Corrosion crack's propagation analysis and fatigue life prediction of the cylinder of 6000HP hydraulic fracturing pump

Hu, Gang; Deng, Shan; Wang, Guorong; Wang, Mingcheng; Xie, Mei-Ying

doi:10.1016/j.engfailanal.2022.106652

Cited by 10 publications

(3 citation statements)

References 20 publications

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“…Therefore, this paper introduced a fatigue crack growth equation to simulate the length of continuous crack growth during the undetected period after crack initiation. Fatigue crack growth can generally be expressed by fatigue crack growth rate and stress intensity factor amplitude, and can be described quantitatively by Paris formula [14], as shown in equation (11). According to Paris crack growth rate formula and fatigue load spectrum of aircraft structure, the relationship between fatigue crack and flight time can be obtained.…”

Section: Fatigue Crack Growth Ratementioning

confidence: 99%

“…In addition, for the safety requirements of the aircraft structures, it is sometimes required to give the risk probability index per flight hour. According to the average service time tm of 24 aircrafts in the fleet, the risk probability of structural damage of the fleet per flight hour can be calculated from equation (14). The calculated risk probability of aircraft structural damage under different maintenance intervals T is shown in Fig.…”

Section: Structural Damage Risk Probabilitymentioning

confidence: 99%

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A risk assessment method of aircraft structure damage maintenance interval Indexed by: considering fatigue crack growth and detection rate

Zhang¹,

Mao²,

Liu³

et al. 2023

Eksploatacja i Niezawodność – Maintenance and Reliability

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The accurate assessment of aircraft structure damage risk is the premise of establishing reasonable, economic and reliable maintenance intervals. While many studies have proposed damage risk assessment methods for aircraft structures, these methods lack the quantification of risk. This paper proposed a risk assessment method of aircraft structure damage maintenance interval considering fatigue crack growth rate and crack detection rate. The damage process of aircraft structure was simulated by Monte Carlo simulation to realize the quantitative assessment of aircraft structure damage risk and maintenance interval. Taking an aircraft fleet as an example, the damage risk of its wing structure was simulated and analyzed. The results show that if the risk is controlled within a reasonable range, the maintenance interval should be shortened to 16 flight hours. At the same time, through the analysis of the risk classification standard and the crack detection rate, the quantitative evaluation of the risk classification standard was realized.

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Section: Fatigue Crack Growth Ratementioning

confidence: 99%

Section: Structural Damage Risk Probabilitymentioning

confidence: 99%

A risk assessment method of aircraft structure damage maintenance interval Indexed by: considering fatigue crack growth and detection rate

Zhang¹,

Mao²,

Liu³

et al. 2023

Eksploatacja i Niezawodność – Maintenance and Reliability

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show abstract

“…Cai et al [8] found that Cl − enrichment and local stress concentration lead to corrosion fatigue crack initiation of the Q690qE high-strength bridge steel. Hu et al [9] found that the crack growth rate of 17-4PH steel in a corrosive environment is 6.39 times that of air. Zhao et al [10] found that corrosion fatigue crack initiation of E690 steel in simulated seawater is affected by the peak stress level.…”

Section: Introductionmentioning

confidence: 99%

The Initiation Characteristics of Corrosion Fatigue Crack in 18Ni (250) Steel

Pan,

Zhu,

Fang

2024

JMSE

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Maraging steel is the material of deep sea pressure equipment. The characteristics of corrosion fatigue crack initiation in 18Ni (250) were investigated by performing a tensile fatigue test under different loading conditions. The mechanism of corrosion fatigue crack initiation was analyzed considering the influence of welding. The results showed that the crack initiation life decreases with increasing load and increases with the stress ratio. In a corrosive seawater environment, crack initiation is affected by both mechanical damage and electrochemical corrosion. The proportion of the crack initiation life of the total sample life is approximately 71.45–99.55%, where the larger this proportion is, the smaller the fatigue zone is. Crack initiation and microcrack propagation in maraging steel correspond to the microfracture mechanism of dimple fractures. The microfracture mechanism is strongly affected by the presence of a weld but weakly affected by the weld position. The results of this study provide a theoretical basis for predicting the corrosion fatigue life of deep-sea submersible pressure hulls.

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Effect of Casting Temperature on the Microstructure and Mechanical Properties of Cu-10Pb-10Sn/42CrMoS4 Bimetallic Hydraulic Cylinder Block

Qi,

Han,

Wang

et al. 2024

J. of Materi Eng and Perform

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Corrosion crack's propagation analysis and fatigue life prediction of the cylinder of 6000HP hydraulic fracturing pump

Cited by 10 publications

References 20 publications

A risk assessment method of aircraft structure damage maintenance interval Indexed by: considering fatigue crack growth and detection rate

A risk assessment method of aircraft structure damage maintenance interval Indexed by: considering fatigue crack growth and detection rate

The Initiation Characteristics of Corrosion Fatigue Crack in 18Ni (250) Steel

Effect of Casting Temperature on the Microstructure and Mechanical Properties of Cu-10Pb-10Sn/42CrMoS4 Bimetallic Hydraulic Cylinder Block

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