CAJ | 학술논문

燃机透平空心冷却叶片的结构异常复杂，叶身表面数量众多，尺寸小巧的气膜孔给应力，计算带来巨大困难。要准确的计算叶身应力，其计算规模将非常巨大，需要消耗大量的计算机资源才能完成。子模型技术通过对几何模型的分解，在保证总体计算规模不太大的同时又可以保证重点部位的计算精度。本研究用Abaqus商业软件的子模型方法分析气膜孔周围应力分布，比较了传统计算方法和子模型方法的计算精度、时间和资源消耗量。
연궤투평공심냉각협편적결구이상복잡，협신표면수량음다，척촌소교적기막공급응력，계산대래거대곤난。요준학적계산협신응력，기계산규모장비상거대，수요소모대량적계산궤자원재능완성。자모형기술통과대궤하모형적분해，재보증총체계산규모불태대적동시우가이보증중점부위적계산정도。본연구용Abaqus상업연건적자모형방법분석기막공주위응력분포，비교료전통계산방법화자모형방법적계산정도、시간화자원소모량。
The structure of the gas turbine cooling blade is extremely complex. It is difficult to calculate the stress in the blade because of large number of tiny and exquisite film cooling hole. Computation of precise stresses in the blade is usually of huge works, requiring super computer service. Submodel technology divides the geometry model to reduces the work of computation of stresses with precise results at key point or position. The analysis introduced in this paper is to use submodel method of Abaqus software to analyse the film cooling holes in the turbine blade, providing comparison of traditional method with the submodel method with respect to calculation accuracy, time and resources required.