摘要
针对某型发动机高压压气机第6级静子叶片掉角故障,分别进行了断口分析、强度计算、振动模态试验和整机动应力测试,综合分析结果表明:第6级静子叶片掉角断口均属于高周疲劳;实测第9阶振型的最大相对振动应力区与故障叶片的裂纹起始位置吻合;第9阶自振频率对叶尖附近的弦长、厚度及尾缘R的尺寸微小变化很敏感。采取了增加频率限制、对涂"W"漆前的吹砂工艺进行细化以保护叶片的措施,使得该故障得以排除。
The fraeture analysis, strength calculation, vibration modal test and engine dynamic stress measurement were conducted for the sixth-stage high-pressure stator blade fracture failure of an aeroengine. The analysis results show thal the sixth-stage slator blade fracture failure is caused by high cycle fatigue. The measured biggest relative vibration stress region of the ninth mode is correspond with initial position of tailured blade crack. The nintil-slage natural frequency is very sensitive to the slight variations of chord length near tip, thickness and size of trailing edge R. The frequency restrict method and tile sand blasting technics refined before ＂w＂ painting are adopted to protect blade and eliminate failure.
出处
《航空发动机》
2012年第2期55-58,共4页
Aeroengine
