This study presents the metallurgical analysis results of fracture failure occurred on the turbine wheel of Jet Fuel Starter (JFS) used on F16 Military Aircraft. A lot of cracks, main material loss, metal deposit and pitting were observed on turbine wheel. When the investigable turbine wheel blade surface was examined, the cracks on blade surfaces were started from multiple points assisted by thermal fatigue. Then, the repeated loads enhanced the cracks from blade edge to center. Finally, the residual cross-section surface was completely broken off because the residual cross-section surface did not endure the overload effects overcoming on it. The imbalance malfunction took place in JFS after the turbine wheel blades were broken. In this situation, the compressor wheel rubbed to the casing, than some damages occurred on the casing surface and compressor wheel blades as a result of rubbing, and the JFS rear bearing disintegrated.

本研究介绍了 F16 军用飞机上使用的喷气燃料启动器 (JFS) 涡轮叶轮发生断裂失效的冶金分析结果。在涡轮叶轮上观察到大量裂纹、主要材料损失、金属沉积和点蚀。在检查可研究的涡轮叶轮叶片表面时，叶片表面的裂纹是在热疲劳的辅助下从多个点开始的。然后，重复载荷增强了从叶片边缘到中心的裂纹。最后，由于残余横截面没有承受克服其上的过载效应，残余横截面被完全折断。涡轮叶片损坏后，JFS 发生了不平衡故障。在这种情况下，压缩机叶轮摩擦到机壳，