Investigation On Compressor Blade’s Profile Performance By Using 3D CFD

Ng, Kong Eng (2017) Investigation On Compressor Blade’s Profile Performance By Using 3D CFD. Project Report. UTeM, Melaka, Malaysia. (Submitted)

Text (24 Pages) Investigation On Compressor Blade’s Profile Performance By Using 3D CFD.pdf - Submitted Version Download (346kB)

Abstract

The key of determining the aerodynamics performance of compressor rotor blade is the drag and lift coefficient. Higher lift to drag coefficient indicates that less input power required for compressor blade rotation and growth in the efficiency of compressor. However, lift to drag ratio differs regarding to the profile of an airfoil. The other factor that contributes to compressor performance is the tip leakage occurrence. Tip clearance leads to the occurrence of tip vortex at suction surface side of compressor rotor and eventually forms a blockage effect that causes compressor stalling. In this study, three dimensional twisted profiles NACA 65(2)415, NACA 65(410) and NACA 65(4)221 are utilized to investigate the most suitable profile for compressor rotor of gas turbine using the method of numerical simulation (CFD). The performances of blade profiles are also determined using graphical visualization in Fluent post-processing (CFD). Profile NACA 65(2)415 has the highest lift to drag ratio of 20.9, which is 10% higher than the other profiles. The developed wake region at the trailing edge of profile NACA 65(410) raises the drag coefficient and deteriorates aerodynamic performance. However, NACA 65(4)221 does not manifest the best result in the three-dimensional visualization of tip leakage vortex (Q-Criterion). Although vortices are formed at the tip of all profiles, the vortex formed on suction side of profile NACA 65(4)221 has the lowest turbulence kinetic energy followed by NACA 65(2)415 and NACA 65(410). This finding corroborates NACA 65(2)415 is the most suitable profile for the industrial axial-flow compressor rotor application. However, the effect of tip vortex shall not be neglected. Further investigation shall be made to control the tip vortex of NACA 65(2)415 and avoid compressor stalling and reduction in compressor efficiency.

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