Structural Characteristics Of Axial Compressor Blades Under Multiple Loads

As a key component of aeroengine,the performance of axial compressor blade directly affects the safety and reliability of the whole engine.In the real working environment,the blade is affected by multi-load coupling such as centrifugal load,aerodynamic load and thermal load,which is prone to blade fracture accidents and greatly affects the safety of use.In this paper,a multi-field coupling platform is constructed,and the strength and vibration of the blade are calculated by the fluid-thermal-solid coupling method.The strength variation law of the blade under different loads is obtained,and the pre-stressed modal analysis of the blade is carried out to judge the resonance of the blade.In order to reduce blade quality and improve its safe service life,a composite compressor blade modeling method was proposed,and the structural characteristics of composite compressor blades were studied on this basis.The main research work is as follows:(1)The finite element model of Rotor 37 blade was built,and the simulation was carried out based on N-S equation,and the simulation results were compared with the experimental results to ensure the accuracy of the numerical simulation method in this paper.The calculated results were in good agreement with the experimental values,and the numerical simulation calculation method in this paper was feasible and accurate.(2)The aerodynamic performance of the rotor blade of the compressor rotor 37 at the design speed and off-design speed was studied,and the changes of stability and instability characteristics of the compressor blade at the design speed of 100%,90%,80% and 70% were analyzed.(3)A multi-field coupling platform was established to conduct fluid-thermal-solid coupling simulation on compressor blades based on the loose coupling theory to study the strength and vibration structure characteristics of the blades under the coupling effects of aerodynamic,thermal and centrifugal loads.The results show that there is a resonance point in the compressor blade at about 63% and 98% rotational speed.In this case,the blade is prone to resonance.(4)A modeling method for composite compressor blades is proposed,and the feasibility and reliability of the modeling method are verified by comparing with the traditional 3D software modeling results.The finite element analysis method was used to study the effect of layering Angle on the structural characteristics of composite blades in different regions.Compared with traditional titanium alloy blades,the weight of composite blades in this paper was reduced by about 60%.Because the blade is always in high speed and high pressure state during working,it is easy to cause fatigue damage caused by vibration.Therefore,the structural characteristics of composite blades under multiple loads are studied and compared with titanium alloy blades.The results show that the resonance point of composite blades changes compared with titanium alloy blades.