航空发动机涡轮叶片包容模拟试验研究

Research on Aero-engine Turbine Blade Containment Experiment

为消除航空发动机非包容失效,首先需要通过叶片包容试验了解发动机部件的撞击、变形和破裂过程。在高速旋转试验台上进行模型的叶片包容试验,使用高速相机和高速数据采集系统构建特别的触发系统,记录叶片撞击机匣时的转子转速、机匣外壁上的应变波及叶片的运动轨迹。试验结果表明,叶片长度和动能对部件的撞击变形及破坏结果有极大的影响。高能量长叶片撞击将引起大变形,叶片弯曲成U形,机匣在第二次撞击处被撕裂击穿。相反地,叶片较短时,即使具有较高的撞击能量,对机匣的破坏作用也是极小的。叶片包容试验可以为结构优化设计和叶片包容仿真软件的开发提供大量有价值的数据。

To eliminate blade uncontained failul＇e, impaction and defnrrnation and fracture of engine components should be firstly understood through the blade contaiinment experiment. Blade containment tests used models components were done on the high-speed spin tester. A special trigger action system was designed using high-speed camera and high--speed data acquisition system. Rotor speed, impact strain wave on outer wall of the containment ring and motion of the released blade were all recorded at and after the blade impact on the inner wall of the ring. Test results clearly show that deformation and failure of the components are dominated hy length and kinetic energy of the released blade. The impaction of long blade with high energy can cause large deformation and the blade will curl as U shape and tear the wall of the ring at the second impact position. On the contrary, the ring causes lesser failure if the blade is short even if kinetic energy is high. Blade containment test can supply wealthy data which are useful for structure optimization and development of hlade containment simulation software.