| 卜嘉利，高志坤，牛建坤，曹勇.航空发动机风扇静子叶片裂纹失效分析[J].航空发动机,2021,47(6):91-95 |
| 航空发动机风扇静子叶片裂纹失效分析 |
| Crack Failure Analysis of a Fan Stator Vane |
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| DOI： |
| 中文关键词: 风扇静子叶片 振动疲劳试验 疲劳裂纹 振动光饰 有限元分析 失效分析 航空发动机 |
| 英文关键词:fan stator vane vibration fatigue test fatigue crack vibration finishing finite element analysis failure analysis aero⁃engine |
| 基金项目:航空动力基础研究项目资助 |
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| 中文摘要: |
| 针对某型航空发动机风扇静子叶片前缘靠近上缘板部位在振动疲劳试验结束后发现的裂纹故障，运用荧光探伤检测、
断口宏微观分析、叶片表面划痕来历分析、源区表面检查、材质分析及有限元应力模拟分析等技术手段，对该裂纹的性质及萌生原
因进行细致分析。分析结果表明：故障风扇静子叶片裂纹的性质为高周疲劳，裂纹断口疲劳起源于叶片叶盆侧前缘靠近上缘板基
体表面划痕处，呈多源线性起始特征。疲劳源区距前缘距离约为2.3 mm，疲劳源区表面未见明显冶金缺陷，疲劳裂纹的萌生与叶
片表面划痕有关。建议严格控制振动光饰机中磨粒棱边的圆滑度，不应存有锋利棱角，避免在振动光饰时磨粒划伤叶片表面，降
低叶片表面完整性，在叶片划伤部位出现应力集中现象。 |
| 英文摘要: |
| The crack initiation was found at the leading edge of the fan stator vane，where was close to the upper edge plate， after the vibration fatigue test finished. The crack property and emergence were identified by fluoroscopy，fracture analysis，surface inspection，scratch analysis，chemical composition analysis，metallographic examination，hardness inspection and finite element analysis. The results show that the property of the crack is high cycle fatigue fracture，the fatigue of the crack fracture originates from the scratch on the front edge of the vane basin side close to the matrix surface of the upper edge plate，the fatigue source region showed multi-source linear initial characteristics. The distance between the fatigue source area and the leading edge is about 2mm，no obvious metallurgical defects are found on the surface of the fatigue source area，the initiation of the crack is related to the scratch of the vane surface. It is suggested that
the smoothness of the abrasive grinding edges in vibration finishing machine should avoid scratching the vane surface by abrasive particles during vibration finishing，reduce the integrity of the vane surface，and stress concentration occurs at the scratched part of vane. |
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