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
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%.
