In a compressor and a turbine, there are some vortices which cause loss. A tip leakage vortex is one of these vortices, and it can lead to great loss in compressor and turbine blade passages. Many researchers have investigated control methods of tip leakage flow. In the present study, jet injection jet from the tip platform of a rotor blade is numerically investigated as a control method of tip leakage flow. This method has the possibility that tip leakage loss is decreases even if relatively large tip clearance is applied. However, it is not well known how injection parameters such as flow rate, injection angle, injection hole-position and so on should be determined to block tip leakage flow effectively. Considering these backgrounds, the purpose of this study is to clarify the possibility of the leakage control by tip injection. Three-Dimensional turbulent flow field near the blade tip is simulated. The computed flow field, mass flow rate of tip leakage flow and total pressure distribution at the downstream of the blade are investigated, and it is confirmed that the tip injection hole located at midchord can effectively control tip leakage loss.
|Publication status||Published - 1 Jan 2012|
|Event||14th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2012 - Honolulu, HI, United States|
Duration: 27 Feb 2012 → 2 Mar 2012
|Conference||14th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2012|
|Period||27/02/12 → 2/03/12|