Computational Analysis of Performance of a Transonic Fan Blade

Abstract

This paper aims to study the performance of the NASA Rotor 67 transonic fan blade at various operating conditions. First, a steady-state computation along with mesh independence study is done using ANSYS CFX at the design operating speed of the rotor. Then the analysis is carried out at 86%, 92%, 96%, and 105% of the design operating speed. The performance of the rotor is compared and analysed for various off-design operating conditions to evaluate the flow behaviour in transonic speed through the highly twisted fan rotor blade.