Multidisciplinary Design Optimization Procedure for Improved Design of a Cooled Gas Turbine Blade
Multidisciplinary Design Optimization Procedure for Improved Design of a Cooled Gas Turbine Blade
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DOI：
10.1080/03052150210917
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发表时间：
2002-01
影响因子：
2.7
通讯作者：
S. Talya;Aditi Chattopadhyay;J. Rajadas
中科院分区：
文献类型：
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作者：
S. Talya;Aditi Chattopadhyay;J. Rajadas
燃气涡轮机叶片设计的多学科优化程序已开发和通用的三维叶片上演示。叶片在内部和外部冷却（薄膜冷却）。空气动力学和传热设计标准与叶片几何形状上的各种约束一起沿着集成。叶片被分成许多展向截面，每个截面由Bezier-Bernstein多项式表示。粘性流场计算采用三维Navier-Stokes方程的综合求解器。采用有限元法计算叶片内部温度。在每个展向截面处的平均叶片温度和最大叶片温度被最小化，其中对叶片几何形状具有空气动力学和几何约束。约束多目标优化问题的解决使用Kreisselmeier-Steinhauser函数的方法。一个通用的涡轮机叶片设计问题的结果表明，优化后的显着改善。
A multidisciplinary optimization procedure for gas turbine blade design has been developed and demonstrated on a generic 3-D blade. The blade is cooled both internally and externally (film cooling). Aerodynamic and heat transfer design criteria are integrated along with various constraints on the blade geometry. The blade is divided into numerous spanwise sections and each section is represented by a Bezier-Bernstein polynomial. A comprehensive solver for 3-D Navier-Stokes equations is used for the viscous flow calculations. The finite element method is used to obtain the blade interior temperatures. The average blade temperature and maximum blade temperature at each spanwise section are minimized, with aerodynamic and geometric constraints on the blade geometry. The constrained multiobjective optimization problem is solved using the Kreisselmeier-Steinhauser function approach. The results for a generic turbine blade design problem show significant improvements after optimization.