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Numerical Analysis of Flow Characteristics within Blades for Design Parameters of Impulse Supersonic Turbine Blade  

신봉근 (부산대학교 항공우주공학과)
정수인 (부산대학교 항공우주공학)
김귀순 (부산대학교 항공우주공학)
이은석 (한국항공우주연구원 터보펌프그룹)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.8, no.2, 2004 , pp. 62-72 More about this Journal
Abstract
In this paper. firstly, numerical results were compared with experimental results to verify accuracy of the results. It is found that the numerical results show good agreements with experimental result. Next, computations about flow within blades for design parameters such as radius of the pressure and suction side's curvature and pitch-chord ratio have been performed. It is found that the flow and performance characteristics mainly depend on shocks occurred at the leading edge of blades and the end of nozzle and separations occurred inside the flow passage. And shock of nozzle and separations depend upon area of flow passage and shocks of blade are affected by the number of blades occupied by a nozzle.
Keywords
Impulse Supersonic Turbine; Design Parameter; Separation; Shock;
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