Analysis of aerodynamic performance of high‐speed rotational components for MEMS based turbomachinery considering effects of tip clearance and diabatic heat transfer

This paper addresses a fundamental design guideline for rotational components of a micro‐scale gas turbine engine considering an interaction between geometrical structure and aerodynamics. The rotational components of the micro‐scale gas turbine engine may be subjected to the centrifugal stress due to high‐speed rotation. The efficiency of each component is strongly controlled by geometrical clearance between rotational and stationary components, and heat transfer from the turbine to the compressor. Therefore, the elastic deformations due to the centrifugal stress and heat transfer have important role to determine the practical aerodynamic performance of the rotational components. A new sophisticated geometrical structure was introduced to the rotational components to control the elastic deformation and maintain the compressor efficiency that is necessary to hold the minimum requirement for the thermodynamic cycle.