چكيده به لاتين
In this thesis, at first, with using the maps presented by the respected professor, the geometric information of the compressor blades with the geometric information of the root and the blade tip and other requirements were extracted and in order to numerically simulate the required maps using the Bladegen was drawn. The tested compressor is a subsonic axial flow type, comprising a stage with 38 rotary blades and 37 fixed blades. A row of inlet guide vane includes38blades in upstream of the rotating component. The air entered the stage after entering the bell-shaped entrance area after passing through the inlet guide vanes. in fact, the compressor is 3 stage with a fixed ring, that's two stages being out of the survey circuit. In the present study, compressor without casing treatment and three casing treatment structure semi-tubular, semi-circular and semi-elliptical were studied. the casing treatments included 23.2%, 33.3%, 43.4%, 53.5%, 63.6%, 73.7% and 83.8% and the numerical results from the empirical results of Mohammad Akhlaghi were compared in 2001.
In the results of the efficiency, all exposures with different percentages of the drop in the maximum efficiency are compared to the solid casing. in the semi-tubular geometry with the 33.3%, 23.2%, and 53.5%rotor exposures have been able to achieve near solid casing efficiencies. In semi-circular geometry, the maximum efficiency is for 33.3% rotor exposures and the highest drop is for 43.4%. Also, in semi-elliptical geometry, the maximum efficiency is for 23.2% rotor exposures, and the highest drop is for 73.7%.
In the results of the stall margin improvement, in the semi-tubular geometry, the casing treatment with the 33.3% rotor exposure proved to be the best configuration. In semi-circular and semi-elliptical geometries, the casing treatments with 83.8 and 63.6% rotor exposures, respectively, have been able to provide the most improvement.
