Numerical study on tip leakage vortex control by jet injection

Ryouta Nakamura, Masaya Suzuki, Makoto Yamamoto

Research output: Contribution to conferencePaper

Abstract

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.

Original languageEnglish
Publication statusPublished - 1 Jan 2012
Event14th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2012 - Honolulu, HI, United States
Duration: 27 Feb 20122 Mar 2012

Conference

Conference14th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2012
CountryUnited States
CityHonolulu, HI
Period27/02/122/03/12

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Nakamura, R., Suzuki, M., & Yamamoto, M. (2012). Numerical study on tip leakage vortex control by jet injection. Paper presented at 14th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2012, Honolulu, HI, United States.