涡桨飞机进气道设计方法及性能研究

发布时间：2018-01-30 08:23

本文关键词： 单勺进气道环形截面设计方法可视化造型软件总压恢复系数总压畸变指数滑移网格螺旋桨滑流　出处：《南京航空航天大学》2016年硕士论文　论文类型：学位论文

【摘要】：上世纪70年代以来,螺旋桨飞机由于推进效率高和经济性好等优点而重新受到重视与发展。由于结构上的兼容性要求,使其进气道几何型面设计具有一定难度。结构特殊性加上螺旋桨滑流影响使进气道流场复杂化,因此快速参数化设计出性能良好的涡桨进气道具有重要意义。本文采用唇冠到唇脊变厚度唇口设计;基于环形截面方法设计主通道,设计几何特征参数沿通道变化规律,改造S型曲线公式以适用涡桨进气道中心线设计要求,提出扩展角采用Nurbs曲线变化规律。并根据单勺进气道设计算法,在Nussyppag体系下编程开发了单勺进气道可视化造型软件TurboPropInlet。针对设计马赫为0.5的单勺进气道模型,本文研究了几何参数对单勺进气道性能的影响,主要结论如下:唇脊收缩比对唇口设计性能影响大于唇冠收缩比;进出口偏距越大或喉道扩展角越大,出口总压畸变指数越大;主通道采用先扩张后收缩方式能很大程度上减小出口总压畸变指数。优选模型设计性能良好,设计状态下总压恢复系数为0.9864,总压畸变指数DC(60)?为0.0912。优选模型在较大流量范围和飞行马赫内性能良好;在小于?15的攻角和侧滑角范围内性能下降幅度小。上述研究结论对于涡桨进气道设计和性能分析有一定指导意义。本文最后基于滑移网格技术研究了低速起飞状态下滑流对涡桨进气道性能的影响,为以后深入进行螺旋桨滑流影响研究打下了一定基础。
[Abstract]:Since -30s, propeller aircraft has been revalued and developed because of its high propulsion efficiency and good economy. It is difficult to design the geometric plane of the inlet. The special structure and the influence of the propeller slip make the flow field of the inlet more complicated. Therefore, it is of great significance to design a fast parameterized impeller inlet with good performance. In this paper, the lip design from lip crown to lip ridge with variable thickness is adopted. The main passage is designed based on the annular section method. The variation law of geometric characteristic parameters along the channel is designed, and the S-shape curve formula is modified to meet the design requirements of the center line of the propeller inlet. The expansion angle is changed by Nurbs curve, and the algorithm is designed according to the single scoop inlet. The visual modeling software Turbo Prop Inlet is developed under the Nussyppag system. A single-scoop inlet model with Mach 0.5 is designed. The effects of geometric parameters on the performance of a single spoon inlet are studied in this paper. The main conclusions are as follows: the effect of lip ridge contraction ratio is greater than that of lip crown contraction ratio; The larger the deviation between the inlet and outlet or the larger the throat expansion angle, the greater the total pressure distortion index of the outlet. The main channel can reduce the total pressure distortion index to a great extent by first expanding and then contracting. The optimal selection model has good design performance and the total pressure recovery coefficient is 0.9864 in the design state. Total pressure distortion index DCU 60? The optimal selection model has good performance in large flow range and flight Mach. The results above are helpful for the design and performance analysis of the propeller inlet. Finally, based on the sliding grid technique, the paper studies the low-speed take-off state based on the slip-grid technique, which is helpful to the design and performance analysis of the propeller inlet in the range of the angle of attack and the sideslip angle. The influence of slip flow on the performance of propeller inlet. It lays a foundation for further research on the influence of propeller slip flow.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V211.48

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