电子束物理气相沉积La_2Ce_2O_7热障涂层的高温燃气热腐蚀行为研究
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摘要
采用电子束物理气相沉积(EB-PVD)方法在镍基高温合金表面制备了La2Ce2O7(LC)/8YSZ双陶瓷层热障涂层,研究了LC涂层在高温燃气热腐蚀条件下的高温稳定性以及涂层的抗热腐蚀性能。结果表明,LC陶瓷涂层在海水和航空煤油的热腐蚀环境下经过950℃曝露100 h后,涂层没有发生分解和相变,显示了良好的抗燃气热腐蚀性能;同时,金属粘结层表面形成了一层连续致密的氧化层。热障涂层经过循环腐蚀100 h后,仍然没有发生剥落失效。
Double-ceramic-layered(DCL) TBCs of La_2Ce_2O_7(LC)/8 YSZ were prepared by electron beam physical vapor deposition(EB-PVD) on Ni-base superalloy. The high temperature stability and corrosion-resistant property of TBCs was investigated in high temperature gas corrosion environment. The results show that no decomposition and phase transformation arises in the TBCs after 100 h exposure at950 ℃ in the flowing air with aviation kerosene and artificial seawater. The TBCs display good high temperature gas corrosion-resistant property. A continuous and dense oxide scale forms on the bonding coat.No spallation of TBCs occurred after 100 h thermal cycling in the corrosion environment.
Double-ceramic-layered(DCL) TBCs of La_2Ce_2O_7(LC)/8 YSZ were prepared by electron beam physical vapor deposition(EB-PVD) on Ni-base superalloy. The high temperature stability and corrosion-resistant property of TBCs was investigated in high temperature gas corrosion environment. The results show that no decomposition and phase transformation arises in the TBCs after 100 h exposure at950 ℃ in the flowing air with aviation kerosene and artificial seawater. The TBCs display good high temperature gas corrosion-resistant property. A continuous and dense oxide scale forms on the bonding coat.No spallation of TBCs occurred after 100 h thermal cycling in the corrosion environment.
引文
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[3]Guo H B,Gong S K,Xu H B.Progress in thermal barrier coatings for advanced aeroengines[J].Mater.China,2009,28(Z2):18(郭洪波,宫声凯,徐惠彬.先进航空发动机热障涂层技术研究进展[J].中国材料进展,2009,28(Z2):18)
[4]Wei S B,Lu F,He L M,et al.Progress in processing techniques and ceramic materials of thermal barrier coatings[J].Therm.Spray Technol.,2013,5(1):31(魏绍斌,陆峰,何利民等.热障涂层制备技术及陶瓷层材料的研究进展[J].热喷涂技术,2013,5(1):31)
[5]Cao X Q,Vassen R,Tietz F,et al.New double-ceramic-layer thermal barrier coatings based on zirconia-rare earth composite oxides[J].J.Eur.Ceram.Soc.,2006,26:247
[6]Zhang T Y,Wu C,Xiong Z,et al.Research progress in materials and preparation techniques of thermal barrier coatings[J].Laser Optoelect.Prog.,2014,51(3):27(张天佑,吴超,熊征等.热障涂层材料及其制备技术的研究进展[J].激光与光电子学进展,2014,51(3):27)
[7]Ma W,Gong S K,Li H F,et al.Novel thermal barrier coatings based on La2Ce2O7/8YSZ double-ceramic-layer systems deposited by electron beam physical vapor deposition[J].Surf.Coat.Technol.,2008,202:2704
[8]Salehnasab B,Poursaeidi E,Mortazavi S A,et al.Hot corrosion failure in the first stage nozzle of a gas turbine engine[J].Eng.Fail.Anal.,2016,60:316
[9]Guo H B,Li D Q,Peng H,et al.High-temperature oxidation and hot-corrosion behaviour of EB-PVDβ-Ni Al Dy coatings[J].Corros.Sci.,2011,53:1050
[10]He J,Luan Y,Guo H B,et al.The role of Cr and Si in affecting high-temperature oxidation behaviour of minor Dy doped Ni Alalloys[J].Corros.Sci.,2013,77:322
[11]He J,Guo H B,Zhang Y L,et al.Improved hot-corrosion resistance of Si/Cr co-doped Ni Al Dy alloy in simulative sea-based engine environment[J].Corros.Sci.,2014,85:232
[12]Bai Z M,Zhou L,Liang T Q,et al.Hot-corrosion behavior of thermal barrier coated DZ125 superalloy exposed to atomized seawater and kerosene[J].Int.J.Mod.Phys.,2010,24B:3155
[13]Rahnavard M,Ostad Ahmad Ghorabi M J,Rafiee H.Comparison of hot corrosion behaviour of FGM and usual TBCs[J].Surf.Eng.,2016,doi:10.1080/02670844.2016.1219106
[14]Bai Z M.Corrosion behavior and failure mechanism of thermal barrier coatings exposed to high temperature corrosive environment[D].Beijing:Beihang University,2012(白致铭.热障涂层的高温热腐蚀行为及失效机理研究[D].北京:北京航空航天大学,2012)
[15]He Q,Qu Y,Wang R J,et al.Gas hot-corrosion resistance of nanostructure and segmentation thermal barrier coatings on DZ40M superalloy[J].J.Mater.Eng.,2014,(5):66(何箐,屈轶,汪瑞军等.DZ40M合金表面纳米和垂直裂纹结构热障涂层的抗燃气热腐蚀性能[J].材料工程,2014,(5):66)