A Cost Effective Approach for Subsonic Aeroelastic Stability Analysis of Turbomachinery 3D Blade Cascade. A Reduced Order Aeroelastic Model Numerical Approach

Abstract

In this paper a cost effective numerical model for subsonic classical flutter analysis for turbomachinery is presented. The model is based on reduced order aeroelastic modeling (ROAM) approach. The prime objective of the ROAM is to significantly reduce the computational time for flutter analysis of low pressure (LP) stage blades of power turbines at preliminary design stage. A mesh free incompressible fluid solver based on boundary element method(BEM) e.g. 3D panel method is developed. The proposed ROAM is employed to perform subsonic aeroelastic stability analysis in 3D blade cascades. The ROAM simulated results are compared against experimental and high fidelity CFD-CSD model's results. The ROAM estimated results show good agreement with experimental results and prove to be much faster in execution compared to CFD-CSD model. Therefore, this gives designers and engineers a freedom to analyze multiple design iteration in very short time on normal workstation. Thus, the ROAM has immense potential for industrial use as a cost effective and faster numerical tool for design and analysis of more efficient and safer power turbines to meet the future demand of electric energy cheaply, quickly and efficiently.

Bulletin of the Polish Academy of Sciences: Technical Sciences

“…A study of Classical flutter as shown in Fig. 1b in the 2D blade cascade using PM based BEM flow solver is carried out by Prasad et al [8,9]. In the stall flutter case, the flow is dominated by separated flow, thus classical PM can be used here.…”