The precise measurement of three-dimensional stress in the rotor is a key means to ensure the assembly accuracy and operational safety of aero-engines. The unclear coupling influence mechanism of different directions of stress on ultrasonic propagation makes it challenging to establish a three-dimensional stress measurement model. This paper proposes a three-dimensional assembly stress measurement method for aero-engine rotors based on ultrasonic propagation time difference decoupling. The three-dimensional assembly stress is converted into the stress component parallel and perpendicular to the ultrasonic wave propagation direction in this method. The acoustoelastic equation including three-dimensional stress parameters is established based on the function model of different direction stress and ultrasonic wave propagation velocity. An innovative three-transducer stress measurement scheme is designed, which integrates ultrasonic wave transmitting and receiving transducers and time difference feedback transducers. The acoustoelastic equations in three propagation directions are constructed by rotating the transducer group to change the propagation direction of ultrasonic waves. Finally, the acoustoelastic equations are solved simultaneously to decouple the ultrasonic propagation time difference, thus achieving a three-dimensional assembly stress measurement of the aero-engine rotor. The experimental results show that the maximum deviation between the measured values and the simulation results in the x ,y, and z directions is 15.885 MPa, 14.113 MPa, and 17.093 MPa, respectively. This study provides effective theoretical and technical support for precisely measuring three-dimensional assembly stress in high-end equipment represented by aero-engines.

中文翻译：

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航空发动机转子三维装配应力超声波测量方法


转子三维应力的精确测量是保证航空发动机装配精度和运行安全的关键手段。不同方向应力对超声波传播的耦合影响机制尚不清楚，这使得建立三维应力测量模型具有挑战性。提出一种基于超声波传播时间差解耦的航空发动机转子三维装配应力测量方法。该方法将三维装配应力转换为平行于和垂直于超声波传播方向的应力分量。基于不同方向应力与超声波传播速度的函数模型，建立了包含三维应力参数的声弹方程。设计了一种创新的三传感器应力测量方案，该方案集成了超声波发射和接收传感器以及时差反馈传感器。通过旋转换能器组改变超声波的传播方向，构建三个传播方向的声弹方程。最后同时求解声弹方程，解耦超声波传播时间差，从而实现航空发动机转子三维装配应力测量。实验结果表明，x、y、z方向的测量值与模拟结果的最大偏差分别为15.885 MPa、14.113 MPa、17.093 MPa。该研究为以航空发动机为代表的高端装备三维装配应力的精确测量提供了有效的理论和技术支撑。