高负荷氦气压气机平面叶栅数值试验及叶型优化  

Numerical Experiment and Blade Profile Optimization of a Plane Cascade in a High-load Helium Compressor

作　　者：龙艳丽[1] 徐立民[2] 于景磊[2] 

机构地区：[1]哈尔滨工程大学动力与能源工程学院,黑龙江哈尔滨150001 [2]中国船舶重工集团公司第七0三研究所,黑龙江哈尔滨150078

出　　处：《热能动力工程》2012年第2期246-252,269-270,共7页Journal of Engineering for Thermal Energy and Power

摘　　要：基于大转折角基元级速度三角形设计概念,使用CFD软件对3种进气马赫数、6种进气角、3种扩压因子、3种叶栅稠度、2种叶型最大厚度比的共计324个平面叶栅流场进行数值计算。为了提高新型叶栅的性能,利用人工神经网络构建基于数据库样本空间的近似函数,采用遗传算法来寻找新的设计,并对新的设计进行气动性能预测。对中弧线和厚度分布进行优化,优化后总压损失系数降低了14.48%。Based on a speed triangle design conception for elementary stages with a large deflection angle,a numerical calculation was performed of a total of 324 flow fields of a plane cascade by using a CFD software,including three air inlet mach numbers,six air inlet angles,three pressure diffusion factors,three cascade solidities and two blade profile maximal thickness ratios.To enhance the performance of the new type cascade,an artificial neural network was employed to constitute an approximate function based on the database sample space and the genetic algorithm was used to look for new designs and predict their aerodynamic performances.Furthermore,the mid-arc line and thickness distribution were optimized and the total pressure loss coefficient has decreased by 14.48% after the optimization.

关 键 词：氦气压气机 大转折角 基元级速度三角形 优化 总压损失 

分 类 号：TK474.8[动力工程及工程热物理—动力机械及工程]