The requirement of laser peening of aeronautical turbine blades is introduced, and the relevant research results are described. The surface profile of laser peening with square spots is measured and compared with the case of common circle spots. TC17 titanium blades are treated by laser peening with overlapped square spots, and then the improvement of bend vibration fatigue properties is tested. The key problems of laser peening turbine engine integrally blade rotor (IBR) are researched. The application of laser peening IBR in China is introduced and prospected.