为解决轮盘形状优化过程中变量多且高度非线性的问题,建立了基于核主成分分析(Kernelized Principal Component Analysis,KPCA)技术的航空发动机轮盘优化方法。利用控制点形式的非均匀有理B样条(NURBS)曲线构造涡轮盘截面形状,以控制点...为解决轮盘形状优化过程中变量多且高度非线性的问题,建立了基于核主成分分析(Kernelized Principal Component Analysis,KPCA)技术的航空发动机轮盘优化方法。利用控制点形式的非均匀有理B样条(NURBS)曲线构造涡轮盘截面形状,以控制点的坐标作为设计变量;利用实验设计(DOE)进行采样,从中选取60个较优样本,计算核矩阵K,应用核矩阵K的特征向量计算投影向量的系数矩阵,采用投影后的变量作为新的设计变量,重构设计空间;最后,在降维后的设计空间中优化涡轮盘。结果表明:优化后轮心当量应力降低4.21%,周向应力降低0.26%,轮背径向应力降低1.58%,子午截面平均周向应力降低2.57%,圆柱截面平均径向应力降低6.51%。展开更多
An Equilibrium Multi-objective Optimization Model（EMOM） with self-regulated weighting factors has been proposed for the optimum design of non-circular clearance hole on the front flange of turbine disk. In the ‘‘e...An Equilibrium Multi-objective Optimization Model（EMOM） with self-regulated weighting factors has been proposed for the optimum design of non-circular clearance hole on the front flange of turbine disk. In the ‘‘equilibrium design＂, both the stress decrease around the hole and the least hole＇s profile variation are considered, which balances two ambivalent design goals. Specific discrete variables are applied to realize the standardization design in the optimization process, in which a Surrogate Genetic Coding Algorithm（SGCA） is introduced, and a special check module is used to get rid of repeated fitness evaluation of the samples. The method offers an equilibrium design for the non-circular clearance hole of the turbine disk with great accuracy and efficiency.展开更多
文摘为解决轮盘形状优化过程中变量多且高度非线性的问题,建立了基于核主成分分析(Kernelized Principal Component Analysis,KPCA)技术的航空发动机轮盘优化方法。利用控制点形式的非均匀有理B样条(NURBS)曲线构造涡轮盘截面形状,以控制点的坐标作为设计变量;利用实验设计(DOE)进行采样,从中选取60个较优样本,计算核矩阵K,应用核矩阵K的特征向量计算投影向量的系数矩阵,采用投影后的变量作为新的设计变量,重构设计空间;最后,在降维后的设计空间中优化涡轮盘。结果表明:优化后轮心当量应力降低4.21%,周向应力降低0.26%,轮背径向应力降低1.58%,子午截面平均周向应力降低2.57%,圆柱截面平均径向应力降低6.51%。
文摘An Equilibrium Multi-objective Optimization Model（EMOM） with self-regulated weighting factors has been proposed for the optimum design of non-circular clearance hole on the front flange of turbine disk. In the ‘‘equilibrium design＂, both the stress decrease around the hole and the least hole＇s profile variation are considered, which balances two ambivalent design goals. Specific discrete variables are applied to realize the standardization design in the optimization process, in which a Surrogate Genetic Coding Algorithm（SGCA） is introduced, and a special check module is used to get rid of repeated fitness evaluation of the samples. The method offers an equilibrium design for the non-circular clearance hole of the turbine disk with great accuracy and efficiency.
