涡轮叶片带肋U型通道水流模拟试验研究  

Experimental research on ribbed U-shaped channels of turbine blade by water flow simulation

作　　者：刘波[1] 王永红[1] 张琳[1] 

机构地区：[1]中国燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2015年第3期39-42,共4页Gas Turbine Experiment and Research

摘　　要：针对航空发动机高压涡轮叶片尖部带肋U型通道、根部带肋U型通道和有尾缘劈缝尖部带肋U型通道放大模型,在保证几何面积相似、冷气流和水流进口雷诺数相等的条件下,分别采用红墨水和氮气作为示踪剂进行水流模拟试验,显示三种带肋U型通道的流动情况。试验结果表明,两种尖部带肋U型通道不存在滞止区,满足设计要求;根部带肋U型通道中气流发生分离,流场不稳定,需要调整肋的位置。Water flow simulation experiments were conducted to investigate ribbed U-shaped channel mod-els of an aero-engine high pressure turbine blade, which were tip-ribbed, root-ribbed, and tip-ribbed with trailing edge slot. The tests were made under the conditions of similar geometric area, equal Reynolds num-ber of water and cool air flow inlet. Red ink and nitrogen were used as tracers to show the flow conditions of the three types of ribbed U-shaped channels. The experimental results indicate that there are no stagnation zones in the two tip-ribbed U-shaped channels, which meet the design requirements, and there is flow sepa-ration in the root-ribbed U-shaped channel causing flow instability and therefore the position of rib needs to be adjusted.

关 键 词：航空发动机 涡轮叶片 带肋U型通道 水流模拟 示踪剂 红墨水 氮气泡 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程] V263.3