双燃烧室冲压发动机对硼基推进剂的促燃效果

doi:10.7527/S1000-6893.2025.31788

Abstract

Abstract:

To investigate the combustion enhancement effect of the Dual Combustor Ramjet engine （DCR） configuration on boron-based propellants and its contribution to engine performance， the scramjet engine （SCR） was selected for comparison. The results indicate that， compared to SCR， the DCR effectively promotes the combustion of boron-based propellants under the conditions of Ma=5 at 28 km height （Case 1） and Ma=6 at 30 km height （Case 2）， benefiting from the high-temperature and high-pressure environment of the subsonic combustor， while maintaining relatively low total pressure loss and better engine performance. In Case 1， the combustion efficiency of DCR is higher than that of SCR by 26.6%， 27.2%， and 23.8% for engine lengths of 1.5 m， 2 m， and 2.5 m， respectively， with specific impulses of 1 964 m/s， 1 970 m/s， and 1 406 m/s. In Case 2， DCR shows combustion efficiencies higher than SCR by 27.9%， 22.3 %， and 22.9 %， with specific impulses of 1 615 m/s， 1 393 m/s， and 960 m/s， respectively. The shorter the engine length， the more pronounced the performance advantage of DCR over SCR， indicating that DCR is preferable in space-constrained application scenarios.

Key words: dual combustor ramjet, scramjet, boron-based propellant, combustion efficiency, specific impulse

CLC Number:

V435

Xianju WU, Zhijun WEI, Yunhui WANG, Ling ZHOU, Ying FENG. Combustion enhancement effect of dual combustor ramjet engines on boron-based propellants[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(18): 131788.

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类型	L₁	L₂	L	R₁	R₂
DCR	590	670	1 500	1 200	600
	690	790	2 000	2 200	1 800
	690	1 290	2 500	2 200	1 800
SCR	500	690	1 500	1 200	600
	600	790	2 000	2 200	1 800
	600	1 290	2 500	2 200	1 800

类别	气相			凝相
类别	H₂	CO	B	B<s>	C<s>
质量分数/%	4.5	21	4.5	52.5	17.5

工况	流量/（kg·s^-1）	发动机类型	燃烧室入口总温/K	燃烧室入口总压/MPa	超燃/亚燃气流配比	燃烧室入口马赫数
工况1	3.11	DCR	1 235	0.67（0.32）	1∶2	2.5（0.3）
工况1	3.11	SCR	1 235	0.67		2.5
工况2	3.45	DCR	1 694	1.36（0.36）	1∶2	3（0.3）
工况2	3.45	SCR	1 694	1.36		3

工况	类型	发动机长度/m	总压恢复系数/%	燃烧效率/%	比冲/（m·s^-1）
工况1	SCR	1.5	10.1	64.6	7 524
		2	9.4	65.9	8 418
		2.5	11.1	69.8	9 184
	DCR	1.5	25.6（16.9）	91.2	9 489
		2	25.1（16.6）	93.1	10 388
		2.5	25.1（16.6）	93.6	10 590
工况2	SCR	1.5	6.5	63.7	6 383
		2	6.2	69.0	7 248
		2.5	7.3	71.4	7 809
	DCR	1.5	19.5（10.2）	91.6	7 998
		2	19.5（10.2）	91.3	8 641
		2.5	19.5（10.2）	94.3	8 769

Combustion enhancement effect of dual combustor ramjet engines on boron-based propellants

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