涡轮弯扭叶片气动设计工程方法研究

Aerodynamic Design Engineering Method of Bending-torsion Turbine Blade

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。

Bending-torsion blade is one of the main methods to improve turbine efficiency, eonstrution of bending-torsion stacking line parametric mode is the important base for design of the turbine bending-torsion blade. To meet the engineering requirement of various turbine bending-torsion blade, the design method about are, parabola, subseetion spline curve stacking line rules were introduced, stacking line generating code was complied, and the application conditions and methods were suggested. The regression orthogonality design method can optimize the design of turbine bending-torsion blade with subsection spline curve stacking line. The bending-torsion balde engineering design method has been used in several turbine aerodynamic design.