航空发动机叶片-机匣碰摩过程的数值模拟

Numerical simulation of the dynamic process of aero-engine blade-to-case rub-impact

提出了基于隐式-显式相结合的积分方法对航空发动机叶片-机匣碰摩过程进行数值模拟,充分考虑了结构的低频线性稳态响应和碰摩引起的高频非线性瞬态响应.以某高压涡轮结构为例,仿真叶片-机匣碰摩的瞬态动力学过程,分析叶片的动力响应特征.研究结果表明:叶片-机匣碰摩过程中将产生影响应力分布的应力波并在叶身传导,碰摩结束后叶片将以低阶固有模态频率进行振动衰减.

Numerical simulation of the dynamic process of aero-engine blade-to-case rubimpact was conducted by explicit-implicit integration scheme. This took full account of lowfrequency liner steady-state response and high-frequency nonliner time-transient response due to the rub-impact. By taking the structure of a certain high-pressure turbine as example, the process of blade-to-case rub-impact was simulated, and the dynamic response characteristic of the blade during the process was analyzed. The results show that, the stress wave, which affects the stress distribution of blade, will be generated and propagated on the body of blade during the process of rub-impact;after the process of rub-impact, the dynamic response of blade is a decaying harmonic motion at the damped low-order natural frequency.