Investigation Of The Aerodynamic Excitation And Vibration Response Of A Compressor Rotor

When compressor blades working in the aircraft engine,it will be loaded unsteady flow excitation force which will lead to force vibration.In this paper,the first stage of a high-pressure compressor rotor blade is the research object.Firstly,the steady and unsteady numerical computational methods are verified.Then,calculate and analyze the flow exciting force and the vibration response caused by it in different working condition.Use the method of harmonic response to analyze vibration response in different working condition and different tip-clearance.At last,the fluid structure coupling is computed,and be compared with the result of decoupled method.The results indicate that the two kinds of unsteady calculation methods all have high accuracy,in addition,the reduction method takes the least time and is suitable for engineering calculation.Though the whole cycle method is the most time-consuming method,it is suitable for observing the flow field details.By analyzing the detail of flow in result of whole cycle method,it's found that the leakage flow of rotor's tip-clearance,the wake of the front leaves and the circumferential flow caused by rotation of rotor is three main reasons for the excitation.For different working conditions of unsteady excitation force,the amplitude of near stall point is obviously larger than other cases,and the location with the largest vibration amplitude mainly concentrates on the leading edge of the blade.For different levels of exciting force,the result shows that it mainly focuses on the first three orders.Besides,the surface integral result of unsteady exciting force is about 10% of the steady exciting force.Finally,by comparing the calculated results of the fluid-structure coupling method and the decoupling method,it is found that the error of them is quite small,which is validated for engineering application.