A Damage Evaluation Model of Turbine Blade for Gas Turbine

Wei, Tingting; Zhang, Huisheng; Ma, Shixi; Weng, Shilie

doi:10.1115/1.4036060

Cited by 17 publications

(10 citation statements)

References 18 publications

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“…Some studies have been focused on the evaluation of failure in gas turbine blades. Zhou et al [51] proposed a physical-based damage evaluation model for high temperature blades of gas turbines. The model can predict the thermodynamic performance, mechanical stress, and creep damage of the blades in gas turbines.…”

Section: Hot-end Blade Damage In Gas Generator Turbinementioning

confidence: 99%

Gas Path Fault and Degradation Modelling in Twin-Shaft Gas Turbines

2018

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In this study, an assessment of degradation and failure modes in the gas-path components of twin-shaft industrial gas turbines (IGTs) has been carried out through a model-based analysis. Measurements from twin-shaft IGTs operated in the field and denoting reduction in engine performance attributed to compressor fouling conditions, hot-end blade turbine damage, and failure in the variable stator guide vane (VSGV) mechanism of the compressor have been considered for the analysis. The measurements were compared with simulated data from a thermodynamic model constructed in a Simulink environment, which predicts the physical parameters (pressure and temperature) across the different stations of the IGT. The model predicts engine health parameters, e.g., component efficiencies and flow capacities, which are not available in the engine field data. The results show that it is possible to simulate the change in physical parameters across the IGT during degradation and failure in the components by varying component efficiencies and flow capacities during IGT simulation. The results also demonstrate that the model can predict the measured field data attributed to failure in the gas-path components of twin-shaft IGTs. The estimated health parameters during degradation or failure in the gas-path components can assist the development of health-index prognostic methods for operational engine performance prediction.

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Section: Hot-end Blade Damage In Gas Generator Turbinementioning

confidence: 99%

Gas Path Fault and Degradation Modelling in Twin-Shaft Gas Turbines

2018

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“…Such thresholds may be determined by the time between overhauls set by OEM or the maximum allowed component degradations. 6. Finally, the degradation mechanisms considered are limited to fouling and erosion arising from ingested particulate matter and turbine blade tip wear due to its residual inelastic creep strain.…”

Section: Methodology 21 Fundamental Assumptionsmentioning

confidence: 99%

“…For aero-engine life assessment, Zhou et al (6) presented a damage evaluation model for blade creep life calculation, Abdul Ghafir et al (7) used a creep factor parameter to express the relative severity of firing temperatures on life consumption whereas Eshati et al (8) and Hanumanthan et al (9) adopted the numerical computational approach to solving the same problem. Gotoh et al (10) proposed a method for evaluating gas turbine equivalent operating time for creep and thermo-mechanical fatigue loadings.…”

Section: Introductionmentioning

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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“…The mechanism can be acidic fluxing or basic fluxing, depending on high SO3 partial pressure or high Na2O activity in the melt, respectively. Type II (Low-Temperature Hot Corrosion) is observed in the temperature range of 650-800 o C. The reactions of Type II Hot Corrosion are activated by high SO3 partial pressure and the lower-melting-point eutectics of Na2SO4-NiSO4 for the nickel phase [14] and Na2SO4-CoSO4 for the cobalt phase [24], with NiSO4 (or CoSO4 respectively) being a corrosion product [25].…”

Section: B Hot Corrosion Backgroundmentioning

confidence: 99%

“…Shi et al [24] performed fatigue testing and projected the experimental findings on the remaining flights until failure due to creep and fatigue interaction. Zhou et al [25] calculated the combined effect of creep and fatigue on the first turbine stage of a power-generation gas turbine engine using the Larson-Miller Parameter and stress-life curve for the two damage mechanisms, respectively. Alozie et al [26] translated the effect of fouling and erosion on an HPT to an equivalent time that the engine would have to operate in a reference mission to suffer the same degradation as when exposed to desert sand.…”

Section: Performance-based Gas Turbine Lifing Studiesmentioning

confidence: 99%

Hot Corrosion Damage Modelling in Aero Engines based on Performance and Flight Mission Analysis

Pontika

Laskaridis

Nikolaidis

et al. 2023

AIAA SCITECH 2023 Forum

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Lifing models for aircraft engines are mainly focused on creep, fatigue and oxidation, while hot corrosion remains one of the least explored areas. Hot corrosion is a form of chemical damage that causes surface degradation, sound material loss and reduced component life. A lifing analysis for aircraft engines without considering hot corrosion can lead to unexpected and unexplained hot corrosion findings by aircraft engine operators and Maintenance, Repair and Overhaul (MRO) providers during inspections. Although hot corrosion does not cause failure on its own, the interaction with other damage mechanisms can reduce component life significantly. Consequently, there is a necessity for including hot corrosion in the damage prediction process of aircraft engines. This paper presents a new methodology to estimate hot corrosion damage based on aero-engine performance and flight mission analysis while taking into account environmental exposure, fuel quality and material factors. The analysis in the present paper focuses on the hot corrosion progress over the course of the flight mission, while varying the major contamination factors and thrust derate, and the hot corrosion rate over flight time is then used to calculate the damage at the end of the mission. The participating mechanisms, from salt and sulfur impurity ingestion to deposition rate and hot corrosion attack, are analytically presented to explain the progress of the phenomenon in aero-engine components. In the investigated type of engine, the first stage of the low-pressure turbine is found to be the most affected. It is concluded that hot corrosion is favored by a combination of high pressure, high sulfur oxide concentration, and high salt deposition rate within an intermediate temperature range while the gas conditions near the component surface remain below the sodium sulfate saturation point, and these conditions are linked with aero-engine operation. The presented hot corrosion framework captures the effect of mission requirements, component operating conditions, environmental exposure, fuel quality and material on the hot corrosion damage of hot section components. It can be used to inform aero-engine maintenance planning, lifecycle analysis and MRO contract-costing, and can benefit digital twins for predictive maintenance.

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A Damage Evaluation Model of Turbine Blade for Gas Turbine

Cited by 17 publications

References 18 publications

Gas Path Fault and Degradation Modelling in Twin-Shaft Gas Turbines

Gas Path Fault and Degradation Modelling in Twin-Shaft Gas Turbines

Assessment of degradation equivalent operating time for aircraft gas turbine engines

Hot Corrosion Damage Modelling in Aero Engines based on Performance and Flight Mission Analysis

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