Fatigue crack propagation analysis in an aero-engine turbine disc using computational methods and spin test

Huang, Xiannian; Chen, Chuanyong; Hu, Xuan; Guo, Xiaojun; Shan, Xiaoming; Hong, Weirong

doi:10.1016/j.tafmec.2022.103745

Cited by 13 publications

(6 citation statements)

References 32 publications

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“…Specifically, the damage caused by n 1 cycle under fatigue loading σ 1 can be converted to the initial damage corresponding n 12 cycle under fatigue loading σ 2 by isodamage theory. The equivalent cycle number n 12 and total life can be calculated by Equations ( 4) and (6).…”

Section: Nonlinear Damage Accumulation Theorymentioning

confidence: 99%

“…Turbine blades generally worked under harsh conditions exposed to high temperature and variable loading, severely limiting the life and safety assessment of aero engines. [1][2][3][4][5][6][7] The damage accumulation theory was important for the residual strength assessment and life prediction. [8][9][10] It was proved that the damage accumulation of low cycle fatigue (LCF) was significantly affected by loading history of variable amplitude loading.…”

Section: Introductionmentioning

confidence: 99%

“…Turbine blades generally worked under harsh conditions exposed to high temperature and variable loading, severely limiting the life and safety assessment of aero engines 1–7 . The damage accumulation theory was important for the residual strength assessment and life prediction 8–10 .…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Nonlinear fatigue life prediction model based on isodamage curve considering two‐block loading

Yun,

Shi,

Fan

et al. 2024

Fatigue Fract Eng Mat Struct

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A non‐linear life prediction model considering the loading history is proposed based on isodamage curve. The stress‐controlled low‐high block loading of low cycle fatigue (LCF) at high temperature, with various previous cycles, was performed on a nickel‐based superalloy. The damage evolvement of the prior loading was revealed using scanning electron microscopy under the low‐high block loading, especially the failure mechanism of coaxing effect. In addition, load history correlation factor was introduced to describe the influence of prior cycle. Based on the Ni‐based superalloy, the life prediction model of two‐step loading, including the low‐high block (LH) and high‐low block loading (HL), was proposed, agreeing well with the experimental results for different metals. Compared with other life prediction models, the proposed model demonstrated the higher prediction accuracy and wider applicability.

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Section: Nonlinear Damage Accumulation Theorymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Nonlinear fatigue life prediction model based on isodamage curve considering two‐block loading

Yun,

Shi,

Fan

et al. 2024

Fatigue Fract Eng Mat Struct

View full text Add to dashboard Cite

show abstract

“…In [28], the crack direction points to the center of the circle, but the crack studied in this paper has an invasion angle, the corrected crack opening displacement is…”

Section: Btt Displacement Measurement Signal Simulationmentioning

confidence: 99%

“…In summary, for the crack monitoring problem of the bladed disk structure, most scholars have studied the blade crack monitoring without studying the disk crack monitoring; for the study of disc cracks, scholars have focused on the study of crack propagation mechanism without studying crack monitoring [28,29]. In this paper, the classical BTT principle is first analyzed to derive the conversion relationship between BTT's time signal and the blade tip's circumferential displacement.…”

Section: Introductionmentioning

confidence: 99%

Characterization of crack on the outer edge of the disk based on blade tip timing technology

Zhang,

Guo,

et al. 2023

Meas. Sci. Technol.

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The structural performance failure of the rotating blade disk with disk crack is one of the major causes of aero-engine failures and even serious accidents. The blade tip timing (BTT) is a non-contact measurement technology that obtains the rotor operation status by detecting the blade. This paper has proposed a crack characterization method for the disk's outer edge based on the BTT technique. In this process, the influence of crack parameters ( length and position ) on the circumferential displacement signal of the blade tip is determined by using the crack tip displacement, the relative position of the blade tip motion during the rotation of the outer edge crack-containing disk and the actual blade tip measuring points, and the critical value of the crack parameters affecting the blade tip offset is analyzed. The finite element simulation results verify the effectiveness and accuracy of the proposed method. The Study of this article can provide a theoretical basis for the measurement of cracks on the disk's outer edge by the BTT technique, which is of great significance for the accurate identification of the operating condition of the rotating blade disk structure.

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Zone‐based failure risk assessment of fatigue crack growth caused by initial defects in powder turbine disc

Wang,

Kong,

Cao

et al. 2024

Quality & Reliability Eng

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In this research, A zone‐based failure risk assessment (FRA) method of fatigue crack growth (FCG) caused by initial defects in the FGH96 alloy turbine disc is developed. Firstly, the initial defects distribution in the FGH96 alloy turbine disc is calculated based on the defect data. Subsequently, a probabilistic short FCG life model is established, taking into account the dispersion in grain size. Meanwhile, a probabilistic long FCG life model is established, incorporating the life dispersion factor. To calculate the Stress Intensity Factor (SIF) at any position of the disc, the general weight function method and the rectangular plate model are established. Finally, the zoning process is established, enabling a FRA that considers the FCG due to initial defects. The results indicate that the number of cycles corresponding to a 0.13% failure probability of the turbine disc is 7150, and the percentage of failures in each zone is analyzed.

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Fatigue crack propagation analysis in an aero-engine turbine disc using computational methods and spin test

Cited by 13 publications

References 32 publications

Nonlinear fatigue life prediction model based on isodamage curve considering two‐block loading

Nonlinear fatigue life prediction model based on isodamage curve considering two‐block loading

Characterization of crack on the outer edge of the disk based on blade tip timing technology

Zone‐based failure risk assessment of fatigue crack growth caused by initial defects in powder turbine disc

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