超燃燃烧室肋片/凹腔组合结构研究

杨文佳; 高峰; 王应洋; 马新鹏

doi:10.15892/j.cnki.djzdxb.2019.01.024

弹箭与制导学报 >

2019 , Vol. 39 >Issue 1: 113 - 118,124

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2019.01.024

超燃燃烧室肋片/凹腔组合结构研究

杨文佳 ,
高峰 ,
王应洋 ,
马新鹏

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空军工程大学,西安 710051

杨文佳(1995-),男,湖南邵阳人,硕士研究生,研究方向:宇航推进理论。

收稿日期: 2018-03-19

网络出版日期: 2025-05-21

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Study on Pylon/cavity Combination in a Supersonic Combustion

YANG Wenjia ,
GAO Feng ,
WANG Yingyang ,
MA Xinpeng

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Air Force Engineering University, Xi'an 710051, China

Received date: 2018-03-19

Online published: 2025-05-21

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摘要

为进一步了解超燃冲压发动机内流特性,优化燃烧室流场,文中运用数值模拟方法在冷流条件下对比分析了肋片/凹腔结构不同组合距离对流场的影响。研究发现:肋片结构的加入能较大提升射流穿透深度,增强掺混,同时不会带来较大总压损失;组合距离越小,对燃料的掺混扩散更有利,凹腔的稳焰能力也更强,却带来更大的总压损失;综合考虑,肋片与凹腔组合距离为6d时,燃料穿透深度、混合效率更好,总压损失也相对较小。

关键词： 超燃燃烧室; 肋片; 凹腔; 数值模拟

本文引用格式

杨文佳 , 高峰 , 王应洋 , 马新鹏 . 超燃燃烧室肋片/凹腔组合结构研究[J]. 弹箭与制导学报, 2019 , 39(1) : 113 -118,124 . DOI: 10.15892/j.cnki.djzdxb.2019.01.024

Abstract

The numerical simulation has been carried out to investigate the cold flow characteristics for mixing efficiency and flame stability of the composite structure of pylon and cavity in the supersonic combustion. The different combination distance of pylon /cavity structure has been comparative analyzed and investigated. It is noted that the pylon can increase the penetration depth of the jet and mixing efficiency, and it won't lead to a higher total pressure loss. The decrease of combination distance enhances the blending and improves the flame stability, but also increase the total pressure loss. Moreover, the distance between pylon and injector of 6d is recommended regarding high mixing efficiency and less total pressure loss.

Key words： supersonic combustion; pylon; cavity; numerical simulation

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参考文献

[1]	徐旭, 陈兵, 徐大军. 冲压发动机原理及技术[M]. 北京: 北京航空航天大学出版社, 2014: 175－200．
[2]	蔡国彪, 徐大军. 高超声速飞行器技术[M]. 北京: 科学出版社, 2012: 77－95．
[3]	俞刚, 范学军. 超声速燃烧与高超声速推进[J]. 力学进展, 2013, 43(5): 449－472．
[4]	张岩, 李崇香, 韦宝禧, 等. 超燃冲压发动机燃料喷注方案综述[J]. 飞航导弹, 2014(2): 61－67．
[5]	高峰, 王宏宇, 张涵. 超燃冲压发动机燃烧室流场数值分析研究综述[J]. 飞航导弹, 2014(1): 80－84 [6]黄伟, 覃慧, 罗世彬, 等. 激波诱燃冲压发动机关键技术研究[J]. 中国科学: 技术科学, 2010, 40(1): 64－70．
[7]	ROSE S K, HARTFIELD R. Experiment and analytical investigation of injection behind a pylon in a compressible flow: AIAA Paper 96-0918 [R]．[S. l.]: AIAA, 1996．
[8]	MONTES D R, KING P I, GRUBER M R, et al. Mixing effects of pylon-aided fuel injection located upstream of a flameholding cavity in supersonic flow: AIAA 2005-3913 [R]．[S. l.]: AIAA, 2005．
[9]	POHLMAN M R, GREENDYKE R B. Parametric analysis of pylon-aided fuel injection in scramjet engine[J]. Journal of Engineering for Gas Turbines and Power, 2013, 135(2): 024501-1—024501-5．
[10]	AGUILERA C, PANG B, GHOSH A, et al. Scramjet mixing control using fin-guided fuel injection: AIAA 2009－5415 [R]．[S. l.]: AIAA, 2009．
[11]	AGUILERA C, PANG B, A, et al. Supersonic mixing enhancement and optimization using fin-guided fuel injection: AIAA 2010-1526 [R]．[S. l.]: AIAA, 2010．
[12]	AGUILERA C, YU K H, GUPTA A K. Fin-guided liquid fuel injection into Mach 2. 1 airflow: AIAA 2011-5763 [R]．[S. l.]: AIAA, 2011．
[13]	GRUBER M R, CARTER C D, MONTES D R, et al. Experimental studies of pylon-aided fuel injection into a supersonic crossflow[J]. Journal of Propulsion and Power, 2008, 24(3): 460－470．
[14]	POHLMAN M R, GREENDYKE R B. Parametric analysis of pylon-aided fuel injection in scramjet engines[J]. Journal of Engineering for Gas Turbines and Power, 2013, 135(2): 24501-01—024501-5．
[15]	BALAR R, YU K, GUPTA A, et al. Pylon-aided fuel injection into supersonic flow: AIAA 2007-834[R]．[S. l.]: AIAA, 2007．
[16]	金劲睿,刘玉英,洪燕. 前置肋片对凹槽火焰稳定器混合特性的影响[J]. 航空动力学报, 2011. 26 (12): 2716- 2721.
[17]	王应洋,李旭昌,王宏宇,等. 超燃燃烧室肋片构型数值研究. 固体火箭技术, 2016, 39 (1): 28– 35.
[18]	张弯洲,乐嘉陵,田野,等. 超燃发动机混合效率评估方法探讨. 航空动力学报, 2012, 27 (9): 1958– 1966.

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