Reduced-Order Modeling of Compressor Blades by 1D Finite Elements Available to Purchase

The concept design of new gas turbines requires fast computational tools able to predict the modal characteristics of the blades on the basis of some incomplete description of their geometry. This paper investigates the potentials of a 1D Finite-Element (FE) formulation based on the beam theory to achieve this result. The key-point of the method is the construction of the FE mesh and the determination of the FE parameters starting from the knowledge of a set of blade cross sections. A typical compressor blade of a large gas turbine is used as a case study to validate the procedure.