Investigation on damage mechanism of compressor blades in turboshaft engine induced by ice impacts at various locations

冰冲击位置对涡轴发动机压气机叶片损伤影响研究

Ice causes impact damage to different positions of the compressor blade,destroys the structural integrity of the rotor structure,and then causes unbalanced failure and even causes nonlinear vibration accidents such as collision and friction,which affects the execution of helicopter tasks.To investigate the influence of impact position on the damage form and dynamic response of blades during ice impact,a dynamic model by finite element-smooth particle fluid dynamic coupling method is created.The ice impact damage experiment of the TC4 plate based on the air gun experimental platform was carried out to verify the reliability of the simulation model.The damage of compressor blades impacted by ice from different positions under static and design speed of 45000 r/min is analyzed.The research results indicate that under static conditions,the damage caused by ice impact from the leading edge blade tip to the leading edge blade root first increases and then decreases,with the maximum damage occurring at the 66.7%blade height position on the leading edge.At the design speed,the closer the impact locations are to the leaf tip,the greater the damage is,and the plastic damage,equivalent stress,and kinetic energy loss of the ice impact are lower than the blade static condition.The research conclusion can provide theoretical reference and data support for the design of structural strength and protection of compressor blades in turboshaft engines.

冰对压气机叶片不同位置造成冲击损伤,破坏转子结构完整性,进而产生不平衡故障甚至诱发碰摩等非线性振动事故,影响直升机任务执行.为研究冰冲击过程中冲击位置对叶片损伤形式及动力学响应的影响,采用有限元-光滑粒子流体动力学耦合方法(FEMSPH)创建了动力学模型.开展基于高速轻气炮实验装置的钛合金板冰冲击损伤实验,验证了仿真模型可靠性,分析静止和设计转速45000 r/min两种工况下冰从不同位置冲击压气机叶片的损伤情况.研究结果表明:静止状态下,冰从前缘叶尖到前缘叶根进行冲击产生的损伤先增大后减小,最大损伤发生在前缘66.7%的叶片高度位置.在设计速度下,冰冲击位置越靠近叶尖产生的损伤越大,冰冲击叶片产生的塑性损伤、等效应力及动能损失均低于叶片静止工况.研究结论可为涡轴发动机压气机叶片结构强度设计及防护提供理论参考和数据支持.