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http://dx.doi.org/10.5293/KFMA.2009.12.2.039

Effect of Turbine Blade tip shape on the Total Pressure Loss of a Turbine Cascade  

Lee, Ki-Seon (한국항공대학교 항공우주 및 기계공학과 대학원)
Park, Seoung-Duck (한국항공대학교 항공우주 및 기계공학과 대학원)
Noh, Young-Chul (한국항공대학교 항공우주 및 기계공학과 대학원)
Kim, Hak-Bong (한국항공대학교 항공우주 및 기계공학과)
Kwak, Jae-Su (한국항공대학교 항공우주 및 기계공학과)
Jun, Yong-Min (한국항공우주연구원 KHP개발실)
Publication Information
The KSFM Journal of Fluid Machinery / v.12, no.2, 2009 , pp. 39-45 More about this Journal
Abstract
Leakage flow through turbine blade tip gap causes strong leakage vortex near the blade suction side and induces large aerodynamic losses. In this study, the conventional plane tip and various squealer tip blades were tested in a linear cascade in order to measure the effect of the tip shape on the total pressure loss. Three tip gap clearances of 0.6%, 1.3%, and 2.0% of blade span were tested. Flow measurement was conducted at one chord downstream from the trailing edge with a five-hole probe. Results showed that the leakage vortex was stronger than passage vortex and the mass averaged overall total pressure loss through the cascade was the lowest for suction side blade tip case. For all tested cases, the area averaged overall total pressure loss was increased as the tip clearance increased.
Keywords
Tip leakage flow; Secondary flow; 5-hole probe; Squealer tip;
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