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采用弯扭叶片设计是提高燃气涡轮效率的主要手段之一,而构建弯扭叶片积叠线的参数化模式是设计涡轮弯扭叶片的重要基础。为了满足各种涡轮叶片弯扭设计的工程需要,提出了采用圆弧型、抛物线型、分段样条曲线积叠线规律的涡轮弯扭叶片设计方法,编制了积叠线生成代码,并推荐了各方法的应用条件和方式;提出的回归正交设计方法可以对分段样条曲线积叠线的涡轮弯扭叶片进行寻优设计。所提出的弯扭叶片工程设计方法已经在多个涡轮气动设计中得到应用。
It is one of the main means to improve the efficiency of gas turbines that the bending and twisting blade design is used. The parameterization mode of constructing the stacking lines of bending and twisting blades is an important foundation for the design of the turbine blades. In order to meet the engineering requirements of all kinds of turbine blade bending and torsion design, the design method of turbine bending and twisting vane with circular arc, parabola and piecewise spline curves is proposed. The application conditions and methods of each method are presented. The proposed regression orthogonal design method can optimize the design of turbine curved and twisted blades with segmented spline curves. The proposed bending and twisting blade engineering design method has been applied in many turbine aerodynamic designs.