复合冷却涡轮导叶的气热耦合数值模拟  

Conjugate Heat Transfer of a Turbine Vane with Compound Cooling Structure

作　　者：邵婧[1] 李杰 吴伟亮[1] 

机构地区：[1]上海交通大学叶轮机械研究所,上海200240 [2]中航商用航空发动机有限责任公司,上海201108

出　　处：《科学技术与工程》2014年第5期292-296,313,共6页Science Technology and Engineering

摘　　要：采用气热耦合方法对高压涡轮一级导叶带全气膜冷却、冲击冷却和尾缘劈缝冷却的复合冷却结构进行了数值模拟。分析了带复合冷却结构叶片的三维温度场,主要研究了主流燃气雷诺数、冷气与燃气的流量比和燃气与冷气的温比对叶片温度和冷却效果的影响。结果表明:随着流量比增大,叶片前缘壁面平均温度先增后减,压力面和吸力面温度均减小。叶片壁面各处平均温度随温比增大而降低,受雷诺数影响很小。叶片综合冷却效果随流量比增大而增大,受温比和雷诺数影响很小。Conjugate heat transfer methodology was employed to simulate the a turbine vane with compound cooling structure which include film cooling,impingent cooling and trailing edge cooling.Distribution of the turbine vane temperature is discussed and focused on the effects of gas Reynolds number,cooling flow rate and gas temperature rate on average wall temperature and vane cooling efficiency.Results showed that the leading edge temperature increased first and then decreased while the pressure and suction side temperature decreased with increasing of flow rate.Average wall temperature decreased with increasing temperature rate and had little difference with increasing Reynolds number.Vane cooling efficiency increased with increasing flow rate and had little difference with increasing temperature rate or Reynolds number.

关 键 词：涡轮叶片 复合冷却 数值模拟 气热耦合 冷却效果 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]