涡轮导叶综合冷效试验件设计及验证  

Design and Verification of Integrated Cooling Effectiveness Test Specimen for Turbine Vane

作　　者：钟山[1] 刘志刚[1] 朱榕川[1] 方弘毅[1] 顾杨[1] 

机构地区：[1]中国燃气涡轮研究院,四川江油621703

出　　处：《燃气涡轮试验与研究》2014年第3期34-38,共5页Gas Turbine Experiment and Research

摘　　要：为保证新研制的导向叶片在发动机上可靠工作,须先对其进行冷效试验,以验证气膜冷却的气动参数、几何参数对冷却效果及涡轮气动性能的影响。试验件结构设计中根据相似原则,采用单层干烧结构,并采用UG参数化建模和装配、间隙分析减小装配误差和干涉,提高了冷效试验效率。试验件内温度场、压力场较好,具有良好的耐温性、密封性;试验件设计中,配合更换试验件耐热材料,较常规水冷式试验件结构简单,且加工周期缩短一半,造价减少约60%。To make turbine nozzle work reliably, cooling effectiveness test should be firstly conducted to study the aerodynamic effect and geometric parameters of film cooling on cooling effectiveness and turbine aerodynamic performance. Based on the principle of similarity,the test specimen adopted simple deck dry combustion constructure. UG parameterized modeling and assembling as well as clearance analysis was ap-plied to reduce the assembling error and interference, and thus improved the efficiency of cooling effective-ness test. Preferable temperature and pressure fields were obtained inside the test specimen, which were of good hot-resistance and sealing performance. Matched heat-resistant material made its common wa-ter-cooling construction simpler, shortened half of its process cycle and reduced approximately 60% of its cost.

关 键 词：涡轮导向叶片 结构设计 间隙分析 数值模拟 冷效试验件 耐热材料 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]