在工業領域中，渦輪系統通常在極高溫環境中運轉。為了確保渦輪維持良好性能，常採 用處理葉片的方法以提升其耐久性。其中，常見的手段是在葉片表面應用一層熱障塗層（ Thermal Barrier Coating，簡稱 TBC），同時在葉片內部設計散孔。
本文主要探討在進行薄層TBC邊界元素分析時可能產生的奇異性，並提出一種弱化奇異性的方法。為提高分析效率，我們引入了利用等效對流條件替代基材表面薄層 TBC部分的策略。此外，本文進行了與傳統有限元素分析的比較，以突顯新方法的優越性。為進一步提升效率，我們 提供 了一個自動化渦輪葉片網格生成程式 ，以解決渦輪葉片在設計時產生不規則形狀所帶來的 網格劃分 困難 ，以及有限分析時所需要的單元邊長比設定困難 ，並設計一個使用者介面使操作者在建模過程中更容易進行設定 。

In the industrial sector, turbine systems commonly operate in extremely high-temperature environments. To ensure optimal performance and durability, various methods are employed to treat turbine blades, with a prevalent approach being the application of a Thermal Barrier Coating (TBC) on the blade surface, accompanied by the incorporation of cooling holes within the blade.
This paper primarily explores potential singularities arising during the boundary element analysis of thin-layer TBC and proposes a method to mitigate these singularities. To enhance analysis efficiency, we introduce a strategy employing equivalent convective conditions to replace the surface portion with thin-layer TBC in the base material. Additionally, a comparative analysis with traditional finite element methods is conducted to emphasize the superiority of the new approach. To further boost efficiency, we provide an automated turbine blade mesh generation program, addressing challenges related to irregular shapes during blade design and difficulties in setting element aspect ratios required for finite analysis. A user interface is designed to facilitate easy configuration during the modeling process.

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