跨声速压气机转子几何误差气动敏感性统计  

Statistics on aerodynamic sensitivities of blade geometric errors for transonic compressor rotor

作　　者：马峰 尚珣 刘汉儒[1] 王掩刚[1] 陈为雄[1] 杜亦璨 MA Feng;SHANG Xun;LIU Hanru;WANG Yangang;CHEN Weixiong;DU Yican(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;Aviation Power Company Limited,Aero Engine Corporation of China,Xi’an 710021,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129 [2]中国航发动力股份有限公司,西安710021

出　　处：《航空动力学报》2023年第10期2483-2500,共18页Journal of Aerospace Power

摘　　要：为了研究跨声速压气机转子的气动性能对不同类型几何误差的敏感性,以NASA Rotor 37为研究对象,采用非均匀有理B样条(NURBS)曲面及遗传算法实现三维叶型曲面重构。考虑了26个几何误差模型。采用拉丁超立方结合蒙特卡洛模拟生成了800个样本,通过定常CFD数值计算获得叶型气动特性及流场结构,采用Spearman秩相关及期望值分析不同工况下几何误差与气动性能之间的非线性关系。对不同工况下效率最敏感的几何误差模型进行了流动机理分析。统计分析结果表明:堵塞工况下,叶中前缘轮廓度对效率有最显著的消极影响,叶尖吸力面轮廓度对压比有最显著的消极影响。最高效率工况下,叶中吸力面轮廓度对效率和压比都有着最显著的消极影响。近失速工况下,叶尖前缘轮廓度对效率有最显著的消极影响,而叶中尾缘轮廓度对压比有着最显著的积极影响。In order to study the sensitivity of the aerodynamic performance of a transonic compressor rotor to different types of geometric errors,NASA Rotor 37 was selected as the research object.The non-uniform rational B-splines(NURBS)surface algorithm and genetic algorithm were used to parameterize the three-dimensional blade surface.A total of 26 geometric errors,including the sweeping error and skewing error,were considered and extracted for the 3D rotor blade.800 samples were generated by uniform Latin hypercube sampling in association with Monte Carlo algorithm.The loss characteristic and flow structure of Rotor 37 were obtained by steady CFD numerical simulation.Spearman rank correlation and expectation curve analysis were used to investigate the nonlinear relationship between geometric deviations and aerodynamic parameters at two typical working conditions.The flow mechanism analysis was carried out on the most sensitive geometric error model of efficiency under different working conditions.Results indicated that leading-edge profile factor of midspan had the greatest negative effects on rotor efficiency;while suction profile factor near shroud was most negatively correlated with pressure ratio at choke point.As for peak efficiency point,suction profile factor of midspan had the most obvious negative influence on rotor efficiency and pressure ratio.Regarding to near stall point,suction profile factor of midspan had great negative correlation with rotor efficiency.Trailing-edge profile factor of midspan was great positively correlated with pressure ratio.

关 键 词：几何误差 跨声速压气机转子 非均匀有理B样条(NURBS)曲面 气动敏感性 相关性分析 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]