摘要
结合民用飞机动力装置/机体集成研究的具体需要,采用数值模拟方法对大涵道比涡扇发动机进气道的侧风畸变特性进行研究,给出了进气道在侧风条件下工作的流场特征,分析了导致侧风畸变的流动机理.研究结果表明:进气道的侧风畸变主要受到典型的气流分离与再附以及地面吸入涡等复杂流动现象的影响;当进气道内部气流出现分离时,侧风畸变会随侧风速度的增加而突然加剧;进气道在近地面工作状态,产生的地面吸入涡现象可能会使短舱的侧风容限明显降低.此外,侧风状态的进气畸变特性随着发动机流量的变化,进气道内部气流的分离与再附存在差别,这导致了进气畸变指数呈现迟滞变化.
The inlet aerodynamic performance of distortion under crosswind for a high bypass ratio turbofan engine was numerically simulated to meet the need of civil aircraft engine/airframe integration.The flow characteristics and their underlying flow physics were investigated.The investigation suggests that：typical flow phenomena of separations,reattachments and ground vortex are found to be the root causes for the inlet distortion under crosswind;there is a sudden intensification in the distortion index as the onset of the inlet internal flow is separated with the increasing speed of crosswind;the civil aircraft inlet tolerance of crosswind would be reduced as the nacelles are affected by the ground vortex phenomenon;the distortion characteristics of civil aircraft inlet are also affected by the engine massflow,whilst the hysteresis loop of the distortion index is captured for the flow separation and reattachments are not exactly repeatable as the engine corrected mass flow rates vary.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2015年第2期289-296,共8页
Journal of Aerospace Power
基金
中国商用飞机有限责任公司博士后基金(SADRI201202)
上海市自然科学基金(14ZR1449600)
关键词
畸变
进气道
民用飞机
侧风
短舱
distortion
inlet
civil aircraft
crosswind
nacelle
