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이강엽(K. Y. Lee),김형모(H. M. Kim),한영민(Y. M. Han),이수용(S. Y. Lee) 한국전산유체공학회 2002 한국전산유체공학회지 Vol.7 No.3
Most of modern aerospace gas turbines must be operated at a gas temperature which is several hundreds of degrees higher than the melting temperatures of the materials used in their construction. Complicated cooling schemes need to be employed in the combustor walls and in the high pressure turbine stages. Internal passages are cast or machined into the hot sections of aero-gas turbine engines and air from the compressor is used for cooling. In many cases, the cooling system is engineered to utilize jets of high velocity air, which impinge on the internal surfaces of the components. They are categorized as 'Impinging Cooling Method' and 'Vortex Cooling Method'. Specially, research of new cooling system(Vortex Cooling Method) that overcomes inefficiency of film cooling and limitation of space. The focus of new cooling system that improves greatly cooling efficiency using less amount of cooling air on surface heat transfer elevation. Therefore, in this study, a numerical analysis has been performed for characteristics of flow and heat transfer in the swirl chamber and compared with the flow measurements by LDV. Especially, for understanding high heat transfer efficiency in the vicinity of wall, we considered flow structure, vortex mechanism and heat transfer characteristics with variation of the Reynolds number.
쉬라우드 공기의 선회 유동 특성 변화에 따른 심플렉스 연료 노즐의 분무 특성
이동훈 ( D. H. Lee ),이강엽 ( K. Y. Lee ),최성만 ( S. M. Choi ) 한국분무공학회 2004 한국액체미립화학회지 Vol.9 No.3
N/A flow on simplex type fuel injector for gas turbine combustor. The spray tests using PDA(Phase Doppler Anemometry) technique were conducted to compare the performance of simplex atomizer with 0°, 40°, 50° swirled-shroud air conditions. In this study, we found that the injector with strong swirled-shroud air has the better atomization performance compared with weaker swirled and non-swirled conditions.