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안윤호(Yunho An),김중석(Joungseok Kim) 대한기계학회 2016 대한기계학회 춘추학술대회 Vol.2016 No.12
This paper introduces and explains axial turbine aerodynamic design of the developing highly-efficiency industrial gas turbine engine by Doosan heavy industries and constructions. Turbine aerodynamic design should be started with proper boundary conditions and constraints from relevant design disciplines such as cycle, combustor, turbine heat transfer and structure. In order to meet the performance target, it is very essential to carry out 1-/2-dimensional through-flow calculations. Airfoil design phase can be performed by the boundary conditions from through-flow calculation results. After airfoil design, turbine performance should be confirmed by numerical calculations or experimental tests. In terms of numerical calculation, engineers apply combustion gas compositions, exact inlet and outlet boundary conditions to its numerical domains. In case of cooled turbine, they should consider secondary air and cooling air.
이우상(Wusang Lee),이현(Hyun Lee),김동화(Dongwha Kim),김중석(Joungseok Kim) 대한기계학회 2009 대한기계학회 춘추학술대회 Vol.2009 No.5
In common with manufacturers, considerable efforts have been made nearly 40 years to investigate 3D blade stacking arrangement to improve turbine performance. Stacking line modifications are often used in turbomachinery as a means of controlling the degree of reaction, blade loading and secondary flows. Although 3D blade designs has been proved as an effective way of controlling blade loading and secondary flow, its influence on turbine performance and efficiency is not completely understood. The aim of this study is to understand the mechanism and the consequence of the compound lean blade on multistage performance and efficiency on the industrial gas turbine. In order to analysis the effect of compound lean, this paper discusses the CFD results focusing on pressure gradient, blade loading and entropy function.