Numerical Investigation of the Effect of Rotor Sweep on the Performance of One- Stage Transonic Compressor of an Industrial Gas Turbine

Compressor is one of the most parts of gas turbines that increase the pressure in the cycle of gas turbine. In regard to the fact that flow in compressor is influenced by positive pressure gradient and  the nature of the flow at compressor is very complicated, exact aerodynamic design of compressor blades (whose task is transmission work to the flow) is vital. In this project, effects of maximum changes of backward and forward sweeps of a rotor blade of special transonic compressor over the performance curves, including the efficiency and pressure ratio, has surveyed.  For 3d simulation of complex flow field of axial compressor the CFX software was utiliged. The results were compared with prior activities and soundness of that was certified then changes that above mentioned was exerted over the first stage rotor and change effects on performance parameters has surveyed. Results show us exert of changes that above mentioned causes to reduction of efficiency but if just the increase of pressure ratio intended the efficiency rises obviously.