Aero-engine turbine blade life assessment using the Neu/Sehitoglu damage model

Abu, Abdullahi O.; Eshati, S.; Laskaridis, Panagiotis; Singh, Riti

doi:10.1016/j.ijfatigue.2013.11.015

Cited by 37 publications

(12 citation statements)

References 9 publications

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“…this work is based on blade -usage based on lifing. Abdullahi (Abu O. Abdullahi et al, 2014) [7] gives a thorough insight on such methods. Prognosis on the other hand, is the process of analysing data, in order to acquire knowledge about a certain state that comes in force during the future.…”

Section: Literature Reviewmentioning

confidence: 99%

Comparative Study of a Powerplant Life Consumption Rate When Installed in Two Different Aircraft Variants

Templalexis¹,

Lionis²,

Christou³

2021

Aerospace

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The Hellenic Air Force (HAF) operates both EMB-145 and EMB-135 LR versions of Embraer aircraft, used in surveillance and civil missions respectively. These aircraft are equipped with the same version of Rolls Royce, AE 3007 turbofan engine. This study aims to quantify and compare the life consumption rate of this engine when installed in each of the two aircraft variants. Two typical missions, one for each variant, were constructed based on mission profile data dictated by the aircraft commanders. For each mission profile segment, corresponding engine data were matched out of the engine recordings archives held by the Hellenic Air Force. The life consumption rate was based on the Low Cycle Fatigue (LCF) and creep cumulative detrimental effect on the rotor blades of the 1st High-Pressure Turbine stage. For the LCF, the rainflow method was used to determine the respective loading cycles, whereas the Larson - Miller parameter method was used to determine the consumed life fractions due to creep. The main conclusion of the study was that the engine when installed in the EMB-145 military variant, is much more loaded. Despite the fact absolute life consumption values could hide a great level of uncertainty, the comparative outcomes wherein errors are, to a certain extent, cancelled out, could be used as a rule of thumb when monitoring engine life consumption rates.

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Section: Literature Reviewmentioning

confidence: 99%

Comparative Study of a Powerplant Life Consumption Rate When Installed in Two Different Aircraft Variants

Templalexis¹,

Lionis²,

Christou³

2021

Aerospace

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“…For this study, only the effect of HP turbine blade creep strain on HP turbine health parameters was analysed for inclusion in the EOT equation. Previous studies investigating the effect of operating conditions of gas turbine creep damage have considered them as separate from component degradation mechanisms (7,8,36) . However, this failure mechanism which is initiated at the micro-structural level, has a significant impact on the physical geometry and tip surface quality of the blades, which affects the critical gas path flow area and stage efficiency.…”

Section: Creep-strain Mechanismmentioning

confidence: 99%

Assessment of degradation equivalent operating time for aircraft gas turbine engines

Alozie

Diakostefanis

et al. 2020

Aeronaut. j.

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This paper presents a novel method for quantifying the effect of ambient, environmental and operating conditions on the progression of degradation in aircraft gas turbines based on the measured engine and environmental parameters. The proposed equivalent operating time (EOT) model considers the degradation modes of fouling, erosion, and blade-tip wear due to creep strain, and expresses the actual degradation rate over the engine clock time relative to a pre-defined reference condition. In this work, the effects of changing environmental and engine operating conditions on the EOT for the core engine booster compressor and the high-pressure turbine were assessed by performance simulation with an engine model. The application to a single and multiple flight scenarios showed that, compared to the actual engine clock time, the EOT provides a clear description of component degradation, prediction of remaining useful life, and sufficient margin for maintenance action to be planned and performed before functional failure.

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“…All three damages can operate under in-phase (IP) TMF loading, and the creep damage can be negligible under out-of-phase (OP) TMF loading. The model has been employed for the life prediction of the engineering components under TMF loading (Abu et al, 2014;Escola´n et al, 2017;Kang et al, 2007;Minichmayr et al, 2008). Furthermore, the fracture mechanics parameters, including cyclic stress intensity factor (Kraemer et al, 2017), the cyclic Jintegral (Christ et al, 2003;Esmaeilzadeh et al, 2017), and the cyclic crack-tip opening displacement (Seifert and Riedel, 2010;, were also investigated to estimate the crack growth rate under TMF loading.…”

Section: Introductionmentioning

confidence: 99%

Fatigue–oxidation–creep damage model under axial-torsional thermo-mechanical loading

Shang

Cui

et al. 2019

International Journal of Damage Mechanics

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A fatigue–oxidation–creep damage model that can take into account the effect of multiaxial cyclic feature on the damage mechanism is proposed under axial-torsional thermo-mechanical fatigue loading. In the proposed model, the effects of non-proportional additional hardening on fatigue, oxidation, and creep damages are considered, and the variation of oxidation damage under different high temperature loading conditions is also described. Moreover, the intergranular creep damage needs to be equivalent to the transgranular damage before accumulating with the fatigue and oxidation damages. The fatigue, oxidation, and creep damages can be expressed as the fractions of fatigue life, critical crack length, and creep rupture time, respectively, which allows the linear accumulation of different types of damages on the basis of life fraction rule. In addition, the proposed model is validated by various fatigue experimental results, including uniaxial thermo-mechanical fatigue, axial-torsional thermo-mechanical fatigue, and isothermal axial-torsional fatigue under proportional and non-proportional loadings. The results showed that the errors are within a factor of 2.

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Aero-engine turbine blade life assessment using the Neu/Sehitoglu damage model

Cited by 37 publications

References 9 publications

Comparative Study of a Powerplant Life Consumption Rate When Installed in Two Different Aircraft Variants

Comparative Study of a Powerplant Life Consumption Rate When Installed in Two Different Aircraft Variants

Assessment of degradation equivalent operating time for aircraft gas turbine engines

Fatigue–oxidation–creep damage model under axial-torsional thermo-mechanical loading

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