Preliminary study on combustion performance of dual-mode scramjet engine

TIAN Ye; XIAO Bao-guo; ZHANG Shun-ping; XING Jian-wen

doi:10.13224/j.cnki.jasp.2016.12.013

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Preliminary study on combustion performance of dual-mode scramjet engine

更新时间：2026-07-07

- Preliminary study on combustion performance of dual-mode scramjet engine
- Vol. 31, Issue 12, Pages: 2921-2927(2016)
- 作者机构：
  
  中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室,四川,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2016.12.013
  CLC：
- Published：2016
- 稿件说明：
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田野, 肖保国, 张顺平, 邢建文. 双模态冲压发动机燃烧性能初步研究[J]. 航空动力学报, 2016, 31(12): 2921-2927.

doi: 10.13224/j.cnki.jasp.2016.12.013
田野, 肖保国, 张顺平, 邢建文. 双模态冲压发动机燃烧性能初步研究[J]. 航空动力学报, 2016, 31(12): 2921-2927. DOI： 10.13224/j.cnki.jasp.2016.12.013.

doi: 10.13224/j.cnki.jasp.2016.12.013 DOI：

摘要

通过数值模拟和地面试验研究了当量比和注油分布对双模态冲压发动机燃烧性能的影响，结果表明：在隔离段入口马赫数为2.0，总温为1100K，总压为1MPa的来流条件下，总当量比为0.6时，燃烧模态为双模态亚燃，热力喉道位置位于凹槽出口处；总当量比大于0.6时，发动机燃烧模态为亚燃，热力喉道位置相同，流场结构稳定.通过选取压力参考点的方法，发展了发动机推力快速分析方法，误差较小.

Abstract

The effect of equivalence ratio and fuel distribution on combustion performance of the dual-mode scramjet engine was investigated by numerical simulation and experiments. Results showed that

under the inflow condition with Mach number of 2.0

total temperature of 1100K

and total pressure of 1.0MPa. When the total equivalence ratio was 0.6

the combustion mode was dual-mode subsonic combustion

the thermal throat was at the exit of the cavity. When the total equivalence ratio was larger than 0.6

the combustion mode was subsonic combustion

the thermal throat was at the same location in different cases. The flow structure of this dual-mode scramjet was stable under subsonic combustion mode. The fast thrust analysis method is created by choosing pressure reference points is developed

the error of this method is rather small.

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