双支板超燃冲压发动机燃烧特性研究

纪鹏飞; 徐旭; 陈兵; 朱韶华; 刘刚

doi:10.13700/j.bh.1001-5965.2016.0097

双支板超燃冲压发动机燃烧特性研究

doi: 10.13700/j.bh.1001-5965.2016.0097

北京航空航天大学宇航学院, 北京 100083

基金项目:

国家自然科学基金 51276007

详细信息

作者简介:
纪鹏飞, 男, 硕士研究生。主要研究方向:超燃冲压发动机技术

徐旭, 男, 博士, 教授。主要研究方向:超燃冲压发动机技术

通讯作者:
徐旭, E-mail:xuxu@buaa.edu.cn

中图分类号: V235.123
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出版历程
- 收稿日期: 2016-01-26
- 录用日期: 2016-03-25
- 网络出版日期: 2017-02-20

Combustion performance investigation of a dual-struts scramjet

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

Funds:

National Natural Science Foundation of China 51276007

More Information

Corresponding author: E-mail:xuxu@buaa.edu.cn

摘要

摘要:
为研究分级喷注超燃冲压发动机火焰稳定、燃烧状态及火焰传播特性，以双支板超燃燃烧室为基本构型，开展了当量比连续调节试验研究。模拟低飞行马赫数5.5工况，燃烧室入口马赫数为2，总温1 436 K，试验表明：燃烧室单独上游喷注熄火当量比为0.19，该值不受下游燃烧的影响；单独下游喷注熄火当量比为0.46，上游火焰会削弱下游当量比变化对壁面压力的影响，并且会使下游熄火当量比值降低。通过调节上游当量比可实现燃烧状态的转换，转换过程存在迟滞。模拟高飞行马赫数6.5工况，燃烧室入口马赫数为3，总温1 899 K，试验表明：随着总温的增加，单独上游喷注可实现点火和稳焰，上游火焰发生抬举，燃烧室抗反压能力增强，可喷注更多燃料。
- 超燃冲压发动机 /
- 燃烧 /
- 支板 /
- 当量比 /
- 迟滞
Abstract:
In order to investigate the flame stabilization, combustion state and flame propagation characteristics of scramjet, based on a dual-struts supersonic combustor with staged injections, experiments with continuously adjusted equivalence ratio were conducted. Experiments with combustor inlet Mach number of 2 and total temperature of 1 436 K were conducted to simulate flight Mach number of 5.5. The results show that when injecting fuel is solely from the upstream strut, the extinction equivalence ratio is 0.19 and it is not affected by the downstream combustion. When injecting fuel is solely from the downstream strut, the extinction equivalence ratio is 0.46, and the effect of downstream equivalence ratio change on wall pressure would be reduced by upstream flame, with which the extinction equivalence ratio would be decreased. Transformation between two combustion states could be realized by adjusting the upstream equivalence ratio, and hysteresis could be observed in the transformation process. Experiments with combustor inlet Mach number of 3 and total temperature of 1 899 K were conducted to simulate flight Mach number of 6.5. The results show that as the total temperature of incoming flow increases, ignition and stable flame can be realized by fuel injection solely at the upstream strut, the upstream flame is lifted, back-pressure capability of the combustor can be strengthened, and more fuel can be injected into the flow.
- scramjet /
- combustion /
- strut /
- equivalence ratio /
- hysteresis

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图 1 燃烧室、支板和观察窗结构

Figure 1. Configurations of combustion chamber, struts and inspection window

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图 2 可调文氏管结构

Figure 2. Structure of adjustable venturi

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图 3 可调文氏管流量

Figure 3. Mass flow rate of adjustable venturi

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图 4 Case 1不同上游当量比壁面压力分布

Figure 4. Wall pressure distribution of Case 1 with different upstream equivalence ratios

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图 5 Case 1不同上游当量比马赫数分布

Figure 5. Mach number distribution of Case 1 with different upstream equivalence ratios

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图 6 Case 2特征点压力随时间的变化

Figure 6. Time history of feature points pressure of Case 2

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图 7 Case 2不同下游当量比壁面压力分布

Figure 7. Wall pressure distribution of Case 2 with different downstream equivalence ratios

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图 8 Case 4和Case 1不同上游当量比壁面压力分布

Figure 8. Wall pressure distribution of Case 4 and Case 1 with different upstream equivalence ratios

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图 9 Case 5文氏管后压力随时间的变化

Figure 9. Case 5 time history of pressure after venturi

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图 10 Case 5特征点压力随时间的变化

Figure 10. Case 5 time history of feature points pressure

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图 11 Case 5不同下游当量比壁面压力分布

Figure 11. Wall pressure distribution of Case 5 with different downstream equivalence ratios

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图 12 Case 6文氏管后压力随时间的变化

Figure 12. Time history of pressure after venturi of Case 6

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图 13 Case 6特征点压力随时间的变化

Figure 13. Time history of feature points pressure of Case 6

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图 14 上游火焰瞬态图像(Δt=0.5 ms)

Figure 14. Transient image of upstream flame (Δt=0.5 ms)

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图 15 数值模拟边界层分离区

Figure 15. Separation zone of boundary layer in simulation

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图 16 Case 6不同上游当量比壁面压力分布

Figure 16. Wall pressure distribution of Case 6 with different upstream equivalence ratios

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图 17 Case 7不同上游当量比壁面压力分布

Figure 17. Wall pressure distribution of Case 7 with different upstream equivalence ratios

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表 1 入口参数

Table 1. Inlet parameters

入口参数类别	总质量流量/ (kg·s^-1)	模拟飞行马赫数	马赫数	总温/K	总压/MPa
a	2.655	5.5	2.0	1 436	0.78
b	2.044	6.5	3.0	1 899	2.13

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表 2 试验工况

Table 2. Experiment condition

工况	入口参数类别	上游当量比(线性匀速调节)	下游当量比(线性匀速调节)	当量比调节时间/s
Case 1	a	0.3减少至0.1	0.7	3
Case 2	a	0	0.6减少至0.3	2
Case 3	a	0.3减少至0.1	0	3
Case 4	a	0.3减少至0.1	0.6，点火后变至0	3
Case 5	a	0.4	0.6减少至0.3，再增加至0.6	2.4
Case 6	a	0.4减少至0.1，再增加至0.4	0.7	2.4
Case 7	b	0.5减少至0.3，再增加至0.5	0	2.4

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