<p>Fatigue crack, acted as one of the most common failure modes in aero-engine turbine blade, possesses such features as extremely strong concealment and progressive destruction and the investigation on fatigue crack detection has attracted most intention around the world. Thus, this work focuses on the use of ultrasonic infrared thermography for the detection on fatigue crack of turbine blade in aero-engine. To this goal, the detection mechanism regarding to ultrasonic infrared thermography is firstly analyzed, followed by the establishment on finite element model of a component within crack defect. On this basis, numerical simulation on heat generation around crack is calculated and the obtained results show that the heat generation only occurs around crack under the excitation of power ultrasonic and heat generation in the middle of crack is greater than that at the tip of crack. Finally, the detection experiment on aero-engine turbine blade within fatigue crack is conducted using ultrasonic infrared thermography and the crack parameter is quantitatively identified using temperature calibration method. The obtained results show that fatigue crack at the root of the blade can be effectively detected using ultrasonic infrared thermography and the quantitative identification error on the crack parameter is less than 15%. This work proves that the ultrasonic infrared thermography can be acted as an effective alternative method for the detection on fatigue crack in aero-engine turbine blade, with some certain engineering guidance significance and application prospects.</p>