Abstract

This paper presents an optimization platform for an internal-cooled gas turbine blade, using a developed simplified three-dimensional Conjugate Heat Transfer analysis method. This paper manages to improve the aerodynamic efficiency while ensuring the heat transfer performance. The simplified 3D CHT method is based on a one dimensional program for internal pipe network calculation and ANSYS CFX code. It’s for flow field prediction outside the blade and the solid region computation. Numerical verification is performed for the procedure. The platform is validated and used in aerodynamic optimization design for a turbine rotor in this study. The constraints for this optimization design is that the average and maximum temperature on the blade surface should meet the design requirement. The optimization results show that the variation in the average and maximum temperature is no more than 2K compared with the prototype. The aerodynamic efficiency is increased by 0.34%, and it the coolant mass is reduced by 7.66%.

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