APPLICATIONS OF NUMERICAL OPTIMIZATION TECHNIQUES TO DESIGN OF AXIAL COMPRESSOR BLADES
This paper describes the shape optimization of rotor and stator blades, NASA rotor 37 and a single-stage transonic axial compressor. Shape optimization of the rotor and stator blades operating at the design flow condition has been performed using the response surface method and three-dimensional Navier-Stokes analysis. Thin-layer approximation is introduced to the Navier-Stokes equations, and an explicit Runge-Kutta scheme is used to solve the governing equations. The three design variables, blade sweep, lean and skew, are introduced to optimize the three-dimensional stacking line of the blades. The objective function of the shape optimization is an adiabatic efficiency. Throughout the shape optimization of the rotor blade, it is found that the adiabatic efficiency can be increased by reducing the hub corner and tip losses. Separation line due to the interference between a passage shock and surface boundary layer on the blade suction surface is moved downstream for the optimized blade compared to the reference one. Flow characteristics inside the blade passage are analyzed to compare the flow pattern between the optimized and reference blades.
Choon-Man Jang Kwang-Yong Kim Sang-Ho Jung Dong-Yun Shin
Fire & Engineering Services Research Dept, KICT, Rep.of Korea Inha University, Rep.of Korea
国际会议
昆明
英文
35-42
2006-09-18（万方平台首次上网日期，不代表论文的发表时间）