进气畸变条件下非轴对称风扇设计及扩稳机理  

Design and stabilization mechanism of non-axisymmetric fansunder inlet distortion conditions

作　　者：余军杨 傅文广 孙鹏 张韬[2] 王春雪[2] 赵伟[2] YU Junyang;FU Wenguang;SUN Peng;ZHANG Tao;WANG Chunxue;ZHAO Wei(College of Safety Science and Engineering,Civil Aviation University of China,Tianjin 300300,China;Beijing Power Machinery Institute,Beijing 100074,China)

机构地区：[1]中国民航大学安全科学与工程学院,天津300300 [2]北京动力机械研究所,北京100074

出　　处：《航空学报》2024年第16期75-96,共22页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金民航联合基金重点项目(U2233207);中央高校基本科研业务费项目中国民航大学专项(3122024038)。

摘　　要：动力系统的进气畸变问题导致风扇性能下降、引发气动不稳定,从而对飞行器的安全构成潜在威胁,在军、民航空领域已受到广泛关注。为确保进气畸变条件下推进系统的可靠运行和飞行安全,本研究基于数值方法对某小涵道比涡扇发动机开展抗畸变风扇设计及扩稳研究。针对其畸变影响特征,采用非轴对称静子(NAS)布局来消除其不利影响,研究表明:NAS能够有效改善进气畸变条件下的风扇性能。相较于原型,在同流量工况下,绝热效率和总压比可分别增加1.37%和1.26%,稳定裕度可增加8.31%,实现了该NAS风扇的性能提升及扩稳目的;NAS设计直接作用于畸变区,有效改善了畸变区内的静叶冲角,抑制了静叶通道涡系结构的发展和迁移,较大程度减小静叶的扩压因子,从而有效消除了静叶的角区分离,使得静叶冲角周向分布相对均匀,有效改善风扇静叶内部流场,整体提高风扇的气动性能。此外,NAS设计还具有改善风扇后部内涵流场的潜力,使内涵出口的不均匀流场朝着周向均匀化方向发展,并且在有效减弱动态总压畸变强度、改善流场均匀性的同时,还兼具改善总温畸变的能力。Inlet distortion in propulsion systems leads to decrease in fan performance and induces aerodynamic insta⁃bility,posing a potential threat to aircraft safety and drawing extensive attention in both military and civil aviation fields.To ensure reliable operation of propulsion systems under inlet distortion conditions and maintain flight safety,this study conducted research on anti-distortion fan design and stability enhancement for a small bypass ratio turbofan engine us⁃ing numerical methods.Taking into account the characteristics of distortion effects,we employed a Non-Axisymmetric Stator(NAS)arrangement to mitigate the adverse effects.The research suggests that the NAS can effectively en⁃hance fan performance under inlet distortion conditions.Compared to the prototype operating at the same mass flow rate,relative increases of 1.37%,1.26%and 8.31%can be observed in adiabatic efficiency,total pressure ratio,and stability margin,respectively,successfully meeting the objectives of improving performance and expanding stabil⁃ity for the NAS fan.The NAS design directly impacts the distortion zone,effectively improving the stator incidence angle within the distorted region.It suppresses the development and migration of vortex structures in the stator pas⁃sage,resulting in a significant reduction in the stator diffusion factor.Consequently,it effectively eliminates corner separation in the stator passages,leading to a more uniform circumferential distribution of stator incidence angles.This,in turn,improves the internal flow field within the fan stator and enhances the overall aerodynamic performance of the fan.Furthermore,the NAS design has the potential to improve the flow field of the inner-bypass region behind the fan,encouraging the development of a more circumferentially uniform flow field at the inner-bypass outlet.Addi⁃tionally,while effectively reducing the intensity of dynamic total pressure distortion and improving flow field uniformity,the NAS design also possesses the capability to mitigate tota

关 键 词：进气畸变 涡扇发动机 非轴对称静子 气动性能 稳定裕度 

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]