Thermal barrier coatings (TBCs) applied to high-temperature components of gas turbines consist of a ceramic top coat, a metallic bond coat, and thermally grown oxide (TGO) generated between the top coat and bond coat. Because TBCs are subjected to repeated thermal stress at the coating interface under thermal fatigue conditions and eventually breakage, it is crucial to evaluate the thermal fatigue durability of TBCs according to the stress. In this study, coin-type TBC specimens were prepared by depositing commercial coating powders on Ni-based super alloys via the air plasma spray method, and the thermal fatigue life of the TBCs was experimentally evaluated. According to the test results and references, a finite-element analysis was conducted. The maximum stress of the TGO interface was evaluated according to the thickness and equivalent elastic modulus, and simulating the microstructure including the pores of the top coat. Using these relationships, a thermal fatigue life prediction equation considering the coating thickness (t), equivalent elastic modulus (E), and operating temperature (T) was derived, and subsequently verified.

应用于燃气轮机高温部件的热障涂层（TBC）由陶瓷面涂层，金属粘结层以及在该顶层和粘结层之间产生的热生长氧化物（TGO）组成。由于TBC在热疲劳条件下会在涂层界面处反复受到热应力，并最终断裂，因此根据应力评估TBC的热疲劳耐久性至关重要。在这项研究中，硬币型TBC样品是通过空气等离子喷涂法将商业涂料粉末沉积在Ni基超级合金上制备的，并通过实验评估了TBC的热疲劳寿命。根据测试结果和参考资料，进行了有限元分析。根据厚度和等效弹性模量，并模拟包括面涂层孔的微观结构，评估TGO界面的最大应力。利用这些关系，推导了考虑涂层厚度（t），等效弹性模量（E）和工作温度（T）的热疲劳寿命预测方程，并随后进行了验证。