| Title |
Performance of an Axial Turbo Fan by the Revision of Impeller Pitch Angle |
| Keywords |
Axial turbo fan ; 축류식 터보팬 ; Impeller ; 임펠러 ; Pitch angle ; 피치각 |
| Abstract |
The aim of this paper is to suggest one efficient method for the various requirements of performance during the process designing and producing an impeller. The study considers that the revisions of a pitch angle of an impeller at an axial turbo fan affect an air flow rates and a static pressure rise. The axial turbo fan specified with the 250 Pa maximum static pressure and 1300 CMH fan air flow rates was tested and analyzed by CFD. The Numerical results show that the air flow rates are calculated to 1,175 CMH, 1,223 CMH, 1,270 CMH, 1,340 CMH and 800 CMH in cases that the pitch angles are 44°, 49°, 54°, 59° and 64° respectively. Also the static pressure rises are shown to 108 Pa, 122Pa, 141 Pa, 188 Pa and 63 Pa at the same cases. The air flow rate is increased linearly according to the changes of the pitch angle from 44° to 59° and the maximum air flow rate passing the impeller is increased to 13% over at the case of 59° pitch angle compared with the reference case of 54° pitch angle. The static pressure rise is increased linearly according to the changes of the pitch angle from 44° to 54°, too. The static pressure rise at the 59° pitch angle is increased to 33% over compared with the 54° pitch angle. The result shows that the revisions of pitch angle make the static pressure rise increase widely. However the air flow rates and the static pressure rise at the 64° pitch angle are suddenly decreased because of over-changed pitch angle. |