Experimental investigation of fatigue crack growth behavior of GH2036 under combined high and low cycle fatigue

Hu, Dianyin; Meng, Fanchao; Liu, Huawei; Song, Jun; Wang, Rongqiao

doi:10.1016/j.ijfatigue.2015.10.027

Cited by 62 publications

(40 citation statements)

References 18 publications

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“…All these concepts ensure that the blades are tightly fitted on the disc through considering the effect of finishing on the blade strength and life [ 4 , 5 , 6 ]. In particular, the structural integrity of a turbine blade can be threatened by two or more damage mechanisms: (a) fatigue, including thermal fatigue, multiaxial fatigue (high cycle fatigue (HCF)/low cycle fatigue (LCF)); (b) creep; (c) corrosion; and (d) foreign object damage and oxidation [ 7 , 8 , 9 , 10 , 11 , 12 , 13 , 14 , 15 ]. It is worth noting that fatigue strength of a turbine blade is often greatly reduced during the engine’s operation, even giving rise to its premature failure [ 16 , 17 , 18 , 19 , 20 ].…”

Section: Introductionmentioning

confidence: 99%

A Combined High and Low Cycle Fatigue Model for Life Prediction of Turbine Blades

Zhu

Yue

et al. 2017

Materials

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Combined high and low cycle fatigue (CCF) generally induces the failure of aircraft gas turbine attachments. Based on the aero-engine load spectrum, accurate assessment of fatigue damage due to the interaction of high cycle fatigue (HCF) resulting from high frequency vibrations and low cycle fatigue (LCF) from ground-air-ground engine cycles is of critical importance for ensuring structural integrity of engine components, like turbine blades. In this paper, the influence of combined damage accumulation on the expected CCF life are investigated for turbine blades. The CCF behavior of a turbine blade is usually studied by testing with four load-controlled parameters, including high cycle stress amplitude and frequency, and low cycle stress amplitude and frequency. According to this, a new damage accumulation model is proposed based on Miner’s rule to consider the coupled damage due to HCF-LCF interaction by introducing the four load parameters. Five experimental datasets of turbine blade alloys and turbine blades were introduced for model validation and comparison between the proposed Miner, Manson-Halford, and Trufyakov-Kovalchuk models. Results show that the proposed model provides more accurate predictions than others with lower mean and standard deviation values of model prediction errors.

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Section: Introductionmentioning

confidence: 99%

A Combined High and Low Cycle Fatigue Model for Life Prediction of Turbine Blades

Zhu

Yue

et al. 2017

Materials

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“…Hot engine section components such as turbine discs and blades are often subjected to complex multiaxial cyclic loads, and their life evaluation is of great importance for ensuring the reliability and structural integrity of aero engines [ 1 , 2 , 3 , 4 ]. In particular, one or more of the following failure mechanisms threaten the integrity of these components: (a) multiaxial fatigue; (b) creep; (c) high temperature corrosion [ 5 , 6 , 7 , 8 , 9 , 10 , 11 , 12 ]. Multiaxial fatigue failure is one of the main failure modes of these components and has been widely studied.…”

Section: Introductionmentioning

confidence: 99%

Multiaxial Fatigue Damage Parameter and Life Prediction without Any Additional Material Constants

Zhu

Liu

et al. 2017

Materials

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Based on the critical plane approach, a simple and efficient multiaxial fatigue damage parameter with no additional material constants is proposed for life prediction under uniaxial/multiaxial proportional and/or non-proportional loadings for titanium alloy TC4 and nickel-based superalloy GH4169. Moreover, two modified Ince-Glinka fatigue damage parameters are put forward and evaluated under different load paths. Results show that the generalized strain amplitude model provides less accurate life predictions in the high cycle life regime and is better for life prediction in the low cycle life regime; however, the generalized strain energy model is relatively better for high cycle life prediction and is conservative for low cycle life prediction under multiaxial loadings. In addition, the Fatemi–Socie model is introduced for model comparison and its additional material parameter k is found to not be a constant and its usage is discussed. Finally, model comparison and prediction error analysis are used to illustrate the superiority of the proposed damage parameter in multiaxial fatigue life prediction of the two aviation alloys under various loadings.

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“…Nevertheless, the investigation of the effect of a long dwell time (for instance from several to dozens of minutes corresponding to the service dwell time of a turbine disc) on the creep-fatigue behavior of the turbine disc of superalloy GH720Li has not been performed. Secondly, some mechanical properties (fatigue crack growth and creep-fatigue) of the test pieces cut from the actual turbine disc are different from the plain specimens due to the different microstructure induced by the manufacturing process [19,20]. Consequently, creep-fatigue experimental data of the specimens from an actual turbine disc should be used to predict "turbine disc component" lifetime.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of fatigue crack growth behavior of GH2036 under combined high and low cycle fatigue

Cited by 62 publications

References 18 publications

A Combined High and Low Cycle Fatigue Model for Life Prediction of Turbine Blades

A Combined High and Low Cycle Fatigue Model for Life Prediction of Turbine Blades

Multiaxial Fatigue Damage Parameter and Life Prediction without Any Additional Material Constants

Creep-fatigue behavior of turbine disc of superalloy GH720Li at 650 °C and probabilistic creep-fatigue modeling

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