In order to study the crack damage propagation law of rotor blades under complex loads in the actual service of aero-engines

the crack propagation life curve of blades was constructed based on the operational data of aero-engine

and the crack propagation rate formula was established by fracture mechanics theory. Taking the high-pressure compressor blade as an example

the load model of the compressor blade structure was constructed by the fluid-solid coupling method. The Paris， Walker and Newman crack growth rate formulas were used to analyze the three-dimensional crack propagation in the tip region of the compressor blade. The simulation results show that the prediction results of the three crack propagation rate formulas are consistent with the crack propagation curve of the engine operation data in the early stage of crack propagation

which can better describe the crack propagation law of the blade. In the stage of stable crack propagation

the prediction results of Walker and Newman formulas are relatively dangerous

and the prediction results of Paris formula are in good agreement with each other

and can be mutually confirmed with the requirements of damage development control in the manufacturer's technical manual.