Temperature Estimation and Life Prediction of Turbine Blades Using Post Service Oxidation Measurements

Swaminathan, V. P.; Allen, J. M.; Touchton, G. L.

doi:10.1115/96-gt-528

Cited by 5 publications

(3 citation statements)

References 5 publications

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“…The modified Arrhenius equation presented by Swaminathan et al . [ 23 ] is used to model oxidation damage. This method assumes that the oxide layer grows parabolically.…”

Section: Tools and Modellingmentioning

confidence: 99%

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Severity estimation and effect of operational parameters for civil aircraft jet engines

Hanumanthan

Laskaridis

Singh

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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Engine maintenance costs for civil aircraft largely depend on the life consumption of critical parts like high-pressure turbine blade and disk. Severity (defined as a measure of relative damage) can be used to characterize the degree of life consumption for the parts subjected to low cycle fatigue, creep, and oxidation as predominant life-limiting modes under normal engine operation. In this context, a numerical tool has been developed to study the impact of engineaircraft operational parameters on engine severity. This is accomplished by combining aircraft performance, gas turbine performance, component sizing, heat transfer calculation, thermal analysis, structural analysis, life and severity estimation for the high-pressure turbine, and the disk components of jet engines. Operational parameters such as take-off (TO) derate, climb derate, outside air temperature, and airport altitude have been studied for lower thrust and larger thrust engines. The observations from the study show that TO derate and outside air temperature are dominant parameters in terms of engine severity. The use of climb derate also lowers the severity and is more beneficial for larger thrust engines, while airport altitude effects could be minimized by the use of suitable TO derate. The severity characteristics estimated through the numerical tool can provide an enhanced perspective on aircraft engine maintenance.

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“…The modified Arrhenius equation presented by Swaminathan et al . [ 23 ] is used to model oxidation damage. This method assumes that the oxide layer grows parabolically.…”

Section: Tools and Modellingmentioning

confidence: 99%

“…The Palmgren–Miner hypothesis [ 23 , 24 ], which predicts failure when the damage fractions approach unity, has been used in the model. Equation (18) holds good for the phenomenon of the low cycle fatigue which is dependent on the cycles to failure.…”

Section: Tools and Modellingmentioning

confidence: 99%

Severity estimation and effect of operational parameters for civil aircraft jet engines

Hanumanthan

Laskaridis

Singh

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Once the free elongation, mechanical strain and oxide thickness of the TGO are calculated, the oxidation model estimates the spallation of the TBC during each segment of flight for one cycle. 38…”

Section: Aeroengine’s Life Estimationmentioning

confidence: 99%

On the trade-off between minimum fuel burn and maximum time between overhaul for an intercooled aeroengine

Saatlou

Kyprianidis

Sethi

et al. 2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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A large variety of promising power and propulsion system concepts are being proposed to reduce carbon dioxide and other emissions. However, the best candidate to pursue is difficult to select and it is imperative that major investments are correctly targeted to deliver environmentally friendly, economical and reliable solutions. To conceive and assess gas turbine engines with minimum environmental impact and lowest cost of ownership in a variety of emission legislation scenarios and emissions taxation policies, a tool based on a techno-economic and environmental risk assessment methodology is required. A tool based on this approach has been developed by the authors. The core of the tool is a detailed and rigorous thermodynamic representation of power plants, around which other modules can be coupled (that model different disciplines such as aircraft performance, economics, emissions, noise, weight and cost) resulting in a multidisciplinary framework. This approach can be used for efficient and cost-effective design space exploration in the civil aviation, power generation, marine, and oil and gas fields. In the present work, a conceptual intercooled core aeroengine design was assessed with component technologies consistent with 2020 entry into service via a multidisciplinary optimisation approach. Such an approach is necessary to assess the trade-off between asset life, operating costs and technical specification. This paper examines the influence of fuel consumption, engine weight and direct operating costs with respect to extending the engine life. The principal modes of failure such as creep, fatigue and oxidation, are considered in the engine life estimation. Multidisciplinary optimisation, comprising the main engine design parameters, was carried out with maximum time between overhaul as the objective function. The trade-off between minimum block fuel burn and maximum engine life was examined; the results were compared against the initial engine design and an assessment was made to identify the design changes required for obtaining an improved engine design in terms of direct operating costs. The results obtained from the study demonstrate that an engine optimised for maximum time between overhaul requires a lower overall pressure ratio and specific thrust but this comes at the cost of lower thermal efficiency and higher engine production costs.

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Validation of CESI Blade Life Management System by Case Histories and in situ NDT

Rinaldi

Bicego

Colombo

2004

Journal of Engineering for Gas Turbines and Power

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A life management system was developed for hot components of large industrial gas turbines, in the form of a software tool for predicting component lives under typical operational transients (normal and also abnormal) and steady-state periods. The method utilizes results of previous thermo-mechanical finite element and finite volume fluid mechanics analyses. The basic idea of this method is using data from structural and aero-thermal analyses (pressures and temperatures), blade life theory, and material properties as an input to algorithms, and using operational and historical data to validate the predicted damage amounts. The software developed in this project, of general applicability to all GT models, has been implemented with reference to the geometries, materials, and service conditions of a Fiat-Westinghouse model.

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Temperature Estimation and Life Prediction of Turbine Blades Using Post Service Oxidation Measurements

Cited by 5 publications

References 5 publications

Severity estimation and effect of operational parameters for civil aircraft jet engines

Severity estimation and effect of operational parameters for civil aircraft jet engines

On the trade-off between minimum fuel burn and maximum time between overhaul for an intercooled aeroengine

Validation of CESI Blade Life Management System by Case Histories and in situ NDT

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