整级端壁造型对压气机总体性能影响的数值研究  

Numerical study on the influence of stage endwall profiling on the overall performance of compressor

作　　者：唐海兵 聂永发 余又红[2] TANG Haibing;NIE Yongfa;YU Youhong(Department of Electromechanical Management,China Coast Guard Academy,Ningbo 315000,China;Coll.of Power Engineering,Naval Univ.of Engineering,Wuhan 430033,China)

机构地区：[1]武警海警学院机电管理系,浙江宁波315000 [2]海军工程大学动力工程学院,武汉430033

出　　处：《兵器装备工程学报》2024年第S01期263-268,共6页Journal of Ordnance Equipment Engineering

基　　金：国家科技重大专项(J2019-I-0012-0012)。

摘　　要：以NASA Stage35为研究对象,通过NUMECA/Design3d商用优化软件,采用人工神经网络(ANN)与多目标遗传算法(NSGA-Ⅱ)相结合的方法,在喘振点附近对压气机转子和静子轮毂进行优化造型,对流场结构、气动性能以及压气机稳定性进行分析。结果表明:非轴对称端壁削弱了转子通道内的二次流强度,消除了静子前缘的马蹄涡,压气机的气动性能得到明显改善,压气机在不同设计转速下的喘振裕度都有增加,工作的稳定性得到提高。Taking NASA Stage35 as the research object,the compressor rotor and stator hub were optimized near the surge point by using the commercial optimization software NUMECA/Design3d and the method of combining artificial neural network(ANN)and multi-objective genetic algorithm(NSGA-Ⅱ).The flow field structure,aerodynamic performance and compressor stability were deeply analyzed.The results show that the non-axisymmetric endwall weakens the secondary flow intensity in the rotor channel,eliminates the horseshoe vortex at the leading edge of the stator,obviously improves the aerodynamic performance of the compressor,increases the surge margin of the compressor at different design speeds,and improves the stability of the compressor.

关 键 词：非轴对称端壁 整级端壁造型 轴流压气机 压气机稳定性 喘振裕度 

分 类 号：TK474.8[动力工程及工程热物理—动力机械及工程]