Thermal barrier coatings （TBC） have been improved for the engine applications. During working process of the engine, components were subjected to thermal stresses. For simulating thermally stressed engine parts, dis...Thermal barrier coatings （TBC） have been improved for the engine applications. During working process of the engine, components were subjected to thermal stresses. For simulating thermally stressed engine parts, disc specimen was objected to airflow at the temperatures about 1,000℃. In this study, finite element structural and thermal analyses were carried out on both uncoated （without coating） and ceramic-coated disc specimen using ANSYS code. A 150 micron super alloy bond coating （NiCrAIY） was first applied to the specimen. Then, the disc specimen was covered by 350 micron thickness of Mullit （3Al2O3.2SiO2） as a top coating. These analysis were performed for detecting the possible thermally problem areas. The disc＇s thermal stressed problematic areas were determined by the finite element analysis was helpful for improving the geometry and TBC.展开更多
In order to reduce product development cycle time, aerospace companies tend to develop various correlations integrating geometric and performance parameters. This paper covers the development of a parameterization mod...In order to reduce product development cycle time, aerospace companies tend to develop various correlations integrating geometric and performance parameters. This paper covers the development of a parameterization modeling, to be used in the preliminary design phase, for the turbine cover plate of an aero-engine. The parameterization modeling of the turbine cover plate is achieved by using commercial CAD （computer aided design） software processing in batch mode. Two main approaches are presented the outer face and the skeleton models. These models can then be integrated into an iterative process for designing optimal shapes. Both models are capable of reproducing existing cover plate with reasonable accuracy in relatively shorter time periods. However, the skeleton approach provides probably the best results in terms of flexibility and accuracy, but increases programming complexity and requires greater run times.展开更多
文摘Thermal barrier coatings （TBC） have been improved for the engine applications. During working process of the engine, components were subjected to thermal stresses. For simulating thermally stressed engine parts, disc specimen was objected to airflow at the temperatures about 1,000℃. In this study, finite element structural and thermal analyses were carried out on both uncoated （without coating） and ceramic-coated disc specimen using ANSYS code. A 150 micron super alloy bond coating （NiCrAIY） was first applied to the specimen. Then, the disc specimen was covered by 350 micron thickness of Mullit （3Al2O3.2SiO2） as a top coating. These analysis were performed for detecting the possible thermally problem areas. The disc＇s thermal stressed problematic areas were determined by the finite element analysis was helpful for improving the geometry and TBC.
文摘In order to reduce product development cycle time, aerospace companies tend to develop various correlations integrating geometric and performance parameters. This paper covers the development of a parameterization modeling, to be used in the preliminary design phase, for the turbine cover plate of an aero-engine. The parameterization modeling of the turbine cover plate is achieved by using commercial CAD （computer aided design） software processing in batch mode. Two main approaches are presented the outer face and the skeleton models. These models can then be integrated into an iterative process for designing optimal shapes. Both models are capable of reproducing existing cover plate with reasonable accuracy in relatively shorter time periods. However, the skeleton approach provides probably the best results in terms of flexibility and accuracy, but increases programming complexity and requires greater run times.
