Abstract: To verify the feasibility and effectiveness of ultrasonic infrared thermal imaging detection method for detecting micro crack defects with different distribution types on the surface of aviation engine turbine blades. A combination of theoretical analysis and experimental methods was used by analyzing the principle of ultrasonic infrared thermal imaging, a detection system for ultrasonic infrared thermal imaging was established. Several known crack types of turbine blades were tested using ultrasonic infrared thermal imaging. Based on the experimental results, the effectiveness of this method and the impact of crack distribution on the detection results were analyzed. The results indicated that this method can quickly determine whether there were defects in the blades. For blades with independent crack distribution, this method can accurately detect the size and location of cracks, while for blades with dispersed crack distribution, although this method can quickly detect the crack distribution area, it was difficult to quantitatively analyze the number of cracks.