AERODYNAMIC INVESTIGATION OF A SINGLE-STAGE AXIAL COMPRESSOR WITH A CASING GROOVE AND TIP INJECTION USING FLUID-STRUCTURE INTERACTION ANALYSIS

摘要

In this paper, a fluid-structure interaction (FSI) analysis was performed for a single-stage axial compressor with casing groove and tip injection using three-dimensional Reynolds-Averaged Navier-Stokes equations. The k-e turbulence model and hexahedral grids system were used in the analysis. ANSYS solid 186 elements type was used to analyze the solid characteristic. In order to achieve robust stability of the transonic axial compressor, a casing groove was installed with tip injection on rotor tip region. FSI analysis was carried out to predict the deformation of the blades, and the results were compared to those of non-FSI analysis. Validation of the numerical results performed in comparison with experimental data, showed good agreements with experimental data for the adiabatic efficiency and total pressure ratio. It was found that deformation of blades affects the aerodynamic performance of the compressor to some extent. Stability of the axial compressor was enhanced by installing the casing groove with tip injection.