重型燃气轮机透平叶片热障涂层的高温氧化寿命预测
High Temperature Oxidation Life Prediction of Thermal Barrier Coating for Heavy Gas Turbine Blade
摘 要
采用大气等离子喷涂技术在DZ411合金基体上制备ZrO2-8Y2O3（质量分数/%）热障涂层，研究了热障涂层的高温氧化性能和氧化后的截面微观形貌，建立了高温氧化寿命预测模型并进行了试验验证。结果表明：在940，1 030℃下氧化时，热障涂层的氧化质量增加Δm和热生长氧化物层厚度均呈抛物线增长规律；热障涂层在1 030℃下的Δm增大速率较940℃下高；建立的热障涂层高温氧化寿命预测模型预测的热生长氧化物层厚度值与试验结果相比在±2倍的分散带内，说明建立的寿命模型及分析方法能较好地预测热障涂层的高温氧化寿命。
热障涂层
高温氧化
寿命预测模型
turbine blade
thermal barrier coating
high temperature oxidation
life prediction model
Abstract
ZrO2-8Y2O3 (mass fraction/%) thermal barrier coating was prepared on DZ411 alloy substrate by atmospheric plasma spraying. The high temperature oxidation properties and the section micromorphology after oxidation of the thermal barrier coating were studied. The high temperature oxidation life prediction model was established and verified by experiments. The results show that the oxidation mass gain Δm and the thermal growth oxide layer thickness of the thermal barrier coating increased in a parabolic pattern during oxidation at 940, 1 030℃. The Δm increase rate of the thermal barrier coating at 1 030℃ was larger than that at 940℃. Compared with the experimental results, the predicted value of the themal growth oxide layer thickness by the established high temperature oxidation life prediction model was within the dispersion band of ±2 times, indicating that the established life model and the analysis method could predict the high temperature oxidation life of the thermal barrier coating well.
中图分类号 TG174.44 DOI 10.11973/jxgccl202311011
所属栏目 物理模拟与数值模拟
基金项目 国家科技重大专项（HT-J2019-I-0003-0004）；华能集团科技项目（HNKJ20-H42）；西安热工研究院有限公司青年基金项目（T1-22-TYK24）
收稿日期 2022/6/7
修改稿日期 2023/7/20
网络出版日期
作者单位点击查看
备注南晴(1987-),女,陕西咸阳人,高级工程师,硕士
引用该论文: NAN Qing,XIAO Junfeng,GAO Sifeng,TANG Wenshu,LI Yongjun,ZHANG Jiong,LIU Quanming. High Temperature Oxidation Life Prediction of Thermal Barrier Coating for Heavy Gas Turbine Blade[J]. Materials for mechancial engineering, 2023, 47(11): 62～66
南晴,肖俊峰,高斯峰,唐文书,李永君,张炯,刘全明. 重型燃气轮机透平叶片热障涂层的高温氧化寿命预测[J]. 机械工程材料, 2023, 47(11): 62～66
共有人对该论文发表了看法，其中：
人认为该论文很差
人认为该论文较差
人认为该论文一般
人认为该论文较好
人认为该论文很好
参考文献
【1】王铁军,范学领.热障涂层强度理论与检测技术[M].西安:西安交通大学出版社,2016. WANG T J,FAN X L.Strength theory and testing technology of thermal barrier coating[M].Xi'an:Xi'an Jiaotong University Press,2016.
【2】PADTURE N P,GELL M,JORDAN E H.Thermal barrier coatings for gas-turbine engine applications[J].Science,2002,296(5566):280-284.
【3】王铁军,范学领,孙永乐,等.重型燃气轮机高温透平叶片热障涂层系统中的应力和裂纹问题研究进展[J].固体力学学报,2016,37(6):477-517. WANG T J,FAN X L,SUN G,et al.The stresses and cracks in thermal barrier coating system:A review[J].Chinese Journal of Solid Mechanics,2016,37(6):477-517.
【4】MILLER R A.Thermal barrier coatings for aircraft engines:History and directions[J].Journal of Thermal Spray Technology,1997,6(1):35-42.
【5】RABIEI A.Failure mechanisms associated with the thermally grown oxide in plasma-sprayed thermal barrier coatings[J].Acta Materialia,2000,48(15):3963-3976.
【6】CHEN W R,WU X,DUDZINSKI D.Influence of thermal cycle frequency on the TGO growth and cracking behaviors of an APS-TBC[J].Journal of Thermal Spray Technology,2012,21(6):1294-1299.
【7】MEIER S M, SHEFFLER K D, NISSLEY D M. Thermal barrier coating life prediction model development, phase 2[J]. International Journal of Fatigue, 1991, 11:205.
【8】魏洪亮,杨晓光,齐红宇.等离子涂层涡轮导向叶片热疲劳寿命预测研究[J].航空动力学报,2008,23(1):1-8. WEI H L,YANG X G,QI H Y.Study on thermal fatigue life prediction for plasma sprayed thermal barrier coatings on the surface of turbine vane[J].Journal of Aerospace Power,2008,23(1):1-8.
【9】STECURA S.Two-layer thermal barrier coatings I:Effects of composition and temperature on oxidation behavior and failure[J].Thin Solid Films,1989,182(1/2):121-140.
【10】MILLER R A.Life modeling of thermal barrier coatings for aircraft gas turbine engines[J].Journal of Engineering for Gas Turbines and Power,1989,111(2):301-305.
【11】DEMASI J T, SHEFFLER K D, ORTIZ M. Thermal barrier coating life prediction model development phase i final report[R]. [S. l.]:NASA Technical Memorandum, 1989.
【2】PADTURE N P,GELL M,JORDAN E H.Thermal barrier coatings for gas-turbine engine applications[J].Science,2002,296(5566):280-284.
【3】王铁军,范学领,孙永乐,等.重型燃气轮机高温透平叶片热障涂层系统中的应力和裂纹问题研究进展[J].固体力学学报,2016,37(6):477-517. WANG T J,FAN X L,SUN G,et al.The stresses and cracks in thermal barrier coating system:A review[J].Chinese Journal of Solid Mechanics,2016,37(6):477-517.
【4】MILLER R A.Thermal barrier coatings for aircraft engines:History and directions[J].Journal of Thermal Spray Technology,1997,6(1):35-42.
【5】RABIEI A.Failure mechanisms associated with the thermally grown oxide in plasma-sprayed thermal barrier coatings[J].Acta Materialia,2000,48(15):3963-3976.
【6】CHEN W R,WU X,DUDZINSKI D.Influence of thermal cycle frequency on the TGO growth and cracking behaviors of an APS-TBC[J].Journal of Thermal Spray Technology,2012,21(6):1294-1299.
【7】MEIER S M, SHEFFLER K D, NISSLEY D M. Thermal barrier coating life prediction model development, phase 2[J]. International Journal of Fatigue, 1991, 11:205.
【8】魏洪亮,杨晓光,齐红宇.等离子涂层涡轮导向叶片热疲劳寿命预测研究[J].航空动力学报,2008,23(1):1-8. WEI H L,YANG X G,QI H Y.Study on thermal fatigue life prediction for plasma sprayed thermal barrier coatings on the surface of turbine vane[J].Journal of Aerospace Power,2008,23(1):1-8.
【9】STECURA S.Two-layer thermal barrier coatings I:Effects of composition and temperature on oxidation behavior and failure[J].Thin Solid Films,1989,182(1/2):121-140.
【10】MILLER R A.Life modeling of thermal barrier coatings for aircraft gas turbine engines[J].Journal of Engineering for Gas Turbines and Power,1989,111(2):301-305.
【11】DEMASI J T, SHEFFLER K D, ORTIZ M. Thermal barrier coating life prediction model development phase i final report[R]. [S. l.]:NASA Technical Memorandum, 1989.
相关信息
