论文部分内容阅读
为了有效地克服传统叶尖间隙在航空发动机涡轮叶盘的健康监测中传递信息能力有限的不足,充分考虑了在航空发动机运行过程中涡轮叶片叶尖的3维特征,提出包含径向间隙、叶片叶尖端面轴向偏转角和周向偏转角在内的涡轮3维叶尖间隙的概念,并将3维叶尖间隙特征参量作为叶片故障信号载体,通过有限元方法分析了3维叶尖间隙特征参量对高压涡轮叶片典型裂纹故障的响应特性。结果表明:3维叶尖间隙特征参量对高压涡轮叶片尾缘裂纹的故障特征信息有良好的反映效果。
In order to effectively overcome the limited ability of traditional tip clearances to transmit information in the health monitoring of aero-engine turbine disk, the 3-dimensional characteristics of turbine blade tip during aero-engine operation are fully considered. Tip tip axial deflection angle and the circumferential deflection angle of the turbine tip three-dimensional tip clearance concept, and the three-dimensional tip clearance characteristic parameters as a blade fault signal carrier, by finite element analysis of the three-dimensional tip clearance Response of Characteristic Parameters to Typical Crack Fault in High Pressure Turbine Blade. The results show that the characteristic parameters of 3-dimensional tip clearance have a good effect on the fault characteristic information of the trailing edge crack of high-pressure turbine blades.