等离子涂层热疲劳失效模式及失效机理研究

魏洪亮; 杨晓光; 齐红宇; 韩增祥

等离子涂层热疲劳失效模式及失效机理研究

1.
北京航空航天大学能源与动力工程学院, 北京 100083
2.
北京航空材料研究院, 北京 100095

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出版历程
- 收稿日期: 2007-01-17
- 修回日期: 2007-03-21
- 刊出日期: 2008-02-28

Study of failure mode and failure mechanisms on thermal fatigue of plasma sprayed thermal barrier coatings

1.
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
Beijing Institute of Aeronautical Materials, Beijing 100095, China

摘要

摘要: 开展了等离子涂层构件热疲劳实验研究,对失效过程及失效模式进行考察,分析了对失效起主导作用的应力分量.针对陶瓷层材料引入粘塑性本构模型,对涂层的热疲劳进行数值模拟研究.分析表明,氧化层厚度为2 μm时,陶瓷层波峰位置容易萌生Ⅰ型横向裂纹,界面中部偏上位置容易萌生Ⅱ型横向裂纹;氧化层厚度为8 μm时,陶瓷层内部法向应力主导横向裂纹的扩展;不同厚度的氧化层内部将形成较高的应变能密度.给出了等离子涂层内部裂纹形成过程及机理.
- 航空、航天推进系统 /
- 热障涂层 /
- 热疲劳 /
- 失效模式 /
- 失效机理
Abstract: Thermal fatigue test was conducted to study the failure process and failure mode of the plasma sprayed thermal barrier coating structures.The controlling factors for failure were also analyzed.Aviscoplastic constitutive model was introduced for the ceramic coat.Moreover,the thermal fatigue behavior of the coating layer was studied numerically.The analysis indicates that: mode Ⅰ crack is easily initiated at the peak position,and mode Ⅱ crack at above middle position of interfaces when TGO(thermaly growth oxides) thickness is 2 μm;the extension of transverse crack is dominated by normal stress when TGOthickness is 8 μm;high strain energy density is formed within TGOof different thickness.The process and mechanisms of crack coalescence within PS-TBC(plasma sprayed thermal grown oxides) were presented.
- aerospace propulsion system /
- thermal barrier coatings /
- thermal fatigue /
- failure mode /
- failure mechanisms

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参考文献(12)

[1]	Rabiei A,Evans A G.Failure mechanisms associated with the thermally grown oxide in plasma-sprayed thermal barrier coatings[J].Acta Mater.,2000,48:3963-3976.
[2]	Busso E P,Lin J,Sakurai S.et al.A mechanistic study of oxidation-induced degradation in a plasma-sprayed thermal barrier coating system.Part Ⅱ:Life prediction model[J].Acta materialia,2001,49:1529-1536.
[3]	Evans A G,Mumm D R,Hutchinson J W,et al.Mechanisms controlling the durability of thermal barrier coatings[J].Progress in Materials Science,2001,46:505-553.
[4]	Evans A G,He M Y,Hutchinson J W.Effect of interface undulations on the thermal fatigue of thin films and scales on metal substrates[J].Acta Mater.,1997,45:3543-3554.
[5]	Karlsson A M,Hutchinson J W,Evans A G.A fundamental model of cyclic instabilities in thermal barrier systems[J].Journal of the Mechanics and Physics of Solids,2002,50:1565-1589.
[6]	Karlsson A M,Hutchinson J W,Evans A G.The displacement of the thermally grown oxide in thermal barrier systems upon temperature cycling[J].Materials Science and Engineering,2003,A351:244-257.
[7]	Freborg A M,Ferguson B L,Brindley W J,et al.Modeling oxidation induced stresses in thermal barrier coatings[J].Mater.Sci.Eng.A,1998,A245(3):182-1190.
[8]	Aktaa J,Sfar K,Munz D.Assessment of TBC systems failure mechanisms using a fracture mechanics approach[J].Acta Materialia,2005,53:4399-4413.
[9]	Janosik L A,Duffy S F.A viscoplastic constitutive theory for monolithic ceramics-I[J].ASME J.Eng.Gas Turbines Power,1998,120:155-161.
[10]	Xie Wangang,Walker K P,Jordan E H,et al.Implementation of a viscoplastic model for a plasma sprayed ceramic thermal barrier coating[J].J.Eng.Mater.Technol.,2003,125:200-207.
[11]	耿瑞.热障涂层强度分析及寿命预测研究[D].北京:北京航空航天大学,2001.GENG Rui.Strength analysis and life prediction study on thermal barrier coatings[D].Beijing:Beijing University of Aeronautics and Astronautics,2001.(in Chinese).
[12]	Berndt C C,Miller R A.Failure analysis of plasma-sprayed thermal barrier coatings[R].NASA Technical Memorandum No.83777,1984.