Research On The Fracture Of Aircraft Engine Compressor Blade On LAMMPS

In order to improve the safety of the aircraft engine, it’s necessary to fully consider the motion characteristics of debris, so the fracture of engine rotor blade should be studied. Then it sets up the reasonable analysis process and analysis methods so as to evaluate the safety of engine.Taking into account the complex working conditions of the turbine blade, first, this paper selected the aviation engine compressor rotor blades to be the research object. This paper analyzed the macro-fracture mechanism of blade using fracture mechanics theory and the initiation mechanism of microscopic cracks of blade using the dislocation theory. This paper studied the macro-fracture mechanism of blades using Peridynamics, a method of molecular dynamics software—LAMMPS(Large-scale Atomic/Molecular Massively Parallel Simulator),analyzed the relationship between the Peridynamics method and the traditional theory. The research of the blade fracture makes the research of potential functions to be a very important key. In order to study the fracture of blade, multi-element alloys, EAM(embedded atom method) was introduced to Peridynamics method to calculate the potential function, this paper analyzed the new Peridynamics equations of motion using the method of EAM, computed the discrete Peridynamics equations of motion, the feasibility of this approach that introduces the EAM to Peridynamics method was also analyzed by defining the parameters of multi-element alloy EAM potential function.Finally, this paper built two-dimensional rectangular plate model and three-dimensional blade models of aircraft engine rotor blade, using the Peridynamics method of LAMMPS, and converted the calculation results to graphics by a molecular visualization program, VMD, and analyzed the series of calculation results and stress-strain curves of blade models, analyzed the main factors that influence fracture of blade, proposed the appropriate technical measures preventing the failure and fracture of blades, this conclusion provided reference for safety study of aircraft engine.