To improve the fatigue performance of aircraft rotor of TB6 titanium alloy, the effects of laser shock peening (LSP), shot peening (SP) and their combination processing methods on surface integrity and axial fatigue property of the titanium alloy are investigated. The surface topography, residual stress distribution and microstructure are characterized by white light interferometer, X-ray diffraction stress tester and scanning electron microscope. The axial fatigue life and limit are investigated by fatigue tester. Results show that compared with the grinding (GD) specimen under the same test conditions, the fatigue life of LSP specimens is improved by 32.2 times, while the fatigue lifes of SP and the combination processing specimens are both increased by at least 126.4 times. The combination processing method exhibits better improvement for fatigue limit than the SP method.

laser shock peening  /  shot peening  /  titanium  /  fatigue limit  /  surface integrity