二元收扩喷管设计参数对气动性能影响的数值研究

发布时间：2019-04-23 09:07

【摘要】：采用正交试验设计方法进行喷管气动性能数值模拟算例的设计,综合研究了二元收扩喷管8个设计参数对气动性能的影响,研究的设计参数包括圆到矩超椭圆型面过渡段几何参数(长径比、横截面积变化率、长半轴变化率、短半轴变化率)和主喷管段几何参数(喉部宽高比、喉部型面半径比、收敛半角、扩张半角),并且对喉部宽高比、喉部型面半径比、收敛半角、扩张半角等4个参数对喷管气动性能影响的灵敏度进行了分析.结果表明:喉部型面半径比R_w/R_8是二元收扩喷管气动性能影响的最主要参数,因此在喷管设计中应尽量增大R_w/R_8,尤其是在收敛半角α较大时,增大R_w/R_8可使喷管气动性能明显增大;喉部宽高比不是二元收扩喷管气动性能影响的主要参数;二元收扩喷管的气动性能几乎与过渡段型面无关.
[Abstract]:The numerical simulation example of nozzle aerodynamic performance is designed by using orthogonal test design method. The influence of eight design parameters on aerodynamic performance of binary expansion nozzle is comprehensively studied. The design parameters include geometric parameters of transition section of circle to moment superellipse surface (length-diameter ratio, cross-sectional area change rate, long half-axis change rate, short half-axis change rate) and main nozzle section geometry parameters (throat width-height ratio, throat surface radius ratio), and the main nozzle section geometry parameters (throat width-height ratio, throat surface radius ratio). The sensitivity of four parameters, I. E., width to height ratio of throat, radius ratio of throat profile, convergence half angle and expansion half angle, on the aerodynamic performance of nozzle is analyzed. The results show that the ratio of throat to surface radius (R_w/R_8) is the most important parameter affecting the aerodynamic performance of the two-dimensional nozzle. Therefore, in the nozzle design, R _ (w) R _ (?) 8 should be increased as much as possible, especially when the convergence angle 伪 is large. The aerodynamic performance of nozzle can be obviously increased by increasing R_w/R_8. The ratio of throat width to height is not the main parameter affecting the aerodynamic performance of the binary nozzle, and the aerodynamic performance of the binary nozzle is almost independent of the transition section profile.
【作者单位】：南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室;
【分类号】：V231

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