Assembly Optimization Of High Pressure And Pneumatic Maneuvering Balance Blades For Aero Engine

The aero engine is one of the most core components of the aircraft.When the highpressure compressor rotates at high speed,the imbalance measurement of the rotor has a greater impact on the vibration of the whole machine,which has become one of the main factors that cause aero engine vibration failure.The high-pressure compressor rotor usually has both static imbalance and force couple imbalance after assembly.It is necessary to perform dynamic balancing on the dynamic balancer several times after the blade installation is completed or after multi-stage assembly to improve the balance,which is time-consuming and economical.Big.How to minimize the initial imbalance after blade installation is a problem encountered by engine manufacturers in blade assembly.Firstly,the causes of the imbalance of the rotor of the high-pressure compressor and the principle of static and dynamic balance of the quasi-rigid rotor are analyzed.A mechanical model was developed to make the static imbalance of the rotor single rotor blades smaller,and it was converted into a mathematical model.According to the actual installation requirements of the manufacturer,an improved particle swarm optimization algorithm was used to optimize the single-stage blade sequencing scheme.After the simulation calculation of the actual data of the engine V2500 fourth-stage blades,the residual static imbalance was greatly reduced;and then through the rotor multi-stage disk mechanics The establishment of the model studied the two-objective optimization problem that required the unbalanced force and the unbalanced torque to be relatively small at the same time,and constructed a suitable single-objective function.Then the traditional genetic algorithm was used to solve the optimization of the multi-stage rotor phase angle,and the search range was too large.And there are too many unknown dimensions,and it is difficult to get accurate optimization results.The quantum genetic algorithm has a highly parallel principle in its coding method.The search range is wide and the convergence speed is faster than the traditional genetic algorithm.The quantum genetic algorithm was used to calculate the installation phase of the multi-stage disc rotor,and compared with the data of the traditional genetic algorithm,the residual unbalanced torque and unbalance force of the high-pressure compressor rotor after the multi-stage disc installation was optimized,so that The rotor of the high-pressure compressor can have a good balance accuracy after the blade assembly is completed.Finally,based on MATLAB,a GUI interactive interface "Assembly Optimization System for High-pressure Compressed Aircraft Mobility Balance Blades of Aero Engines" was established to use and calculate the optimization scheme of compressor rotor balance assembly more intuitively,and verified the system feasibility after complete data calculation Has good practical significance.