Research Of Turbine Blade Lifecycle For Small Civilian High Bypass Ratio Turbofan Engine

The rapid rise of general aviation has promoted the popularity of small aircraft,and the matching power unit small large bypass ratio engine has also attracted attention.The turbine component is the main source of power for the aircraft.The working environment is extremely harsh,and it is directly in contact with the high-temperature gas discharged from the combustion chamber,and is subjected to temperature alternating and stress alternating.Therefore,estimating the life of turbine blades is one of the key aspects of engine performance research.In this paper,based on the actual conditions,a small large bypass ratio engine with more material data is selected as the research object.Firstly,two tools are used to process the data.The first is an engine mathematical model based on the logical relationship between components.Secondly,the cycle data is processed by the rain flow counting method to obtain the cycle speed spectrum and the temperature spectrum at the turbine inlet.The second method is to use finite element software to simulate the coupling of thermodynamics of turbine blade flow,that is,to study and analyze fluid mechanics,thermodynamics and solid statics simultaneously.The three-dimensional model of the blade is established in Solideworks through the actual three-dimensional parameters of the turbine blade.Combined with the import and export conditions given by the mathematical model,the variation of the performance parameters of the turbine under actual operation is simulated.Finally,the simulated data is brought into the model of turbine blade life prediction to predict the fatigue life,creep life and fatigue/creep life of the turbine blade.Finally,it is estimated that the value of the turbine blade fatigue/creep life is 6,288 cycles,11947.2 hours.