旋转多段连接通道换热特性数值模拟研究

发布时间：2018-01-29 12:58

  本文关键词： 航空航天科学技术基础学科 带肋通道 旋转 对流传热 数值模拟 压力系数　出处：《兵工学报》2016年03期 　论文类型：期刊论文

【摘要】：为深入了解旋转作用力对涡轮叶片多段连接通道换热特征的影响,采用三维数值模拟方法研究了多段连接内通道模型的流动换热。选取通道入口雷诺数为17 000、旋转数范围为0~0.09,多段连接通道3个出口的质量流量比例为25%、50%、25%,旋转半径与水力直径之比的范围为0~69.6,研究了旋转数、旋转半径对各段通道带肋壁面换热分布的影响。结果表明:旋转附加力造成径向出流通道沿程压力系数逐渐增大,径向入流通道的沿程压力系数迅速减小;径向出流通道后缘面的换热系数随旋转数增加而增大,径向入流通道后缘面的换热系数随旋转数增加而稍有减小,旋转作用对前缘面换热的影响情况与后缘面的情况相反;前、后缘面的换热系数沿流向均随旋转半径与水力直径比的增加稍有增大,换热增大幅度较小。
[Abstract]:In order to understand the effect of rotating force on the heat transfer characteristics of turbine blade multi-section connection channel. In this paper, the flow heat transfer of the multi-segment connected internal channel model is studied by using three-dimensional numerical simulation method. The Reynolds number at the entrance of the channel is 17 000 and the rotation number is 0 ~ 0.09. The mass / flow ratio of the three exits of the multi-section connecting channel is 25 / 50 and the ratio of the radius of rotation to the hydraulic diameter is 0 / 69.6. the number of rotations is studied. The effect of radius of rotation on the heat transfer distribution on the ribbed wall of each section of channel. The results show that the pressure coefficient of radial outlet channel increases gradually and the pressure coefficient of radial inlet channel decreases rapidly due to the additional force of rotation. The heat transfer coefficient of the rear edge of the radial outlet increases with the increase of the number of rotations, and the heat transfer coefficient of the rear edge of the radial flow channel decreases slightly with the increase of the number of rotations. The effect of rotation on the heat transfer on the front edge is opposite to that on the rear edge. The heat transfer coefficient of the front and rear edge surfaces increases slightly along the flow direction with the increase of the ratio of the radius of rotation to the hydraulic diameter, but the increase of heat transfer is smaller.
【作者单位】： 西安航空学院;西安航天动力试验技术研究所;
【基金】：国家自然科学基金项目(51575420) 陕西省自然科学基金项目(2014JM2-5069) 西安市技术转移促进工程-产学研合作重大项目(CXY1518(2))
【分类号】：TK401
【正文快照】： 0引言现代燃气涡轮发动机燃气的温度已远高于涡轮叶片材料的耐热极限,必须对涡轮叶片采取有效的冷却措施,才能使得燃气涡轮发动机安全、稳定、可靠的运行。现代燃气涡轮叶片多采用内、外部组合冷却方式,目的是借助最少的冷气达到相对较好的冷却效果;叶片内部是采用多腔通道的，

本文编号：1473474