Research On The Optimal Assembly Method For The Unbalanced Quantity Of The Multi-stage Rotor With Separate Disk And Blades Of Aeroengine

As the power source of aircraft,aeroengine has become the key development object of China’s aviation industry due to the high requirements of processing technology,materials and design ability.High temperature and high pressure environment put forward high requirements for the working performance of engine rotor,in which the rotor unbalance is an important index for the excellent performance evaluation of engine rotor,which directly affects the vibration characteristics of the rotor.In this paper,the multi-stage disk separated rotor is taken as the object,starting from the assembly technology,the assembly method to reduce the rotor unbalance is studied,in order to improve the working performance of aero-engine.In order to solve the problem that the transmission mechanism of unbalance in disk separation rotor is not clear,a multi-stage disk separation rotor unbalance transmission model is established.The model analyzes the machining error,the influence of assembly error on the characteristics of blade assembly centroid,and the transfer process of machining error between adjacent rotor systems.It shows the relationship between unbalance of rotor system and blade mass moment and errors.Based on the model,an optimization method for the unbalance assembly of array blades is proposed,and the feasibility of the optimization method is analyzed by simulation.In order to solve the problems of low search accuracy and long calculation time of the current array blade arrangement algorithm,an intelligent blade arrangement algorithm based on the quartile weight interleaving distribution is proposed in this paper.The algorithm combines the advantages of genetic algorithm and four sector weight interleaving distribution method to achieve high precision and high-speed search.Based on this algorithm,a double condition termination method is proposed,which solves the problem of falling into local optimum in the application of genetic algorithm in blade layout and maintains good stability of search accuracy.In order to solve the problem that the important parameters of aero-engine assembly process exceed the standard easily,a multi-stage rotor virtual model is established to realize the monitoring of rotor centroid and unbalance characteristics.Based on the digital modeling method,multi-dimensional data part expression method,spatial data volume parameter calibration method and data volume control method,the model realizes the spatial virtual assembly of multi-stage disk separation rotor and the monitoring of unbalance and centroid parameters,and solves the problems of large number of rotor parts,long assembly time,inconvenient disassembly and replacement and easy wear.In order to verify the effectiveness of the unbalance transfer model and the blade array optimization method,the unbalance detection experiments of single-stage rotor and multi-stage rotor assembly are carried out.In the experiment,by measuring the basic parameters,machining error,unbalance and mass moment of the disk and blade,the assembly unbalance of the disc separated rotor is predicted.The results show that the maximum error of unbalance prediction is 14.9%,and the maximum error of angle prediction is 6.8°,The effectiveness of unbalance transfer of disk separation rotor is verified;In addition,compared with the genetic algorithm,the improved genetic algorithm improves the single-stage rotor unbalance by 16.7%,Compared with genetic algorithm,hybrid intelligent algorithm optimizes 32.6%;In the optimization of combined rotor unbalance,advanced genetic algorithm is 35.7%higher than genetic algorithm,and hybrid intelligent algorithm is 66.9% higher than genetic algorithm.