気孔層上に形成されてセラミックスからなり、イッテルビア安定化ジルコニア材料またはイットリア安定化ジルコニア材料にて構成され、層厚さが0.05mm以下とされ、気孔率が前記高気孔層未満の0.9体積%以下とされ、ビッカース硬さが800Hv以上である、緻密層と、
前記緻密層上に前記緻密層が溶融された溶融層と、
を備え、
前記溶融層下の前記緻密層の層厚さが0.01mm以上であり、前記溶融層の層厚さが前記緻密層以上で0.04mm以下である、遮熱コーティング。 - 前記高気孔層は、前記緻密層が設けられた表面に単位長さ1mm当たり1本以上10本以下で厚さ方向に縦割れを有する、請求項1に記載の遮熱コーティング。
- 前記緻密層は、平均粒径20μm以下の前記セラミックスの粒度分布を有する、請求項1または2に記載の遮熱コーティング。
- 前記耐熱基材と前記高気孔層との間に形成された金属結合層をさらに備える、請求項1から3のいずれか1つに記載の遮熱コーティング。
- 表面に請求項1から4のいずれか1つに記載の遮熱コーティングを備える、タービン部材。
- 請求項5に記載のタービン部材を備える、ガスタービン。
- 耐熱基材上に大気プラズマ溶射法によってセラミックスからなる気孔を含む層であって、層厚さが0.3mm以上1.0mm以下であり、気孔率が1体積%以上30体積%以下であり、ビッカース硬さが800Hv以上である、イッテルビア安定化ジルコニア材料にて構成された高気孔層を形成し、前記高気孔層上に大気プラズマ溶射法、コールドスプレー法、またはエアロゾルデポジション法によってセラミックスからなり、イッテルビア安定化ジルコニア材料またはイットリア安定化ジルコニア材料にて構成され、気孔率が前記高気孔層未満の0.9体積%以下とされ、ビッカース硬さが800Hv以上である、緻密層を形成し、前記緻密層上に前記緻密層が溶融された溶融層を形成し、前記溶融層下の前記緻密層の層厚さが0.01mm以上であり、前記溶融層の層厚さが前記緻密層以上で0.04mm以下とする、遮熱コーティングの製造方法。
- 前記緻密層を大気プラズマ溶射法によって形成する場合、100mm以下の近距離溶射により前記高気孔層の表面に施す、請求項7に記載の遮熱コーティングの製造方法。
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- 2017-06-06 DE DE112017002907.4T patent/DE112017002907T5/de not_active Withdrawn
- 2017-06-06 US US16/306,635 patent/US10808308B2/en active Active
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US10808308B2 (en) | 2020-10-20 |
CN109312442A (zh) | 2019-02-05 |
DE112017002907T5 (de) | 2019-03-07 |
WO2017213113A1 (ja) | 2017-12-14 |
JP2017218635A (ja) | 2017-12-14 |
US20190119804A1 (en) | 2019-04-25 |
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