Sang-Bum Ma

Aerodynamic Optimization of a Single-Stage Axial Compressor with Stator Shroud Air Injection

The effects of stator shroud air injection on aerodynamic performance were investigated for a single-stage axial compressor. Multiobjective optimization of the air injector was performed to maximiz...

Effects of a Circumferential Feed-Back Channel on Aerodynamic Performance of a Single-Stage Transonic Axial Compressor

This paper presents an investigation of a circumferential feed-back channel located on shroud surface in rotor domain to find its effects on aerodynamic performance of a single-stage axial compressor, NASA Stage 37, using three-dimensional Reynolds-averaged Navier-Stokes equations. Validation of numerical results was performed using experimental data for both of single rotor and single-stage compressors. A parametric study of the feed-back channel was performed using various geometric parameters related to the locations and shapes of the channel inlet and outlet. The numerical results showed that a reference circumferential feed-back channel increased the stall margin by 26.8% with 0.14% reduction in the peak adiabatic efficiency, compared to the case without the feed-back channel.Copyright

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

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 ReynoldsAveraged 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.