Modeling of Aeroelastic vibration of a rotating blade

Abstract

An increase in the demand to design an efficient and lighter gas turbine engine leads to an increase in the pressure ratio, operating speed and compact arrangement of thinner and lighter blades with fewer compressor stages and blade counts. As a result, the blades are subjected to higher aerodynamic loading with stronger blade row interaction. Therefore, blades of a modern higher performance gas turbine engines are more susceptible to the structural vibrations which have a negative impact on engine performance and operating costs. The thesis is presented in two parts: dynamics of a rotating blade and aeroelastic vibration. In the first part, modal characteristics such as natural frequencies and mode shapes of a rotating blade modeled using the beam theory are computed using the modal analysis. An aeroelastic phenomena due to vortex induced vibration is investigated in the second part of the thesis. newline