涡轮叶顶间隙形态的优化  

Optimization design of turbine blade tip clearance shapes

作　　者：岂兴明[1] 朴英[1] 周建兴[1] 祝剑虹[1] 

机构地区：[1]清华大学航天航空学院,北京100084

出　　处：《吉林大学学报（工学版）》2009年第4期874-879,共6页Journal of Jilin University:Engineering and Technology Edition

基　　金：军工项目

摘　　要：以某航空发动机上的涡轮叶顶间隙形态为研究对象,采用数值仿真分析手段,讨论了叶顶间隙的参数化建模、设计优化集成以及间隙形态的设计优化等问题。对涡轮流场细节的分析表明,计算结果与试验数据吻合较好,优化后的涡轮绝热效率提高了0.395%。Taking the blade tip clearance shape of the high-pressure turbine in an aero-engine as the objective of research, the parameterized modeling, the process integration and the optimization of the tip clearance shape were explored by means of the numerical analysis. The detailed information of the flow field show that the calculated results agree well with the experiment data. The isentropic efficiency of the turbine was improved by 0. 395 % by optimization.

关 键 词：流体传动与控制 叶顶间隙 航空发动机 高压涡轮 数值分析 优化 

分 类 号：TH137.1[机械工程—机械制造及自动化]