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为克服双喉道射流矢量喷管矢量角偏小的缺点,提出了一种矢量增强型双喉道矢量喷管的设计概念:在喷管尾部增加一扩张段,利用流体的附壁效应使主流在扩张段中进一步偏转,从而获取更大的矢量角.首先对设计概念的可行性进行了仿真分析,而后对扩张段的设计规律进行了研究.结果表明,在喷管尾部附加扩张段可显著强化其推力矢量性能,使矢量角达到20°以上,但也导致了一定的推力损失.在研究范围内,扩张段扩张角、扩张段长度、扩张段型线等设计参数对喷管的矢量效率、推力系数以及内部流态均有着显著影响,而在扩张段开缝则可以作为一种抑制尾喷流过膨胀的有效措施.若将内凹型扩张段与开缝方案相结合,仅需消耗2.8%的次流便可获得24.12°的推力矢量角和0.929的推力系数.
In order to overcome the shortcoming of vector angle of double throat jet vector nozzle, a design concept of vector enhanced double throat vector nozzle is proposed: adding an expansion segment at the end of the nozzle, making use of the Coanda effect of the fluid to make the mainstream And further deflected in the dilatation segment to obtain a larger vector angle.Firstly, the feasibility of the design concept was simulated and then the design rule of the dilatation segment was studied.The results show that the dilatation segment can be significantly increased at the end of the nozzle Strengthen its thrust vector performance, and make the vector angle reach more than 20 °, but also lead to a certain thrust loss.In the research scope, the expansion efficiency of expansion nozzle, expansion length, , The thrust coefficient and the internal flow state have a significant impact, and in the expansion of the section of the slot can be used as an inhibition of tail jet flow through the expansion of the effective measures.If the concave expansion section and the combination of slotting scheme, only 2.8 % Of the second stream will be able to get the thrust vector angle of 24.12 ° and the thrust coefficient of 0.929.