Finite element modeling method used for damage process of thermal barrier coating of turbine blade

A technology for turbine blades and thermal barrier coatings, applied in the field of high-performance aero-engine thermal insulation and protective coating systems, can solve problems such as limited modeling capabilities, difficulty in building object models, and cumbersome operations, and achieve clear thinking, easy to master and Use, overcome the effects of incompatibility
CN101567025BActive Publication Date: 2011-01-05XIANGTAN UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
XIANGTAN UNIV
Publication Date
2011-01-05

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Abstract

The invention discloses a finite element modeling method used for damage processes of the thermal barrier coating of a turbine blade, belonging to the field of heat-insulation protection coating system technology of high-performance aero-engine. The method adopts a CATIA software and a finite element ABAQUS software. The method wholly models all coatings and the substrate in the CATIA software, carries out a secondary processing to geometrical models in the ABAQUS software, carries out geometrical cleaning to the model in the CATIA software, and carries out simulation, calculation and result analysis in the ABAQUS software. The method can effectively overcome the incompatibility of the CAD software such as CATIA and the like and the finite element software, considers both various properties of the heat barrier coating material and the geometrical shape of the substrate, can exactly simulate the relevant key physical quantity of the turbine blade heat barrier coating system in practicalworking environment, has clear concept and is convenient to be mastered and used by the technicians.
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Description

Finite Element Modeling Method for Failure Process of Turbine Blade Thermal Barrier Coating System technical field The invention belongs to the technical field of high-performance aero-engine thermal barrier coating systems, and in particular relates to a finite element modeling method for the destruction process of a turbine blade thermal barrier coating system. Background technique Thermal barrier coatings (TBCs for short) are based on the characteristics of high melting point, low thermal conductivity, low vapor pressure, low emissivity and high reflectivity of ceramic materials. Ceramic powder is sprayed or deposited on superalloy hot end parts (especially turbines Blade) surface to reduce the working temperature of high-temperature components, so as to protect them from high-temperature corrosion and high-temperature oxidation, greatly prolonging the service life of high-temperature components, so that the high-temperature alloy components in modern aviation gas turbin...

Claims

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