高焓激波风洞超燃冲压发动机高频OH-PLIF燃烧诊断

袁勋; 于欣; 彭江波; 卢洪波; 杨超博; 曹振; 陈勇富; 纪锋; 文帅; 张善春

doi:10.13224/j.cnki.jasp.20240647

高焓激波风洞超燃冲压发动机高频OH-PLIF燃烧诊断

doi: 10.13224/j.cnki.jasp.20240647

袁勋^{1, 2},
于欣^{1, 2},
彭江波^{1, 2,*, ,},
卢洪波³,
杨超博^{1, 2},
曹振^{1, 2},
陈勇富³,
纪锋³,
文帅³,
张善春^{1, 2}

1.
哈尔滨工业大学航天学院激光空间信息全国重点实验室，哈尔滨 150001
2.
哈尔滨工业大学光电子技术研究所，哈尔滨 150001
3.
中国航天空气动力技术研究院，北京 100074

基金项目: 国家自然科学基金（62175053，62305087）

详细信息

作者简介:
袁勋（1997-），男，博士，研究方向为高焓非平衡流光学诊断

通讯作者:
彭江波（1981-），男，研究员，博士，研究方向为光电子器件与激光燃烧诊断。E-mail：pengjiangbo@hit.edu.cn

中图分类号: V235.21
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- 被引次数: 0
出版历程
- 收稿日期: 2024-09-18
- 网络出版日期: 2026-02-28

Combustion diagnosis of ramjet in high-enthalpy shock tunnel using high-speed OH-PLIF

YUAN Xun^{1, 2},
YU Xin^{1, 2},
PENG Jiangbo^{1, 2,*
, ,},
LU Hongbo³,
YANG Chaobo^{1, 2},
CAO Zhen^{1, 2},
CHEN Yongfu³,
JI Feng³,
WEN Shuai³,
ZHANG Shanchun^{1, 2}

1.
National Key Laboratory of Laser Spatial Information，School of Astronautics，Harbin Institute of Technology，Harbin 150001，China
2.
Institute of Opt-electronics，Harbin Institute of Technology，Harbin 150001，China
3.
China Academy of Aerospace Aerodynamics，Beijing 100074，China

摘要

摘要:
针对高马赫数超燃冲压发动机高频PLIF（planar laser-induced fluorescence，平面激光诱导荧光）燃烧诊断研究空缺问题，研制了高焓激波风洞高频PLIF测量系统，并在自由活塞驱动高焓激波风洞上首次开展了名义马赫数10飞行模拟条件下超燃冲压发动机高频OH-PLIF燃烧诊断试验，分别获得了乙烯喷注和氢气喷注下燃烧室OH-PLIF时间序列图像。通过对比背景图像发现试验气在风洞起动8 ms左右时到达发动机流道，火焰中OH基靠近唇罩一侧分布，且在矩形流道中观测到了与压缩面一侧的凹腔后缘相平行的激波结构；相较于乙烯喷注，氢气喷注时风洞起动3 ms左右的烧蚀会提前将氢气点燃，进而产生近似全场均匀分布的火焰；上述结果与燃烧室压力数据具有较好一致性。
- 高马赫数超燃冲压发动机 /
- 超声速燃烧 /
- 高焓激波风洞 /
- 平面激光诱导荧光 /
- 乙烯 /
- 氢气
Abstract:
To address the research gap in high-frequency Planar Laser-Induced Fluorescence (PLIF) combustion diagnostics for high-Mach number scramjet engines, a high-enthalpy shock tunnel high-frequency PLIF measurement system was developed. For the first time, high-frequency OH-PLIF combustion diagnostic tests were conducted under nominal Mach 10 flight simulation conditions in a free piston-driven high-enthalpy shock tunnel. Time series images of OH-PLIF in the combustion chamber were obtained for both ethylene and hydrogen injection cases. By comparing the background images, it was observed that the test gas reached the engine flow path approximately 8ms after the tunnel startup for ethylene injection. The OH in the combustion flame was found to be distributed closer to the cowl side, and shock wave structures parallel to the rear edge of the cavity on the compression side were observed within the rectangular flow path. Compared with ethylene injection, hydrogen injection resulted in earlier ignition around 3ms after tunnel startup due to the ablation effect, leading to a flame distribution that was nearly uniform across the entire field. These findings were in good agreement with the combustion chamber pressure data.
- high Mach number scramjet /
- supersonic combustion /
- high-enthalpy shock tunnel /
- planar laser-induced fluorescence /
- ethylene /
- hydrogen

HTML

图 1 超燃冲压发动机示意图

Figure 1. Schematic diagram of the scramjet

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图 2 PLIF系统示意图

Figure 2. Schematic diagram of PLIF system

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图 3 激光系统环境控制平台

Figure 3. Environmental control platform of laser system

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图 4 时序控制图

Figure 4. Synchronization sequence diagram

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图 5 背景图像

Figure 5. Background images

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图 6 乙烯喷注时燃烧室OH-PLIF图像和压力曲线

Figure 6. OH-PLIF images and pressure curve of combustion chamber during ethylene injection

下载: 全尺寸图片幻灯片

图 7 氢气喷注时燃烧室OH-PLIF图像和压力曲线

Figure 7. OH-PLIF images and pressure curve of combustion chamber during hydrogen injection

下载: 全尺寸图片幻灯片

表 1 试验工况

Table 1. Experimental conditions

Ma_∞	p_∞/Pa	R_∞/10⁻³ （kg/m³）	T_∞/K	T_vib,∞/K	U_∞/（m/s）	$ {C}_{{{\text{N}}_{\text{2}}},\mathrm{\infty }} $/%	$ {C}_{{{\text{O}}_{\text{2}}},\mathrm{\infty }} $/%	C_NO,∞/%	C_O,∞/%	C_N,∞/%
9.50	375	4.60	283	1590	3107	73.93	19.95	5.96	0.16	0

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