Aerodynamic and structural performances of a single-stage transonic axial compressor with blade fillet radius

• Published in: International journal of intelligent unmanned systems Vol. 11; no. 3; pp. 407 - 424
• Main Authors: Chu, Hoang-Quan, Dinh, Cong-Truong
• Format: Journal Article
• Language: English
• Published: Bingley Emerald Publishing Limited 29.06.2023; Emerald Group Publishing Limited
• Subjects: Axial stress; Efficiency; Fillets; Fluid-structure interaction; Pressure distribution; Pressure ratio; Reynolds number; Simulation; Turbocompressors; Turbulence models; Vortices; 1-Way FSI; Aerodynamic performances; Fillet radius; 3-D RANS; Structural performances; Single-stage transonic axial compressor
• ISSN: 2049-6427; 2049-6427
• DOI: 10.1108/IJIUS-07-2021-0069

PurposeThis study’s investigation aims to clarify the effect of an additional geometry, i.e. a fillet radius, to the blades of a single-stage transonic axial compressor, NASA Stage 37, on its aerodynamic and structural performances.Design/methodology/approachApplying the commercial simulation software and the one-way fluid–structure interaction (FSI) approach, this study first evaluated the simulation results with the experimental data for the aerodynamic performances. Second, this paper compared the structural performances between the models with and without fillets.FindingsThis research analyses the aerodynamic results (i.e. total pressure ratio, adiabatic efficiency, stall margin) and the structural outcomes (i.e. equivalent von Mises stress, total deformation) of the single-stage transonic axial compressor NASA Stage 37.Originality/valueThis paper mentions the influence of blade fillets (i.e. both rotor hub fillet and stator shroud fillet) on the compressor performances (i.e. the aerodynamic and structural performances).