| SUN Yu-bo,LEI Juan-juan.Research on Fatigue Crack Propagation and Remain Fatigue Life Predic-tion of Aero-engine Blade TC4 Titaniumalloy[J],45(9):207-213 |
| Research on Fatigue Crack Propagation and Remain Fatigue Life Predic-tion of Aero-engine Blade TC4 Titaniumalloy |
| Received:March 05, 2016 Revised:September 20, 2016 |
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| DOI：10.16490/j.cnki.issn.1001-3660.2016.09.031 |
| KeyWord:TC4 titanium alloy fatigue crack propagation remain fatigue life prediction |
| Author | Institution |
| SUN Yu-bo |
a.Tianjin Key Laboratory of Civil Aircraft Airworthiness and Maintenance, b.College of Science, Civil Aviation University of China, Tianjin , China |
| LEI Juan-juan |
b.College of Science, Civil Aviation University of China, Tianjin , China |
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| Abstract: |
| Objective To study vibration fatigue performance of TC4 titanium alloy and predict its service life. Methods The resonance fatigue test was used to analyze the change regularity of stress intensity factor at the crack tip and calculate the fatigue crack propagation rate under different stress levels. The model of remain fatigue life prediction was created. Results The stress intensity factor was an effective parameter to characterize the crack propagation rate and was related to crack lengths and stresses. The calculation results of fatigue crack propagation rate at the initial were in good agreement with fatigue test results at 274 MPa. When the initial crack length was 0.5 mm and the final crack length was 5 mm, the remain fatigue life was 36 577, 19 090 and 13 865 cycles at 274 MPa, 366 MPa and 422 MPa respectively. Conclusion Under the vibration conditions at -1 stress ratio, the crack propagation is accelerated with increase of stresses. If the initial crack length is longer, the crack propagation will be bigger under the same stress. The remain life of workpiece can be calculated by model in this paper. |
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