摘要
为更好保证涡轮气冷叶片结构强度设计阶段的气动综合性能,在二维叶栅传统四线造型方法的基础上,引入了喉道宽度和尾缘弯折角两个参数以保证相关气动指标,同时,提出了一种基于自由曲线的异形冷气入口建模方法以改善冷气入口处的应力集中问题并通过优化算例证明了其潜在价值。在此基础上,对涡轮气冷叶片内部典型冷却结构进行参数化建模。以涡轮叶片质量和叶身最大拉伸应力为优化目标,选取参数对涡轮气冷叶片进行优化,优化后涡轮叶片质量和优化前相比下降0.99%,最大拉伸应力下降6.55%。优化结果表明:相关参数化方法可以满足具有复杂内冷结构的涡轮叶片的设计需求,可以有效提高涡轮设计效率。
In order to better ensure the comprehensive aerodynamic performance of turbine aircooled blades in the structural strength design stage,based on the traditional four-line modeling method of two-dimensional cascade,two parameters,i.e.throat width and trailing edge bending angle,were introduced to ensure the aerodynamic performance.A modeling method based on free curve for irregular cooling air inlet was proposed to alleviate the stress concentration problem at the cold air inlet and its potential value was demonstrated by optimization calculation.On this basis,the typical cooling structure inside the turbine air-cooled blade was modeled parametrically.The mass of blade and the maximal tensile stress of blade body were taken as the optimization objectives,and parameters were selected to optimize turbine air-cooled blades.After optimization,the mass of blade decreased by 0.99%and maximum tensile stress decreased by 6.55%.The optimization results showed that the relevant parameterization method can meet the design requirements of turbine blades with complex internal cooling structure,and can effectively improve turbine design efficiency.
作者
董少静
杨傲然
苑旺
张立章
方宇凡
申秀丽
DONG Shaojing;YANG Aoran;YUAN Wang;ZHANG Lizhang;FANG Yufan;SHEN Xiuli(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Beijing Key Laboratory of Aero-Engine Structure and Strength,Beihang University,Beijing 100191,China;Shenyang Aircraft Design and Research Institute,Aviation Industry Corporation of China,Limited,Shenyang 110035,China;Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China)
出处
《航空动力学报》
北大核心
2025年第3期393-404,共12页
Journal of Aerospace Power
关键词
涡轮气冷叶片
参数化建模
二维叶栅
冷却结构
优化设计
air-cooled blade
parametric modeling
two-dimensional aerofoil
cooling structure
optimization design
