In this research, An investigation is done to understand the effects of blades surface roughness on the Transonic 4-stageAxial compressor performance parameters. A CFD code, which solves the Reynolds-averaged Navier–Stokes equations, was used to simulate the complicated 3D flow field of the Axial compressor. Numerical results was validated against experimental data of the Axial compressor performance curves. Numerical data showed good agreement with experimental data. Then, the effects of blades surface roughness on the Axial compressor performance parameters at design point was analyzed. Results show that blades surface roughness leads to increase boundary layers and pressure loss and decrease the efficiency and pressure ratio. So efficiency reduction goes up comparing with pressure ratio in the compressor.
Sajjadi,S. M. and Asadollahi Ghohieh,A. (2012). The Effect of Blade Surface Roughness on the Transonic 4-stage Axial Compressor Performance. Journal of Aeronautical Engineering, 14(2), 1-10.
MLA
Sajjadi,S. M. , and Asadollahi Ghohieh,A. . "The Effect of Blade Surface Roughness on the Transonic 4-stage Axial Compressor Performance", Journal of Aeronautical Engineering, 14, 2, 2012, 1-10.
HARVARD
Sajjadi S. M., Asadollahi Ghohieh A. (2012). 'The Effect of Blade Surface Roughness on the Transonic 4-stage Axial Compressor Performance', Journal of Aeronautical Engineering, 14(2), pp. 1-10.
CHICAGO
S. M. Sajjadi and A. Asadollahi Ghohieh, "The Effect of Blade Surface Roughness on the Transonic 4-stage Axial Compressor Performance," Journal of Aeronautical Engineering, 14 2 (2012): 1-10,
VANCOUVER
Sajjadi S. M., Asadollahi Ghohieh A. The Effect of Blade Surface Roughness on the Transonic 4-stage Axial Compressor Performance. JoAE, 2012; 14(2): 1-10.
