The invention discloses an aero-engine turbine blade reliability evaluation method based on fracture mechanics. The method comprises the following steps: S1, establishing a simplified model of a bladesection by taking a turbine blade as a research object, calculating a stress intensity factor of the turbine blade containing an initial I-type crack at a blade root by applying a finite element method, substituting the stress intensity factor into a shape factor calculation formula, and determining a shape factor parameter; S2, establishing a turbine blade reliability model based on the generalized stress intensity interference model; and S3, establishing a probability density function of load and fracture toughness, establishing a probability life model and a reliability model for the bladein combination with a Paris formula, and solving the model to obtain the change condition of the reliability of the turbine blade along with the life. According to the method, initial defects existing in the blade are considered, on the basis of the initial defects, the crack propagation life of the I-shaped cracks on the surface of the blade under the cyclic load is established, and life prediction and reliability evaluation of the blade can be more accurate.