中心锥锥角对涡喷发动机尾喷管气动性能影响规律研究
Study on the Effect of Center Cone Taper Angle on the Aerodynamic Performance of Tail Nozzle of Turbojet Engine

尾喷管是航空发动机的重要组成之一。随着航空发动机的发展，对尾喷管性能的要求越来越严格。本文针对尾喷管中心锥锥角进行参数化研究，旨在获得中心锥锥角对尾喷管性能的影响，以140 kg涡喷发动机尾喷管为研究对象，建立了三种具有不同中心锥锥角的尾喷管物理模型，并对其开展全粘性的数值模拟研究，与原模型进行对比分析，得出尾喷管中心锥锥角对尾喷管气动性能的影响规律：当中心锥锥角α在一定范围内降低时，尾喷管出口处的平均速度会升高，速度曲线更加平稳。因此，适当降低中心锥的锥角，将对尾喷管气动性能的提升提供一定的帮助。
The tail nozzle of aeroengine is an important component of turbojet engine. With the development of aeroengine performance, the requirements for the performance of the nozzle are more and more strict. It is of great significance to study the aerodynamic performance of the nozzle for the center cone. In this paper, in order to optimize the two protrusions, a 140 kg turbojet nozzle is taken as an example, three physical models of nozzles with different central cone angles were established, and the numerical simulation of the established nozzle was carried out, which was compared with the original model. The influence law of the central cone angle of the nozzle on the aerodynamic performance of the nozzle is obtained: when the central cone angle α decreases within an appropriate range, the average velocity at the nozzle exit will increase, the velocity curve will become more stable, and the fatigue strength will be higher in actual working conditions. Therefore, appropriately reducing the cone angle of the center cone is helpful to optimize the aerodynamic performance of the nozzle.