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

被引：13

作者：

Sadowski, Tomasz ^{[1
]}

Golewski, Przemyslaw ^{[1
]}

机构：

[1] Lublin Univ Technol, PL-20618 Lublin, Poland

来源：

DIFFUSION IN SOLIDS AND LIQUIDS VII | 2012年 / 326-328卷

关键词：

Turbine blades; Thermal barrier coating (TBC); Computational fluid dynamics (CFD); Computational structural mechanics (CMS); VANE/BLADE RELATIVE POSITION; FGM CYLINDRICAL PLATES; SURFACE; SHOCK;

D O I：

10.4028/www.scientific.net/DDF.326-328.530

中图分类号：

TB3 [工程材料学];

学科分类号：

0805 ; 080502 ;

摘要：

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.

引用

页码：530 / 535

页数：6

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