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

采用大气等离子喷涂技术在DZ411合金基体上制备ZrO_(2)-8Y_(2)O_(3)(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940,1030℃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1030℃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。

ZrO_(2)-8Y_(2)O_(3)(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 gainΔm and the thermal growth oxide layer thickness of the thermal barrier coating increased in a parabolic pattern during oxidation at 940,1030℃.TheΔm increase rate of the thermal barrier coating at 1030℃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.