文献类型：期刊文献

英文题名：Comparative study on failure behavior of promising CMAS-resistant plasma-sprayed thermal barrier coatings in burner rig test with/without CMAS deposition

作者：Fang, Huanjie[1,2,5];Wang, Weize[2];Zhang, Chengcheng[3];Wang, Yongxin[1];Yang, Ting[2];Yang, Zining[2];Liu, Yangguang[2];Ye, Dongdong[4]

机构：[1]Chinese Acad Sci, Ningbo Inst Mat Technol & Engn, Key Lab Marine New Mat & Related Technol, Key Lab Marine Mat & Protect Technol Zhejiang Prov, 1219 Zhongguan West Rd, Ningbo 315201, Peoples R China;[2]East China Univ Sci & Technol, Sch Mech & Power Engn, Key Lab Pressure Syst & Safety, Minist Educ, 130 Meilong Rd, Shanghai 200237, Peoples R China;[3]AECC Commercial Aircraft Engine Co LTD, Shanghai, Peoples R China;[4]Anhui Polytech Univ, Sch Mech Engn, Wuhu 241000, Peoples R China;[5]Chinese Acad Sci, Ningbo Inst Mat Technol & Engn, 1219 Zhongguan West Rd, Ningbo 315201, Peoples R China

年份：2023

卷号：49

期号：8

起止页码：12390

外文期刊名：CERAMICS INTERNATIONAL

收录：;EI(收录号：20225213307551);WOS:【SCI-EXPANDED(收录号:WOS:000961977200001)】；

基金：This research is sponsored by the National Natural Science Founda- tion of China (Grant No. 52175136; No. 52130511) , Shanghai Aero- space Science and Technology Innovation Fund (SAST2019056) , Shanghai Joint Innovation Program in the Field of Commercial Aviation Engines, the National High Technology Research and Development Program of China (2021YFB3702200) , Key Research and Development Projects in Anhui Province (2022a05020004) .

语种：英文

外文关键词：Thermal barrier coatings; CMAS; Failure analysis; Cracking behavior

摘要：Along with continuous progress in inlet temperature of turbine engine, calcium-magnesium-aluminum-silicate (CMAS) deposition has become one of serious challenges for traditional yttria partially stabilized zirconia thermal barrier coatings at elevated temperature. Although lots of materials with superior CMAS resistance have been proposed, there is few comparative research on performance of corresponding coatings reported especially when subjected to thermal cycling and CMAS simultaneously. To this end, some coatings were prepared in present study, and thereafter failure behavior in condition of thermal cycling and thermal cycling-CMAS was systemically investigated and compared. Experimental results showed a varied lifetime and cracking behavior in thermal cycling test and thermal cycling-CMAS test, indicating that CMAS infiltration affected failure behavior of coatings. Besides, it was numerically found that CMAS penetration would lead to a promotion of thermal stress, which increased the tendency for cracking during thermal cycling. And the phenomenon that channel crack was the precondition of delamination crack was revealed.