跨声速风扇气动设计及非定常流场结构研究  

Research on the Aerodynamic Design of Transonic Fan and Unsteady Flow Structure

作　　者：姜斌[1] 郑群[1] 王松涛[2] 冯国泰[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]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《工程热物理学报》2013年第12期2248-2252,共5页Journal of Engineering Thermophysics

基　　金：中央高校基本科研业务费专项资金资助(No.HEUCFR1111)

摘　　要：基于三维数值模拟技术,对某小型跨声速风扇进行了三维气动改型设计,达到了新的设计要求.在此基础之上,采用相位延迟法研究了转/静干涉条件下压气机叶栅内的非定常流场结构.探讨了存在来流干扰情况下,高负荷弯、扭静叶栅的非定常气动性能,研究了下游静叶吸力面非定常附面层发展特点及规律,研究结果表明:三维气动改型设计在保持喘振裕度不降低的情况下,设计效率达到90%左右.在非定常条件下,转/静之间势流的相互干涉强烈影响着下游静叶的非定常负荷分布,而尾迹等高损失区对静叶表面的压力影响范围十分有限.对于表征静叶损失特性的非定常附面层主要受到来流高损失流体传播的影响,势流干扰的影响并不显著.A 3D aerodynamic design of transonic fan was completed by using numerical simulation method and the new design requirement was satisfied. Based on the design result, unsteady flowfield structure was studied by phase-lagged method considering the stator-rotor interactions. The unsteady aerodynamic performance and the development of boundary layer of high load bowed and swept blade was researched under the influenced of incoming flow. The results show that etticiency of new fan designed by 3D numerical method achieved 90% with no decrease of surge margin. The unsteady aerodynamic load of the blade was influenced heavily by the potential flow interaction between rotor and stator, but the influence of high loss fluid such as the rotor wake on the unsteady pressure distribution of stationary blade slightly. The unsteady boundary layer loss is determined by the propagation process of incoming high loss fluid, the influence of potential flow interaction was not significantly.

关 键 词：跨声速风扇 弯掠叶片 数值模拟 非定常 流场结构 

分 类 号：TK471[动力工程及工程热物理—动力机械及工程]