Flutter and Modal Analysis of Gas Turbine Compressor Blades

Abstract

This study aims to analyze the fluttering in the gas turbine compressor blade and the aerodynamic damping effects on the gas compressor blades by analyzing the damping coefficient sign in the model. The flutter in aerodynamic profiles is referred to as the self-excited vibration in air-foils due to unsteady pressure oscillations in the air flow field. The modal analysis of the gas compressor blade of aluminum alloy is carried out at modes 1, 2, and 3 in which the natural and modal frequency of blade is tested by using the ANSYS 17 platform. The various cases are studied for the different number of blades of gas turbine compressor to analyze the effect of fluttering on the blades.