A Mesh Division Method for Finite Element Model of Turbine Blade Thermal Barrier Coating

Abstract

The invention relates to a meshing method of a finite element model of a turbine blade thermal barrier coating. The meshing is conducted in finite element software ABAQUS and comprises the following steps that the established finite element model of the turbine blade thermal barrier coating is cut into two segments of a leaf blade body and a tenon, and the cutting position is a chamfering boundary of the connecting portion of the tenon and the leaf blade body; meshing is conducted to the leaf blade body through the following steps that (1), an auxiliary line is added to connect boundary points of all layered chamfering at the same chamfering, so that a straight line perpendicular to the interface is obtained, (2), seeds are arranged, and overall seed arrangement is firstly conducted according to sizes, then rearrangement of the seeds is conducted to the auxiliary line in the thickness direction according to the number, (3), a hexahedral sweep mesh is selected and meshing is conducted to the portion; meshing is conducted to the tenon portion. The meshing method of the finite element model of the turbine blade thermal barrier coating is simple and feasible, and can be completed just by applying the finite element software ABAQUS, ensures mesh quality, and greatly improves the meshing speed.

Description

technical field [0001] The invention relates to the technical field of finite element modeling of a high-performance aeroengine turbine blade thermal barrier coating system, in particular to a grid division method for a finite element model of a turbine blade thermal barrier coating. Background technique [0002] Thermal barrier coating technology, together with cooling technology and directional solidification single crystal substrate technology, is listed as the three core technologies of the aviation propulsion plans of various countries in the world, and is a key technology that determines the development level of a country's aviation industry. Thermal barrier coating refers to the coating of high temperature resistant and high heat insulation ceramic materials on the surface of the alloy substrate to reduce the surface temperature of the substrate and improve the thermal efficiency of the engine. Facts have proved that the application of 100-400 μm thermal barrier coati...

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Problems solved by technology

[0004] The mesh division of complex geometric models has always been one of the most troublesome problems for finite element modelers. There are generally two traditional methods: method one, reduce the requirements, and use lower mesh quality (such as tetrahedral mesh or Wedge grid, etc.) to divide the grid and then perform subsequent calculations, which not only has a great impact on the calculation accuracy, but also may not be able to achieve data extraction and analysis in post-processing; method two, use professional grid division software (such as Hypermesh etc.), the mesh quality obtained by using this method can be improved, but it introduces a new problem, that is, the compatibility problem between software, especially when it comes to curved surface and microscopic size, the incompatibility between software more pronounced

In addition, for modelers, it is very difficult to learn and use several complex software at the same time

For the finite element model of the thermal barrier coating of the turbine blade, due to the existence of various irregular geometric shapes such as tenons and cooling channels, the division of the mesh is particularly difficult, and a simple, feasible and high-quality mesh division is urgently needed method, but there is no related technology report

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