A computing technology of the numerical simulations based on Abaqus code is presented in this paper for complex analysis of the uniaxial compressed stiffened composite panel,having local impact damage.The technology a...A computing technology of the numerical simulations based on Abaqus code is presented in this paper for complex analysis of the uniaxial compressed stiffened composite panel,having local impact damage.The technology allows simulating both dynamic deformations of the panel subjected to local impact and followed up by an axial static compression.A reliability of the developed computing technology is confirmed by comparison and closeness of the obtained numerical results and experimental data.Discrepancy of values obtained by the simulation from the corresponding experimental data is 8%for maximum contact force between the panel and impactor,7%for crack length on the opposite to the impact side of the panel and 10%for ultimate force,when the initially damaged panel is in compression.Also,the acceptable qualitative similarity of the modeled fracture mechanism and the shape to that observed in the experiments is observed.展开更多
Propagation of low cycle fatigue cracks in main parts of an aviation gas turbine engine can cause sudden engine destruction during operationwith catastrophic consequences.Accurate prediction of an engine lowcycle fati...Propagation of low cycle fatigue cracks in main parts of an aviation gas turbine engine can cause sudden engine destruction during operationwith catastrophic consequences.Accurate prediction of an engine lowcycle fatigue durability can be accessed using finite element simulations.Main aspects of the applied approach for low cycle fatigue stable crack propagation finite element simulations in 3D specification for main parts of an aviation gas turbine engine are described in the article.These include applied formulation and procedure,descriptions of applied models and assumptions,parameters of generated grids,some results of grid convergence studies and simulation results for turbine discs.The significance of some aspects for solution accuracy such as along crack front grid resolution is demonstrated.Advancements to the applied approach are proposed which include solution under-relaxation preventing instability when large crack propagation steps are used and circular correction improving crack path prediction accuracy for bodies of revolution.The improvements result in the overall simulation accuracy increase and effort decrease up to 50%.展开更多
文摘A computing technology of the numerical simulations based on Abaqus code is presented in this paper for complex analysis of the uniaxial compressed stiffened composite panel,having local impact damage.The technology allows simulating both dynamic deformations of the panel subjected to local impact and followed up by an axial static compression.A reliability of the developed computing technology is confirmed by comparison and closeness of the obtained numerical results and experimental data.Discrepancy of values obtained by the simulation from the corresponding experimental data is 8%for maximum contact force between the panel and impactor,7%for crack length on the opposite to the impact side of the panel and 10%for ultimate force,when the initially damaged panel is in compression.Also,the acceptable qualitative similarity of the modeled fracture mechanism and the shape to that observed in the experiments is observed.
基金sponsored by Sarov Engineering Center(www.saec.ru)supported by the UECKlimov。
文摘Propagation of low cycle fatigue cracks in main parts of an aviation gas turbine engine can cause sudden engine destruction during operationwith catastrophic consequences.Accurate prediction of an engine lowcycle fatigue durability can be accessed using finite element simulations.Main aspects of the applied approach for low cycle fatigue stable crack propagation finite element simulations in 3D specification for main parts of an aviation gas turbine engine are described in the article.These include applied formulation and procedure,descriptions of applied models and assumptions,parameters of generated grids,some results of grid convergence studies and simulation results for turbine discs.The significance of some aspects for solution accuracy such as along crack front grid resolution is demonstrated.Advancements to the applied approach are proposed which include solution under-relaxation preventing instability when large crack propagation steps are used and circular correction improving crack path prediction accuracy for bodies of revolution.The improvements result in the overall simulation accuracy increase and effort decrease up to 50%.
