航空发动机高压转子模拟平衡工艺分析与控制

针对大涵道比航空发动机高压转子采用模拟平衡工艺缺少数学分析手段以及模拟转子技术指标缺少制定依据的问题，提出一种模拟平衡工艺量化分析方法。以过转子重心的静和偶不平衡矢量来表示转子不平衡状态，定义了包含质量偏差、重心位置偏差、转动惯量偏差和端跳偏差的模拟转子模型，结合模拟平衡过程和转位平衡原理，建立转子校正不平衡量和转位补偿量数学模型，以高压组合转子初始不平衡量来评估模拟平衡质量。结果表明：模拟平衡能替代组合平衡，被平衡的两个转子均具备装配互换性和装配对接角度不受限制的特点；本案例中为控制模拟平衡质量，模拟转子质量偏差应在±4%以内，重心位置偏差应在±2 mm以内，直径和极转动惯量偏差均应在±5%以内，端跳偏差应小于0.008 mm。

Analysis and control of dummy balance process of aero-engine high pressure rotor

In view of the lack of mathematical analysis means of dummy balance process for high pressure rotor of high bypass ratio aero-engine and the lack of basis for technical indexes of dummy rotor, a quantitative analysis method of dummy balance process was proposed. The rotor unbalance state was represented by the static and couple unbalance vector passing through the rotor center of gravity. The dummy rotor model including weight deviation, center of gravity position deviation, moment of inertia deviation and end runout deviation was defined. Combined with the dummy balance process of high pressure rotor and the principle of index balance, the mathematical model of rotor correction unbalance and index compensation was established. And, the initial unbalance of high pressure combined rotor was used to evaluate the dummy balance quality. Results showed that, the dummy balance can replace the combined balance, and the two balanced rotors had the characteristics of assembly interchangeability and unrestricted assembly docking angle; in this case, in order to control the dummy balance quality, the dummy rotor weight deviation should be within ±4%, the center of gravity position deviation should be within ±2 mm, the diameter and polar moment of inertia deviation should be within ±5%, and the end runout deviation should be less than 0.008 mm.