The Design Of The Dual Rotor Vibration Fault Simulation Test Rig For An Aeroengine

Aeroengine as the power unit of the plane, is the decisive factors of aeroengine’s performance, reliability and cost, and is known as the heart of the plane.However, aeroengine is of high manufacturing costs, low service life, easy to malfunction, and difficult to maintain, which is sources of most aircraft accident.According to statistics,aeroengine fault is more than 70% from the rotor vibration, so to solve the vibration fault of the aeroengine has been one of the important link of the whole engine development and improvement process. Experimental reseach as one of the most important auxiliary means in the study of aeroengine’s vibration fault. It provided a large number of experimental data for theoretical study of vibration fault,which is important to basic research, the whole engine design and manufacture of aeroengine.However testing expenses and risk is both higher using real devices to test in general.Now,simulation test rig become the most important part of the most experimental research.The research content of this article designed the rotor test rig used for vibration fault simulation of a certain type aeroengine.In order to ensure that the rotor test rig can better simulate the typical vibration fault of the actual aeroengine, the similar principles of the physical-mechanical structural characteristics and dynamic characteristics have been taken.The article calculated the critical speed and the mode of vibration of the actual aeroengine rotor and campared it with the given value.According to the critical speed and the mode of vibration of the actual aeroengine rotor, the rotor test rig was designed, and the rotor of test rig were campared with the rotor of actual aeroengine in the support system, the support span, the support stiffness distribution, the mass distribution, the shaft stiffness distribution and the critical speed and the mode of vibration of rotor and so on.In order to ensure that the design scheme is feasible, some experiments have been carried out to test related components.Test results showed that the designed components could meet the experimental requirements.Besides the paper studied the influence of different constraint methods on the rotor’s critical spped, and campared the theoretical calculation value of the critical speed with the experiment measured value. Results showed that the rotor’s critical spped was affected by the rotor’s misalignment,the installation of the squirrel cage and constraints of the motor and so on.Through this topic research,the dual rotor vibration fault simulation test rig for aeroengine has been designed, and the general design method of double rotor test rig was summarized.Besides by contrastive analysis between the finite element calculation values and the testing results,the reliability of the critical speed calculation method of rotor-support system was validated.Research result had certain reference significance for the design of the rotor test rig and the calculation of critical speed.