Blisk fatigue blade failure verification#
Blisk fatigue blade failure crack#

It was recommended that the casting parameters be controlled so that the columnar grains are oriented parallel to the principal stress axis of the blade. Coupled with this, the high operating temperatures were responsible for the failure of the blade by stress rupture. Microstructural studies revealed that the columnar grains at the blade root airfoil region were oriented unfavorably leading to poor stress rupture property in the transverse direction. A systematic analysis was carried out to ascertain the cause for stress rupture.

Blisk fatigue blade failure crack#

Visual inspection, micro and macro fractography, and metallography of the failed blades indicated that the failure was caused by stress rupture at the trailing edge followed by fatigue crack propagation. The integrally bladed disk was made of Mar-M-247 alloy, cast and hipped. Anal.TL DR: In this article, it was found that columnar grains at the blade root airfoil region were oriented unfavorably leading to poor stress rupture property in the transverse direction.Ībstract: Cracks were observed at the trailing edge of the blades of a turbine rotor blisk of a gas turbine engine during inspection following an endurance test.

Liu, Y.X., Cong, P.H., Wu, Y.W., Li, J.L., Wang, X.P.: Failure analysis and design optimization of shrouded fan blade. Tulsidas, D., Shantharaja, M., Bharath, V.G.: Life prediction of a steam turbine blade using low cycle fatigue analysis.

Blisk fatigue blade failure verification#

Wang, J., Zhao, F.T., Sha, Y.D., Gu, S.: Fatigue life research and experimental verification of superalloy thin-walled structures subjected to thermal-acoustic loads. Wan, J.Y., Zho, B.Z.: Elastic-plastic disk burst criteria establishment and variable thickness disk burst rotational speed prediction. Kuang, C.Y., Liu, Y.F.: Design of simulated specimen for low-cycle fatigue of aircraft engine titanium alloy disk. Zhu, Z.Y.: Research on the influence of prestress treatment on the disk fatigue life. Zheng, Y., Han, X.Q., Shao, J., Deng, W.J.: Titanium alloy three layers hollow component-like specimen design and high cycle fatigue test. Yang, X.Y., Dong, L.W., Geng, Z.X., Liu, X.L., Zhao, F.X.: Design and experimentation of simulation specimen for aero-engine compressor disk slot used in low cycle fatigue test. Li, D., Wang, Y.R., Liao, L.F., Wang, J.G., Wei, F.F.: Investigation of high and low cycle fatigue experiment for a curved dovetail assembly. Zheng, X.M., Sun, Y.T., Yang, X.Y., Xiao, X.H., Liao, X.J.: Design of low cycle fatigue simulating specimen for bolt holes of a turbofan engine high pressure turbine. Liu, T.Y., Geng, R., Zhang, J.F.: Design of simulated specimen for low-cycle fatigue of turbine engine disk. Gan, L.P., Huang, G.Z., Zhu, S.P., et al.: Fatigue reliability analysis of turbine disk alloy using saddlepoint approximation. Liu, C.L.: Reliability analysis for an aero-engine turbine disk under low cycle fatigue condition. The simulating specimen approach proves to be a reliable and accurate way to validate the cycle life of the engine critical components. Results comparisons show that the LCF life of the designed simulating specimen is approximate 153339 cycles, which is content with the calculation. Then, by optimizing the three critical parameters with regard to the stress gradient of the specimen, the optimum simulating specimen were confirmed and tested in the thermo-mechanical fatigue test rig. The predicted cycle life of the fan blisk is about 42 cycles using the semi-elliptical crack and the 1/4 surface corner cracks. Meanwhile, the crack propagation simulation was carried out to figure out the propagation cycle life of the critical locations. Afterwards, the LCF life of the blisk was calculated according to Mason-coffin equation and the total damage methods with the predicted maximum allowable LCF life reaching 158352 cycles. The finite element analysis was performed to confirm the constraining locations of the fan blisk. This paper aims at design several simulating specimen to simulate the working condition and stress distribution of a high-loaded fan blisk. The development of blisk structure has made the low cycle fatigue (LCF) life test more expensive for the critical components.