某型航空发动机高压涡轮叶顶间隙三维数值分析  

3-D numerical analysis of the tip clearance of an aero-engine high pressure turbine

作　　者：岂兴明[1] 朴英[1] 祝剑虹[1] 周建兴[1] 

机构地区：[1]清华大学航空航天学院,北京100084

出　　处：《航空动力学报》2008年第5期904-908,共5页Journal of Aerospace Power

摘　　要：利用有限元分析软件计算出了某型航空发动机高压涡轮叶顶间隙的时间历程变化.分析过程中考虑了温度、压力和转速的影响,并给出了施加边界条件的新方法.通过与前人的计算方法进行对比分析,得出了较为合理的结果:转速的影响是轮盘径向尺寸变化的主要因素,而温度是影响机匣和叶片的主要因素,叶顶间隙分别在慢车突然加速和反推力状态下出现最小值.By means of finite element method, the changes of the tip clearance of an aero-engine＇s high pressure turbine （HPT） were calculated, the influences of pressure, temperature and rotation speed were considered and a new method of applying the boundary conditions was presented as well. After comparison with and analysis of former methods, this paper has reached some reasonable conclusions： the shaft speed plays a major role in the displacement of turbine disc, while the temperature is a major influential factor to the blade and shroud. Minimum tip clearance will occur during the first acceleration of the engine and the re-burst processes, respectively.

关 键 词：航空、航天推进系统 叶顶间隙 有限元法 高压涡轮 数值分析 

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]