摘要
将亚音速轴流压气机级的设计问题表述为气动力学损失和重量为极小化、压气机喘振边界极大化的多目标非线性数学规划问题。求优中考虑了多种气动与机械约束条件。介绍了压气机级性能估算的模型，给出了最大效率、最小重量、最大喘振边界以及效率、重量、喘振边界三者权衡最优条件下的算例。此方法可拓广用于多级轴流压气机中。
Design of a subsonic axial flow compressor stage has been formulated as a nonlinear multiobjective mathematical programing problem in which minimizing the aerodynamic losses and the weight of the stage,and maximizing the compressor stage stall margin are selected as the objectives.Aerodynamical and mechanical constraints are considered in the problem formulation.A model for estimating the performance of the compressor stage is also presented.Three objective functions,eight design variables and fourty-six constraint conditions are involved in the optimization.A numerical optimization is given for a subsonic axial compressor stage with maximum efficiency,minimum weight,maximum stall margin,in which weighted optimum relationship between efficiency,weight and stall margin has been obtained.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1995年第3期283-285,共3页
Journal of Aerospace Power
