Development of an integrated procedure for aerodynamic and aeromechanic design of gas turbine engines

The objective of this work is focused on the development of an integrated procedure for the aerodynamic and aeromechanic design of axial gas turbines blade rows. The methodology is based on steady and unsteady CFD simulations, which are used to evaluate the aerodynamic performance, aerodynamic damping and forcing functions which excite the turbine blade rows. FEM analyses are also rpovided to obtain natural frequencies and mode shapes, which are input data to calculate the aerodynamic damping (by means of flutter computations) and the forced response analysis of the component under investigation.