后侧穿越下起飞飞机发动机喷流数值模拟研究

Numerical Simulation of Jet Flow of Take-off Aircraft Based on Rear Runway Crossing Way of Take-off Aircraft

现阶段跑道穿越方式已经成为限制多跑道机场场面运行效率的主要因素之一,为了在保证安全水平的前提下有效地增加跑道容量,提升场面运行效率,提出起飞飞机后侧跑道穿越方式,确定了发动机内外流场的边界条件,对发动机喷流场进行数值模拟。研究发动机喷流影响距离是确定起飞飞机后侧穿越方式的重要前提,也是实施起飞飞机后侧穿越方式的首要条件。因此,分别采用SST以及SA湍流模型模拟研究了三维发动机喷管简化模型的喷流场,并验证了模型的可行性,同时研究了喷口出口较远距离的喷流场,确定了喷流的影响范围以及影响距离,可为机场进一步实施起飞飞机后侧穿越方式提供技术支持。

At present,the runway crossing method has become one of the main factors that limit the operating efficiency of multi-runway airport scenes.In order to effectively increase the capacity of the runway and improve the operating efficiency of the scene under the premise of ensuring the safety level,this study proposes a runway crossing mode at the rear of the take-off aircraft.The engine jet flow field is numerically simulated.The study of the impact distance of the jet of the engine is the prerequisite for determining the rear-side crossing mode of the take-off aircraft,and the first condition for implementing the rear-side crossing mode of the taking-off aircraft.Therefore,this article uses SST and SA turbulence models to numerically simulate the jet flow field of the simplified model of the three-dimensional engine nozzle,and compares it with the calculation results of references to verify the feasibility of the calculation method.The calculation results show that the SST and SA turbulence models are basically consistent with the calculation results of the reference,which can provide technical support for the airport to further implement the take-off aircraft rear side traversal method.