航空发动机涡轮叶片包容试验及数值模拟

Aero-Engine Turbine Blade Containment Tests and Numerical Simulation

为了解断裂涡轮叶片与包容环的撞击过程,研究航空发动机的包容性能,提高飞机飞行安全。在高速旋转试验台上进行了飞断平板叶片与包容环的撞击试验,并采用基于撞击动力学理论的有限元数值计算方法模拟了撞击过程。结果表明,平板叶片撞击包容环产生两个撞击点,第二撞击点是较为危险的撞击点,撞击点处的径向凸起量随初始撞击动能的增大而线性增大,两撞击点间的距离随初撞击动能的增大而线性减小,数值模拟准确地反映了叶片与包容环的撞击过程。研究结果对航空发动机包容环结构的优化设计和包容能力的校核计算有一定的参考价值。

In order to have more understanding of the process of breaking off blade impact on containment ring,a series of impacting tests to investigate the aero-engine containment capability has been carried out in a high speed spin facility. Single plate blade was used during the tests. Impacting processes were simulated with finite element numerical method based on impact dynamics theory. Single released blade exerted two impacts one after another on the containment ring at two different points. The second impact is more dangerous than the first. Radial bulge of the containment ring at impact point increases linearly with the initial kinetic energy of the broken blade. However ,circumferential distances between two impacted zones decrease linearly with initial kinetic energy. Numerical simulations show a good agreement of the predicted impacting process with the experimental results. The results can be used as a reference for the containment ring optimum design and blade containment capability check.