复合式气冷涡轮导叶冷却设计与试验  

Design and Experimental Research of Compound Air-cooled Turbine Guide Vane

作　　者：郭文[1] 吉洪湖[1] 蔡毅[2] 刘玉芳[2] 呼艳丽[2] 潘炳华[2] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]中国燃气涡轮研究院,四川成都610500

出　　处：《航空动力学报》2005年第3期456-459,共4页Journal of Aerospace Power

摘　　要：介绍了某型复合式气冷涡轮导叶的冷却设计与试验研究,在较高的温度和压力条件下,进行了真实叶片的冷却效果试验。通过对试验状态的对比计算及试验结果的分析,结果表明:所设计的涡轮复合式气冷导叶在较宽广的冷气流量比范围内,具有良好的冷却特性,计算结果与试验结果吻合较好。In modern aircraft engines, different kind of cooling techniques such as film showerhead, film spills internal heat transfer enhancement and pin-fin with impingement were used together to keep the turbine blades and guide vanes operating safely. Design and experimental research of compound air-cooled turbine guide vane were presented. The overall cooling characteristics of a real vane was tested and calculated at elevated pressures and temperatures. Experimental results show that the cooling characteristics of the vane are superior while the cooling mass flow ratios varies between 6% and 16%, and the calculation results are in good agreement with the experiments.

关 键 词：航空、航天推进系统 导叶冷却设计 试验 复合式冷却 

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]