横向侧风及反推气流对安装状态下发动机进口流场影响的数值研究

目的探究横向侧风及反推气流对大涵道比涡扇发动机进口流场的影响。方法采用CFD手段模拟飞机滑跑着陆过程中反推力装置打开后的全机三维流场,获得不同横向侧风风速下反推气流的扰流流场细节。结果相对来流马赫数越小,反推气流越容易被发动机吸入,横向侧风风速的增加,进一步加大了被发动机吸入的可能性。在侧风的作用下,反推气流对远离侧风来流一侧的两台发动机影响更严重,随着横向侧风风速的增大,远离侧风来流一侧的发动机进口截面上的周向总压畸变和总温畸变程度基本上是逐渐增大的,其中最大值约变为平均值的4倍。结论通过研究获得的飞机受到侧风时的反推状态下发动机进口流场细节及流场畸变情况可以为飞机进气畸变实验工作奠定技术基础。

Numerical Investigation on Influence of Vertical Crosswind and Reverser Flow to Engine Inlet Flow Field under Installation

The work aims to investigate the influence of vertical crosswind and reverser flow on the inlet flow field of high bypass ratio turbofan engine. Computational fluid dynamics (CFD) technology was used to simulate the 3D flow field of the whole aircraft after the thrust reverser is opened during landing. The detailed flow field information of the reverser flow under different vertical crosswind speeds during the landing process of the aircraft was obtained. The smaller the relative flow Mach number, the easier the reverser flow was ingested by the engine. The increase of the crosswind speed further increased the possibility of being sucked by the engine. Under the action of crosswind, the two engines far from the side of the crosswind were more seriously affected by the reverser flow. As the crosswind speed increased, the circumferential total pressure distortion and total temperature distortion of the engine inlet section away from the side of the crosswind was gradually increasing. The maximum total pressure distortion became about 4 times the average value. The details of engine inlet flow field and the distortion of aircraft under reverse thrust conditions and crosswind can lay a technical foundation for distortion experiment of aircraft.