Preprint Article Version 1 This version is not peer-reviewed

Aeromechanical Optimization of First Row Compressor Test Stand Blades

Version 1 : Received: 2 May 2019 / Approved: 6 May 2019 / Online: 6 May 2019 (10:29:25 CEST)

How to cite: Ghalandari, M.; Ziamolki, A.; Mosavi, A.; Shamshirband, S.; Chau, K. Aeromechanical Optimization of First Row Compressor Test Stand Blades. Preprints 2019, 2019050049 (doi: 10.20944/preprints201905.0049.v1). Ghalandari, M.; Ziamolki, A.; Mosavi, A.; Shamshirband, S.; Chau, K. Aeromechanical Optimization of First Row Compressor Test Stand Blades. Preprints 2019, 2019050049 (doi: 10.20944/preprints201905.0049.v1).

Abstract

In this study, an optimization of the first blade in new test rig presented. Blade tuning is conducted using 3D geometrical parameters. Sweep and dihedral play an essential role in this study. Compressor characteristics and blades vibrational behavior are the main objective of the evaluation. Here, the attachments are designed to isolate blade dynamics from Disk. So, the Vibrational behaviors of the one's blade are tuned based on the self-excited and forced vibration phenomenon. Using a semi analytical MATLAB code instability conditions are satisfied. The code takes advantages of whitehead and force response theory to predict classically and stall flutter speeds. Beside, Forced vibrations instability is controlled using a theory presented by Campbell. Aerodynamics of new blade geometry determined using multistage simulations Computational fluid dynamics (CFD) software. Numerical results show increasing performance near the surge line and working interval along with increasing mass flow.

Subject Areas

design optimization; axial compressor blade; Sweep angle; Taper; Dihedral angles; Aero elasticity; multidisciplinary design optimization; computational fluid dynamics

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