郑州航空工业管理学院学报

为明确振动信号在航空发动机支承结构的响应机理，从航空发动机中简化出4种应用最多的典型支承结构并建立有限元模型，通过谐响应与瞬态响应计算得到其在单点激励下的稳态响应特征与动力学响应状况并分析其振动响应规律。建立航空发动机支承系统有限元模型，计算其单点激励下的振动响应，以整机系统验证响应规律的普适性。研究结果表明：支承结构加速度响应峰值与激励方向及结构延伸特性呈显著相关性；4种支承结构皆在前三阶内的固有频率处产生相应峰值，之后间断产生峰值；信号测点距固定端较远时，激励大小增加1倍，支承结构加速度最大响应值增大1倍；激励频率增大1倍，I型支承结构的响应值增大5至10倍，Z型支承结构沿激励方向的响应值衰减73%，突变I型支承结构沿两方向的响应值增大2.4至4.4倍，突变Ⅱ型支承结构沿两方向的响应值增大1.6倍。航空发动机典型支承结构振动响应机理可为研究振动传递路径与振动监测传感器布局提供参考。

In order to clarify the response mechanism of vibration signals in the aero-engine Supporting Structures, four typical support structures that are most widely used in aero-engines are simplified and their finite element models are established. Through the calculation of harmonic response and transient response, the steady-state response characteristics and dynamic response under single-point excitation are obtained, and the vibration response rules are analyzed. Then, a finite element model of the aero-engine supporting system is established to calculate its vibration response under single-point excitation, and the universality of the response rules is verified with the whole engine system. The results show that there is a significant correlation between the acceleration response peak value of the supporting structure, the excitation direction, and the structural extension characteristics; all four types of supporting structures generate corresponding peaks at the natural frequencies within the first three orders, and then generate peaks intermittently; when the signal measuring point is far away from the fixed end, doubling the excitation magnitude leads to a doubling of the maximum acceleration response value of the supporting structure; when the excitation frequency is doubled, the response value of the type I supporting structure increases by 5 to 10 times, the response value of the type Z supporting structure along the excitation direction decreases by 73%, the response values of the mutant type I supporting structure along the two directions increase by 2.4 to 4.4 times, and those of the mutant type II supporting structure along the two directions increase by 1.6 times. The vibration response mechanism of the typical aero-engine supporting structure can provide a reference for the research on the vibration transmission paths and the layout of vibration monitoring sensors.