Creep-life prediction of service-exposed turbine blades

Marahleh, G.; Kheder, A.R.I.; Hamad, H. F.

doi:10.1007/s11003-006-0103-8

Cited by 34 publications

(21 citation statements)

References 2 publications

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“…Figure 3 shows the Sherby-Dorn and Larson-Miller parameter diagrams for Rene 80 superalloy. It is worth noting that the Larson-Miller method is a reliable technique for life prediction as long as the alloy microstructure is stable during prolonged exposure at high temperature (Koul and Castilo 1988;Marahleh et al 2006). The method of Manson-Succop is based on the parallelism of the iso-stress lines, with same slope B, in a graph log(tr) versus T , in the following way (Bueno and Sordi 2008):…”

Section: Iso-stress Methodsmentioning

confidence: 99%

Life prediction of a Ni-base superalloy

Aghaie-Khafri

Noori

2011

Bull Mater Sci

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Section: Iso-stress Methodsmentioning

confidence: 99%

Life prediction of a Ni-base superalloy

Aghaie-Khafri

Noori

2011

Bull Mater Sci

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“…Several methods of assessing the creep life consumption of the creep-critical components, i.e. turbine blades of gas turbine engines, have been published [1][2][3][4] but the accuracy of the methods is of concern to both the manufacturers and the operators alike. Even the more elaborate finite element procedures for the analysis of creep life of engine components do not always give satisfactory results [5].…”

Section: Introductionmentioning

confidence: 99%

Creep-Life Usage Analysis and Tracking for Industrial Gas Turbines

Saturday

Ogiriki

et al. 2017

Journal of Propulsion and Power

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Creep life usage analysis and tracking of first stage turbine rotor blades of an aero-derivative industrial gas turbine engine is investigated in this study. An engine performance model is created while blade thermal and stress models are developed for the calculation of the blade material temperatures and stresses at different sections of the blade. A creep life model is developed based on the Larson-Miller Parameter method by taking inputs from the thermal and stress models. An integrated creep life estimation system is developed by bringing together the engine performance model, the blade thermal and stress models, the creep life model and a data acquisition and pre-processing model. Relative creep life consumption analysis using new concepts developed in this research is introduced for the analysis of creep life consumption of the gas turbine engine operating for a period of time; these concepts include Equivalent Creep Life (ECL) and Equivalent Creep Factor (ECF). The developed algorithms have been applied to the creep life tracking of an aero derivative gas turbine engine using its field test data. The results show that it is able to provide a quick evaluation and tracking of engine creep life consumption and provide very useful information for gas turbine operators to support their operation optimization and creep life consumption monitoring.

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“…Abu et al provided a life assessment tool for aero jet engine blades by integrating suitable models and software with the Neu/Sehitoglu damage model [31]. Marahleh et al predicted the operating life of service-exposed blades used in industrial gas turbines [32]. Chen et al proposed a power-exponent function model for the life prediction of turbine blades under creep-fatigue interaction [33,34].…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Creep Damage and Life Prediction of Superalloy Turbine Blade

Liu

2015

Mathematical Problems in Engineering

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Creep caused failure is an important failure mode of the turbine blade. A numerical approach of life assessment of the superalloy turbine blade is proposed in the present paper based on the Lemaitre-Chaboche creep damage model. Material damage is introduced into each element based on the ANSYS APDL function, and the creep damage effect is considered through the modification of Young’s modulus. At last, the strength life and stiffness life of the blade can be obtained through the maximum damage and maximum creep strain criterion, respectively. The present method can not only consider the effect of creep damage, but also give the time histories of the element stresses, damage, and creep strain. The above life prediction results based on the proposed method are compared with theθprojection method, and the results suggest that the present life prediction method of turbine blade is feasible and turbine blade’s life in the present study is determined by creep fracture rather than creep deformation.

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Creep-life prediction of service-exposed turbine blades

Cited by 34 publications

References 2 publications

Life prediction of a Ni-base superalloy

Life prediction of a Ni-base superalloy

Creep-Life Usage Analysis and Tracking for Industrial Gas Turbines

Numerical Simulation of Creep Damage and Life Prediction of Superalloy Turbine Blade

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