Creep life prediction for a nickel-based single crystal turbine blade

Li, Zhen; Zhou, Wen; Pei, Haiqing; Yue, Xiaowei; Pu, Wei; Ai, Changsheng; Yue, Zhufeng

doi:10.1080/15376494.2021.1972187

Cited by 18 publications

(6 citation statements)

References 38 publications

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“…Furthermore, the creep life is influenced by the dimensions, configuration, and dispersion of grain boundary carbide. Li et al [38] developed a constitutive model for a material using microcrystalline plasticity theory and a macroscopic phenomenological model of creep. They conducted simulations of the creep behavior of three-dimensional blades and proposed a technique for determining the creep life of turbine blades using the skeleton point stress method, as depicted in Figure 5.…”

Section: Review On Creep Of Aircraft Componentsmentioning

confidence: 99%

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Review on Creep Phenomenon and Its Model in Aircraft Engines

Yuan,

Chenglong,

Yongchao

et al. 2023

International Journal of Aerospace Engineering

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The aircraft is subjected to high-temperature and high-pressure conditions during flight, which renders it susceptible to the occurrence of creep phenomenon. Several academics have conducted extensive research on this issue. This research paper provides a comprehensive overview of the existing literature on creep phenomena in aircraft engines. First, several classical creep calculation models are enumerated and categorized as creep life calculation, creep-fatigue life calculation, and creep deformation calculation. Studies on creep phenomena are conducted in various components of aircraft engines, such as the engine’s turbine blades, turbine disks, and combustion chambers. The creep behavior of turbine blades in aircraft engines has been extensively researched. Furthermore, the protective measures aimed at mitigating creep are presented. Materials with high creep resistance can be used, and alternative fuels could be implemented. This paper provides an in-depth analysis of the advantages of creep in aircraft, presented in a favorable perspective. Finally, the prospective future research direction is discussed.

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Section: Review On Creep Of Aircraft Componentsmentioning

confidence: 99%

“…Creep life calculation by constitutive equation [56], [58], [60], and [70] Creep life calculation [29], [31], [32], [34], [36], [38], [48], [49], and [71] Creep-fatigue life [23], [25], [39], [50], [41], [42], [46], [47] and [54] Figure 15: Appearance of TBC sample after cyclic heating test [74].…”

Section: Calculation Object Literaturesmentioning

confidence: 99%

Review on Creep Phenomenon and Its Model in Aircraft Engines

Yuan,

Chenglong,

Yongchao

et al. 2023

International Journal of Aerospace Engineering

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“…The blade's useful life under low-cycle fatigue was estimated based on the fatigue analysis results. Li et al [7] analyzed the creep performance through the fluid-structure-interaction simulation of a three-dimensional (3D) blade, and the creep life prediction method for a single crystal blade was proposed based on the parameters at the skeletal points. Moreover, some researchers applied a statistical method for considering the uncertainties of the blade life predication.…”

Section: Introductionmentioning

confidence: 99%

Remaining Useful Life Prediction Method for High Temperature Blades of Gas Turbines Based on 3D Reconstruction and Machine Learning Techniques

Xiao,

Chen,

Zhang

et al. 2023

Applied Sciences

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Turbine blades are crucial components exposed to harsh conditions, such as high temperatures, high pressures, and high rotational speeds. It is of great significance to accurately predict the life of blades for reducing maintenance cost and improving the reliability of gas turbine systems. A rapid and accurate blade life assessment method holds significant importance in the maintenance plan of gas turbine engines. In this paper, a novel on-line remaining useful life (RUL) prediction method for high-temperature blades is proposed based on 3D reconstruction technology and data-driven surrogate mode. Firstly, the 3D reconstruction technology was employed to establish the geometric model of real turbine blades, and the fluid–thermal–solid analysis under actual operational conditions was carried out in ANSYS software. Six checkpoints were selected to estimate the RUL according to the stress–strain distribution of the blade surface. The maximum equivalent stress was 1481.51 MPa and the highest temperature was 1393.42 K. Moreover, the fatigue-creep lifetime was calculated according to the parameters of the selected checkpoints. The RUL error between the simulation model and commercial software (Control and Engine Health Management (CEHM)) was less than 0.986%. Secondly, different data-driven surrogate models (BP, DNN, and LSTM algorithms) were developed according to the results from numerical simulation. The maximum relative errors of BP, DNN, and LSTM models were 0.030%, 0.019%, and 0.014%. LSTM demonstrated the best performance in predicting the RUL of turbine blades with time-series characteristics. Finally, the LSTM model was utilized for predicting the RUL within a gas turbine real operational process that involved five start–stop cycles.

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“…This point is referred to as a skeletal node. Li et al 12 defined the combination of Mises stress and maximum principal stress at skeletal point as effective stress, which is used to predict the creep life of turbine blades. Wen et al 13 further refined the skeletal point position by considering the geometric shape of the structure.…”

Section: Introductionmentioning

confidence: 99%

Creep life prediction of Ni‐based single‐crystal superalloy plate with film‐cooling holes using a modified critical distance method based on the improved weight function

Wang,

Wen,

et al. 2023

Fatigue Fract Eng Mat Struct

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This paper proposed a new weight function modified critical distance method to predict the creep life of Ni‐based single‐crystal superalloy plate with film‐cooling holes through experimental and numerical research. The creep test and numerical simulation results both indicated that cracks originated around the hole, and the location of the maximum Mises stress point around the hole was consistent with the crack initiation point shown in the test results. Considering the stress gradient in the thickness direction, a critical fracture surface was defined, and the stress distribution at the critical fracture surface was defined using polynomials. An improved stress gradient function and weight function were introduced to calculate the effective stress at the critical fracture surface. The effective stress was used to predict the creep life of the plate with film‐cooling holes. Compared with the experimental results, the errors were all within the dispersion band of 1.5 times, indicating good prediction results.

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Creep life prediction for a nickel-based single crystal turbine blade

Cited by 18 publications

References 38 publications

Review on Creep Phenomenon and Its Model in Aircraft Engines

Review on Creep Phenomenon and Its Model in Aircraft Engines

Remaining Useful Life Prediction Method for High Temperature Blades of Gas Turbines Based on 3D Reconstruction and Machine Learning Techniques

Creep life prediction of Ni‐based single‐crystal superalloy plate with film‐cooling holes using a modified critical distance method based on the improved weight function

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