摘要
研究了燃气轮机涡轮涡流交错肋冷却导向叶片的冷却效果。采用由联立的连续方程、动量方程和能量方程构成的专用程序,计算了冷却系统流体动力和换热特性;采用通用的有限元计算方法计算了叶片温度场。通过对涡流交错肋通道的几何特性、流体阻力特性参数、叶片冷却系统的流体动力和换热、叶片温度场的计算,获得了气冷导向叶片的冷却效果。考虑到最大径向和周向不均匀度和+30℃裕度的情况,得到气冷叶片的中间截面平均降温为350℃,气冷叶片中截面的平均冷却效果为0.383。
The cooling efficency of the turbine guide vane with vortex interlaced rib was studied. The fluid dynamic and heat transfer of the cooling system were calculated by the special program consisted of the continuity equation, the momentum equation and the energy equation. The blade temperature field was calculated by the finite element method. The cooling efficency of the air-cooled vane was defined according to the calculations on geometrical parameter, fluid resistance characteristic, fluid dynamic and heat transfer of the cooling systemr, temperature field of the interlaced rib channels. Taking the maximal axial and radial irregularity and the ＋30℃ margin into account,the average temperature drop of the mid section for the air-cooled vane was 350℃, and the average cooling efficency of the mid section was 0.383.
出处
《航空发动机》
2010年第4期12-16,共5页
Aeroengine
关键词
气冷叶片
冷却技术
涡流
air-cooled vane
cool technology
vortex
作者简介
李俊山（1968-），男。高级工程师，从事航空发动机和燃气轮机的空气系统设计、热分析、气冷叶片冷却设计。
