Reliability analysis for low cycle fatigue life of the aeronautical engine turbine disc structure under random environment

Liu, C.L.; Lu, Zhen; Xu, Ying-Ying; Yue, Zhufeng

doi:10.1016/j.msea.2004.12.014

Cited by 51 publications

(36 citation statements)

References 10 publications

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“…Previous studies [28][29][30][31] reported fatigue lifetime always follows a log normal distribution. Meanwhile, test creep-fatigue lifetime shows different scattering (see Fig.…”

Section: Probabilistic Creep-fatigue Lifetime Assessmentmentioning

confidence: 99%

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

Shang

et al. 2016

Materials Science and Engineering: A

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“…Previous studies [28][29][30][31] reported fatigue lifetime always follows a log normal distribution. Meanwhile, test creep-fatigue lifetime shows different scattering (see Fig.…”

Section: Probabilistic Creep-fatigue Lifetime Assessmentmentioning

confidence: 99%

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

Shang

et al. 2016

Materials Science and Engineering: A

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“…The fatigue life distribution function should be assumed to follow a certain distribution type in the first place, then estimated the distribution pattern parameters by collecting experimental data. Zhao [2] and Lee [3] and other researchers had researched fatigue reliability, Liu [4] had generalized this reliability analysis method to engineering application. But sample size and distribution pattern have great influence on deducing of the fatigue life distribution [5], meanwhile create uncertainty on reliability analysis.…”

Section: Introductionmentioning

confidence: 99%

Notice of Retraction Uncertainty analysis of turbine blade fatigue life distribution based on Bayesian inference

Luo

Zhang

et al. 2013

2013 International Conference on Quality, Reliability, Risk, Maintenance, and Safety Engineering (QR2MSE)

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This paper investigated the application of Bayes' theorem in life distribution. The uncertainty of the model itself was rarely cared about Bayesian theory. So probability distribution model uncertainty and structural parameter uncertainty was researched through Bayes' theorem. This paper developed the fatigue life distribution mode of turbine blade. Firstly, find the best model by quantification of fatigue life distribution model; then update the parameters of the model; finally, calculate Bayesian posterior probability by Markov Chain Monte Carlo Algorithm (MCMC) in OpenBUGS.

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“…About the reliable lifetime evaluation for engine components, researchers have presented several models [7][8][9][10][11][12][13]. For example, Shen [7] put forward a probability-based procedure to predict the reliability of gas turbine engine blades subjected to high cycle fatigue, which provides lifetime design guide lines for blades and an optimal maintenance strategy in management.…”

Section: Introductionmentioning

confidence: 99%

“…For example, Shen [7] put forward a probability-based procedure to predict the reliability of gas turbine engine blades subjected to high cycle fatigue, which provides lifetime design guide lines for blades and an optimal maintenance strategy in management. On the basis of the linear damage accumulation rule and the simulated probability density distributions of the stress and the strain, Yue et al [8] developed a reliability model for the low cycle fatigue life analysis of turbine disk structure, which considers the randomness in the life characteristic of the material. Salam et al [9] investigated the failure cause of one engine in fighter plane during flight, which resulted from the 2 nd stage fractured turbine blade.…”

Section: Introductionmentioning

confidence: 99%

Fatigue Life Estimation of an Aircaft Engine Under Different Load Spectrums

Huang

Gong

Zuo

et al. 2012

Int. J. Turbo Jet-Engines

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Aircraft engine components are subjected to variable amplitude load conditions usually they tend to experience fatigue damage. Many fatigue damage accumulation theories have been put forward to predict the fatigue lives of structure components. Under different load spectra, the aircraft engine has different working life. In this paper, based on the linear damage rule, the fatigue life of an aircraft engine was estimated by considering the load spectrum difference factor. According to one aircraft engine used for different load spectrums, the relationship between the load spectrum and the life is discussed. Moreover, the fatigue life of this engine used in A-type bomber is estimated based on the different load spectrum of the B-type bomber. A good agreement is found between the estimated results and real life data. Nomenclature s L stress level L n L corresponding numbers of load cycles at stress level L N L cycles to failure under the stress level L D fatigue damage S i corresponding load n i load cycles N i number of cycles R stress ratio X p peak load K t stress concentration factor a stress amplitude a0 stress amplitude when the mean value is 0 m mean stress m0 mean stress when the stress amplitude is 0 L f specified reliability coefficient V 2 high-pressure rotor speed S a symmetrical cyclic stress S a stress amplitude S m mean stress S b ultimate tensile strength

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Reliability analysis for low cycle fatigue life of the aeronautical engine turbine disc structure under random environment

Cited by 51 publications

References 10 publications

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

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

Notice of Retraction Uncertainty analysis of turbine blade fatigue life distribution based on Bayesian inference

Fatigue Life Estimation of an Aircaft Engine Under Different Load Spectrums

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