In this work, laser shock peening (LSP) induced spalling on aero-engine blades was studied. Multitimes LSP–induced spalling behavior was investigated using variable-thickness blade specimens (11° leaf surface angle), which were designed according to a real aircraft engine TC17 titanium alloy compressor blade. Further, the influence of specimen thickness and spot shape on the initiation site of spalling was explored using different thickness plate specimens. Results show that concave deformation was generated on the peened surface and macroscopic distortion was observed on the variable-thickness TC17 titanium alloy blade specimens after peening with 25 J, 4 mm square spot. Spalling and local peeling was not detected until peened 6 times and 8 times, respectively. Furthermore, analysis of the plate specimen that LSP–induced spalling is positively correlated with specimen thickness. The thicker the specimen is, the higher peening-times threshold for initiating spalling. Besides, spalling is not significantly related to the shape of the laser spot. Both circular and square spots can induce spalling, which is more easily generated in the softening region where Cr and Sn are enriched. LSP-induced spalling is not only related to the transmission characteristics of the shock waves but may also be related to material factors such as element segregation, and enrichment.