扩张段射流对旁路式双喉道喷管矢量特性的影响研究

夏雪峰; 高峰; 张倩; 马岑睿

doi:10.7638/kqdlxxb-2020.0070

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扩张段射流对旁路式双喉道喷管矢量特性的影响研究

研究论文 | 更新时间：2026-05-28

- 扩张段射流对旁路式双喉道喷管矢量特性的影响研究
- Investigation on the vector performance of a bypass dual throat nozzle with injection at the divergent section
- 空气动力学学报 2021年39卷第4期页码：51-58
- 作者机构：
  
  空军工程大学防空反导学院,西安,710051
- 作者简介：
  
  夏雪峰*（1992-），男，四川遂宁人，助教，研究方向：航空宇航推进理论与技术. E-mail：xxfair@163.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2020.0070
  中图分类号： V233.7+57
- 纸质出版：2021
- 稿件说明：
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夏雪峰, 高峰, 张倩, 等. 扩张段射流对旁路式双喉道喷管矢量特性的影响研究[J]. 空气动力学学报, 2021, 39(4): 51−58.

XIA Xuefeng, GAO Feng, ZHANG Qian, et al. Investigation on the vector performance of a bypass dual throat nozzle with injection at the divergent section[J]. 2021, 39(4): 51-58.
夏雪峰, 高峰, 张倩, 等. 扩张段射流对旁路式双喉道喷管矢量特性的影响研究[J]. 空气动力学学报, 2021, 39(4): 51−58. DOI： 10.7638/kqdlxxb-2020.0070

XIA Xuefeng, GAO Feng, ZHANG Qian, et al. Investigation on the vector performance of a bypass dual throat nozzle with injection at the divergent section[J]. 2021, 39(4): 51-58. DOI： 10.7638/kqdlxxb-2020.0070.

摘要

为探究腔体扩张段射流对旁路式双喉道喷管气动矢量特性的影响，采用数值模拟方法对喷管在不同次流入射位置和次流压比下的内流情况进行仿真研究。结果表明：在扩张段引入次流能够改善喷管内流性能，随着次流入射位置后移，推力矢量角先增大后减小，推力系数逐渐增大且增幅渐缓；随着次流压比增加，喷管推力矢量角逐渐增加后基本保持不变，推力系数先增加后快速下降，而矢量效率先急剧上升后趋于平稳；改进后的喷管在最佳算例中得到推力矢量角为27.59°，推力系数为0.956，矢量效率3°/1%次流流量。

Abstract

The bypass dual throat nozzle (BDTN) is a new type of dual-throat fluidic thrust-vectoring nozzle

which introduces secondary flows by a bypass set between the upstream minimum area and the upstream convergent section. The BDTN can achieve a good thrust vectoring performance without setting complex secondary-flow channels in the engine. Numerical studies were performed to analyze the thrust-vectoring performances of a BDTN with injections at the divergent section under different injection locations and secondary pressure ratios. The main results show that the BDTN with injection at the divergent section can improve the thrust-vectoring performances. With the injection location moving backward

the thrust vector angle increases first and then decreases

while the thrust ratio increases slowly. The secondary pressure ratio rise makes the thrust vector angle and efficiency increase to constant values. But it can lead to a thrust loss when it is larger than a certain value. For the optimal case of the modified BDTN

the thrust vector angle and thrust ratio respectively reach 27.59 degree and 0.956

yielding a vector efficiency of 3°/1% per rate of secondary flow

which indicates that the modified nozzle can achieve a fine thrust vectoring performance.

关键词

Keywords

references

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