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HomeDefect and Diffusion ForumDefect and Diffusion Forum Vols. 326-328The Analysis of Heat Transfer and Thermal Stresses...

The Analysis of Heat Transfer and Thermal Stresses in Thermal Barrier Coatings under Exploitation

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Abstract:

Effectiveness of internal combustion turbines in aero-engines is limited by comparatively low temperature of exhaust gas at the entry to turbine of the engine. A thermal efficiency and other capacities of turbine strongly depend on the ratio of the highest to the lowest temperature of a working medium. Continuous endeavour to increase the thermal resistance of engine elements requires, apart from laboratory investigations, also numerical studies in 3D of different aero-engine parts. In the present work, the effectiveness of the protection of turbine blades by thermal barrier coating and internal cooling under thermal shock cooling was analysed numerically using the ABAQUS code. The phenomenon of heating the blade from temperature of combustion gases was studied. This investigation was preceded by the CFD analysis in the ANSYS Fluent program which allows for calculation of the temperature of combustion gases. The analysis was conducted for different levels of the shock temperature, different thickness of applied TBC, produced from different kinds of materials.

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Diffusion in Solids and Liquids VII

Info:

Periodical:

Defect and Diffusion Forum (Volumes 326-328)

Pages:

530-535

DOI:

https://doi.org/10.4028/www.scientific.net/DDF.326-328.530

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Cite this paper

Online since:

April 2012

Authors:

Tomasz Sadowski, Przemysław Golewski

Keywords:

Computational Fluid Dynamics (CFD), Computational Structural Mechanics (CMS), Thermal Barrier Coating (TBC), Turbine Blade

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