喷注位置对RBCC释热特性及发动机性能的影响

于洋; 方哲; 范健; 裴金亮; 李宇飞

doi:10.13224/j.cnki.jasp.20250571

喷注位置对RBCC释热特性及发动机性能的影响

doi: 10.13224/j.cnki.jasp.20250571

中国航天科技集团有限公司北京宇航系统工程研究所，北京 100076

详细信息

作者简介:
于洋（1998-），男，博士生，主要研究方向为组合动力技术。E-mail：yyzy1998@buaa.edu.cn

通讯作者:
范健（1983-），男，研究员，博士，主要研究方向为动力系统总体设计。E-mail：fanjian0116@163.com

中图分类号: V438
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出版历程
- 收稿日期: 2025-12-08
- 网络出版日期: 2026-05-15

Influence of injection position on heat release characteristics and engine performance of the RBCC

Beijing Institute of Astronautical Systems Engineering，China Aerospace Science and Technology Corporation，Beijing 100076，China

摘要

摘要:
针对来流马赫数为6条件下的RBCC发动机释热特性开展数值模拟研究，结合对数化处理与滤波函数等手段，对比分析了喷注位置对流动特征、释热分布、燃烧模式及发动机性能的影响。研究表明，喷注位置前移会使激波串起点向上游移动，流道高压区分布随之扩大，整体压力水平显著提高；同时，可增大燃烧反应区体积，提高总释热量，并使集中释热区向上游移动；此外，喷注前移通过减小释热对应的流道面积来提高释热峰值，但燃料支板诱导的激波因其减速增压效应对局部释热增强更为显著。研究还发现，各喷注位置工况均以扩散燃烧与亚声速燃烧模式占优，而隔离段凹腔上游喷注可提高预混燃烧比例，中心支板侧壁喷注更有利于提高超声速燃烧比例。在研究范围内，前移喷注可有效提升燃烧效率、推力及比冲，于隔离段凹腔上游进行喷注可获得最优发动机性能。
- 火箭基组合循环 /
- 喷注位置 /
- 释热特性 /
- 燃烧模式 /
- 发动机性能
Abstract:
Numerical simulations are conducted to investigate the heat release characteristics of an RBCC engine under freestream Mach number 6 conditions. The influence of fuel injection position on flow feature, heat release distribution, combustion mode, and engine performance were analyzed with the aid of logarithmic processing and filter functions. Results showed that moving the injection position upstream shifted the shock train leading edge forward, expanded the high-pressure zone within the flow path, and significantly increased the overall pressure level. It also enlarged the combustion reaction zone, increased the total heat release, and shifted the concentrated heat release region upstream. Furthermore, upstream injection increased the peak heat release rate by reducing the corresponding cross-sectional area, although the shock induced by the fuel strut contributed more significantly to local heat release enhancement via its compression effect. All tested injection positions exhibited dominant diffusion and subsonic combustion modes. Injection upstream of the isolator cavity increased the proportion of premixed combustion, while injection of the central strut sidewall was more conducive to supersonic combustion. Within the studied range, upstream injection effectively improved combustion efficiency, thrust, and specific impulse, with injection upstream of the isolator cavity yielding the optimal engine performance.
- RBCC /
- injection position /
- heat release characteristics /
- combustion mode /
- engine performance

HTML

图 1 RBCC发动机构型图

Figure 1. Configuration of RBCC engine

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图 2 壁面压力的试验与数值模拟结果对比

Figure 2. Comparison of experimental and numerical results for wall pressure

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图 3 网格无关性验证

Figure 3. Grid independence analysis

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图 4 不同喷注位置下对数化密度梯度云图（左）和马赫数云图（右）

Figure 4. Logarithmic density gradient contours （left） and Mach number contours （right) with different injection positions

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图 5 不同喷注位置下平均归一化压力轴向分布

Figure 5. Axial distribution of average normalized pressure with different injection positions

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图 6 不同喷注位置下平均马赫数轴向分布

Figure 6. Axial distribution of average Mach number with different injection positions

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图 7 不同喷注位置下对数化释热率云图

Figure 7. Logarithmic heat release rate contours with different injection positions

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图 8 不同喷注位置下释热通量轴向分布

Figure 8. Axial distribution of heat release flux with different injection positions

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图 9 不同喷注位置下扩散燃烧释热通量轴向分布

Figure 9. Axial distribution of diffusion combustion heat release flux with different injection positions

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图 10 不同喷注位置下预混燃烧释热通量轴向分布

Figure 10. Axial distribution of premixed combustion heat release flux with different injection positions

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图 11 不同喷注位置下亚声速燃烧释热通量轴向分布

Figure 11. Axial distribution of subsonic combustion heat release flux with different injection positions

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图 12 不同喷注位置下超声速燃烧释热通量轴向分布

Figure 12. Axial distribution of supersonic combustion heat release flux with different injection positions

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表 1 来流入口参数

Table 1. Inflow parameters

马赫数	空气流率/（kg/s）	总温/K	总压/MPa
2.6	2.50	1660	1.37

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表 2 不同工况的燃料喷注位置

Table 2. Fuel injection positions for different cases

工况	当量比	喷注位置
Case 1	1.0	A：隔离段凹腔上游10 mm
Case 2	1.0	B：中心支板末端上游15 mm
Case 3	1.0	C：燃料支板前缘侧壁中心处

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表 3 煤油三步简化动力学

Table 3. Three-step reduced chemical kinetics for kerosene

反应	A/ （cm³/（mol·s））	E_a/ （J/（kmol））	β
C₁₀H₁₆+5O₂=10CO+8H₂	2.35×10⁴	1.633×10⁸	1
2CO+O₂=2CO₂	3.48×10⁸	8.42×10⁷	2
2H₂+O₂=2H₂O	3.0×10¹⁷	0	−1

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表 4 不同喷注位置下燃烧反应区体积与总释热量

Table 4. Volume of reaction zone and total heat release with different injection positions

工况	V_react /m³	Q_total /W
Case 1	5.86e-02	6.74e+06
Case 2	5.38e-02	5.89e+06
Case 3	4.39e-02	5.76e+06

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表 5 不同喷注位置下扩散燃烧与预混燃烧模式占比

Table 5. Proportion of diffusion and premixed combustion modes with different injection positions

工况	ξ_d/%	ξ_p/%	η_d/%	η_p/%
Case 1	86.9	13.1	77.7	22.3
Case 2	93.6	6.4	83.0	17.0
Case 3	93.9	6.1	81.3	18.7

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表 6 不同喷注位置下亚声速燃烧与超声速燃烧模式占比

Table 6. Proportion of subsonic and supersonic combustion modes with different injection positions

工况	ξ_sub/%	ξ_sup/%	η_sub/%	η_sup/%
Case 1	31.1	68.9	81.7	18.3
Case 2	24.2	75.8	55.1	44.9
Case 3	21.0	79.0	67.9	32.1

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表 7 不同喷注位置下发动机性能

Table 7. Engine performance with different injection positions

工况	η_c/%	T_Inlet /N	T_Isolator /N	T_Combustor /N	T_Nozzle /N	T_Engine /N	I_sp /s
Case 1	91.6	−447.1	320.3	946.9	684.8	1505.1	900.3
Case 2	80.1	−447.1	−93.6	1089.0	702.3	1250.7	748.1
Case 3	78.3	−447.1	−164.4	1010.2	759.3	1158.0	692.6

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