Calculation And Analysis Of Thermal Stress Of Turbomachinery Guide Vane Using The Finite Element Method

This paper presents the calculation and analysis of thermal stress of turbomachinery guide vane of aeroengine using the Finite Element Method. Turbomachinery guide vane is a assembly which turns partial heat energy of airflow into kinetic energy and makes the airflow meet entrance direction of turbo impeller. The Finite Element Theory is summarized in the paper. At the same time, a simplified model of turbomachinery guide vane of aeroengine is set up by UG software. Then, the model is switched to ANSYS to calculate and analyze thermal stress. Finally, response distribution of heat exchange and heat stress changing are gained. The calculation method adopted and the results obtained here have special reference to the study of turbomachinery guide vane.Two calculation model of turbomachinery guide vane of aeroengine are established by the simplification processing of the guide vane. Model A: The turbomachinery guide vane is subjected to axial temperature changing. Temperature load is directly set in two faces. Front face is set to 1000℃, behind is 800℃. The thermal stress is analyzed when inside and outside rings are not constrained and are constrained respectively. The figures of thermal and stress distribution are gained. Model B: The turbomachinery guide vane is subjected to radial temperature changing. The thermal stress is also analyzed when inside and outside rings are not constrained and are constrained respectively. The figures of thermal and stress distribution are gained. Finally, the results of calculation of two models are compared and analyzed properly.