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| Numerical Investigation on Influence of Vertical Crosswind and Reverser Flow to Engine Inlet Flow Field under Installation |
| Received:May 25, 2020 Revised:July 06, 2020 |
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| DOI：10.7643/issn.1672-9242.2020.11.014 |
| KeyWord:high bypass ratio turbofan engine thrust reverser vertical crosswind numerical simulation total pressure distortion |
| Author | Institution |
| DAI Xiao-qiang |
Southwest Technology and Engineering Research Institute, Chongqing , China |
| ZHANG Yun |
Southwest Technology and Engineering Research Institute, Chongqing , China |
| HUANG Qiang |
Southwest Technology and Engineering Research Institute, Chongqing , China |
| XIE Lan-chuan |
Southwest Technology and Engineering Research Institute, Chongqing , China |
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| Abstract: |
| 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. |
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