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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.
Combining with the specific needs of civil aircraft power plant / body integration research, the numerical simulation method is used to study the crosswind characteristics of the inlet of large bypass ratio turbofan engine, and the flow of inlet working under crosswind conditions is given. Field characteristics and the flow mechanism leading to the crosswind distortion are analyzed.The results show that the crosswind of the inlet is mainly affected by the complex flow phenomena such as the typical flow separation and reattachment and the suction vortex on the ground.When the inlet airflow When the separation occurs, the crosswind distortion will suddenly increase with the increase of the crosswind velocity. The ground suction vortices generated when the air inlet is near the ground may reduce the sidewind tolerance of the nacelle obviously.In addition, Distortion Characteristics of Intake Distortion With the change of engine flow rate, there is a difference between the separation and re-attachment of the airflow in the intake passage, which leads to a hysteresis variation in the distortion index of intake air.