Qualitative Calculation of Fatigue Life for Turbine Rotor Blade

Abstract:

Fatigue fracture occurred on one blade when a certain aero-engine was under test run. The fracture is observed to measure the crack length and the average distance between fatigue striations. The Paris formula is employed to calculate the fatigue propagation life of the two main fatigue propagation regions observed on the fracture. The results show that the rate of crack propagation present a tendency of regular increase, and the fatigue propagation life takes a very small ratio of the total fatigue life of the blade.

• Periodical: Applied Mechanics and Materials (Volumes 477-478)
• Pages: 63-66
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.477-478.63
• Online since: December 2013
• Authors: Wei Fang Zhang, Qing Yun Tang*
• Keywords: Fatigue Fracture, Fatigue Life, Paris-Formula, Qualitative Calculation, Rotor Blade

References

[1] Lin J.W., Zhang J.H., and Yang S.: Chinese Journal of Aeronautics, Vol. 26, No. 3 (2013), pp.631-637.

[2] Cao H.H. and Huang J.J.: Gas Turbine Experiment and Research, Vol. 21, No. 1 (2008), pp.22-25. In Chinese.

[3] Qu S., Fu C.M., and Dong C. et al: Engineering Failure Analysis, Vol. 32 (2013), pp.292-303.

[4] Gao Y., and Wang Y.R.: Gas Turbine Experiment and Research, Vol. 18, No. 2 (2005), pp.23-26. In Chinese.

[5] Zhang W.F., Tao C.H., Xi N.S., Gao W., and Liu G.Y.: Material Engineering, No. 1 (2003), pp.38-41. In Chinese.