Optimization Design of Solid Rocket Scramjet Engine Based on Orthogonal Experiments

doi:10.12382/bgxb.2024.0820

Abstract

Abstract:

The effects of the ignition and combustion characteristics of boron particles in a solid rocket scramjet engine and the combustor structure on the combustion performance of engine are studied.A user-defined function program for characterizing the ignition and combustion processes of boron particles is written,and the dynamic characteristics of combustion energy release of condensed-phase particles in a ramjet is analyzed.Furthermore,based on the orthogonal design experimental method,the effects of boron particle size,gas injection angle and cavity depth,as well as their interactions on engine combustion efficiency are analyzed from the perspectives of particle characteristics and engine structure.Through range and variance analyses,the results indicate that the factors influencing the engine combustion efficiency are ranked as follows:boron particle size > interaction between particle size and gas injection angle > gas injection angle > cavity depth > interaction between gas injection angle and cavity depth > interaction between particle size and cavity depth.The optimal combination achieves a combustion efficiency of 77.01%.The boron particle size has a significant effect on the combustion efficiency of solid rocket scramjet engine,and the interaction between particle size and gas injection angle cannot be ignored.

Key words: solid rocket scramjet engine, boron particle, orthogonal design, interaction, combustion efficiency

FENG Ying, FU Wenjuan, HU Zhenkun, TANG Yong, ZHAO Majie, SHI Baolu. Optimization Design of Solid Rocket Scramjet Engine Based on Orthogonal Experiments[J]. Acta Armamentarii, 2025, 46(9): 240820-.

Figures/Tables 24

Fig.1 Analysis method of factors influencing combustion efficiency in solid rocket scramjet engine based on orthogonal experiment

Fig.2 Iterative process for gas-solid two-phase numerical simulation

Table 1 Gas-phase chemical reaction mechanism

`化学反应	A/(m³·kmol^-1·s^-1)	E/(J·kmol^-1)
2CO+O₂→2CO₂	2.239×10¹²	1.7×10⁸
2H₂+O₂→2H₂O	9.87×10⁸	3.1×10⁷
2B₂O₂+O₂→2B₂O₃	1.1×10¹²	1.0×10⁸

Table 2 Surface chemical reaction mechanism of carbon particles

化学反应	A/(kg·m^-2·s^-1·Pa^-1)	E/(J·kmol^-1)	B
C+O₂→2CO	0.86	1.0495×10⁸	0

Table 3 Heterogeneous chemical reaction mechanism of boron particles

过程	反应速率	反应机理
点火过程	R₁	2/3B(s)+2/3B₂O₃(l)→B₂O₂(g)
	R₂	B₂O₃(l)→B₂O₃(g)
	R₃	B(s)+O₂(g)→BO₂(g)
	R₄	2/3B(s)+2/3B₂O₃(l)+H₂O(g)+ 1/2O₂(g)→2HBO₂(g)
	R₅	B₂O₃(l)+H₂O(g)→2HBO₂(g)
燃烧过程	R₆	2B(s)+O₂(g)→B₂O₂(g)
	R₇	2B(s)+2/3O₂(g)+H₂O(g)→2HBO₂(g)
	R₈	B(l)→B(g)(蒸发)
	R₉	B(l)→B(g)(沸腾)

Fig.3 Schematic diagram of the verification model for the solid rocket scramjet engine

Table 4 Mass fraction of gas components

组分	CO	H₂	MgCl₂	N₂
质量分数	0.4063	0.1325	0.3688	0.0924

Fig.4 Centerline pressure distribution at the combustor exit cross-section for different grid quantities

Fig.5 Comparison diagram of wall pressure along the length

Fig.6 Schematic diagram of the solid rocket scramjet engine[21]

Table 5 Factor level table

编号	因素	水平
编号	因素	1	2	3
A	颗粒粒径/μm	3	6	9
B	燃气入射角/(°)	45	90	135
C	凹腔深度/mm	10	20	30

Table 6 L27(313) orthogonal design table

试验号	1	2	3	4	5	6	7	8	9	10	11	12	13
试验号	A	B	A×B	A×B	C	A×C	A×C	B×C			B×C
1	1	1	1	1	1	1	1	1	1	1	1	1	1
2	1	1	1	1	2	2	2	2	2	2	2	2	2
3	1	1	1	1	3	3	3	3	3	3	3	3	3
4	1	2	2	2	1	1	1	2	2	2	3	3	3
5	1	2	2	2	2	2	2	3	3	3	1	1	1
6	1	2	2	2	3	3	3	1	1	1	2	2	2
7	1	3	3	3	1	1	1	3	3	3	2	2	2
8	1	3	3	3	2	2	2	1	1	1	3	3	3
9	1	3	3	3	3	3	3	2	2	2	1	1	1
10	2	1	2	3	1	2	3	1	2	3	1	2	3
11	2	1	2	3	2	3	1	2	3	1	2	3	1
12	2	1	2	3	3	1	2	3	1	2	3	1	2
13	2	2	3	1	1	2	3	2	3	1	3	1	2
14	2	2	3	1	2	3	1	3	1	2	1	2	3
15	2	2	3	1	3	1	2	1	2	3	2	3	1
16	2	3	1	2	1	2	3	3	1	2	2	3	1
17	2	3	1	2	2	3	1	1	2	3	3	1	2
18	2	3	1	2	3	1	2	2	3	1	1	2	3
19	3	1	3	2	1	3	2	1	3	2	1	3	2
20	3	1	3	2	2	1	3	2	1	3	2	1	3
21	3	1	3	2	3	2	1	3	2	1	3	2	1
22	3	2	1	3	1	3	2	2	1	3	3	2	1
23	3	2	1	3	2	1	3	3	2	1	1	3	2
24	3	2	1	3	3	2	1	1	3	2	2	1	3
25	3	3	2	1	1	3	2	3	2	1	2	1	3
26	3	3	2	1	2	1	3	1	3	2	3	2	1
27	3	3	2	1	3	2	1	2	1	3	1	3	2

Table 7 Test results

试验号	η_B/%	η_C/%	η_t/%
1	61.46	99.37	72.30
2	62.42	99.56	73.04
3	58.22	99.60	70.05
4	67.80	100.00	77.01
5	67.79	100.00	77.00
6	67.23	100.00	76.60
7	60.90	99.12	71.83
8	60.75	99.28	71.77
9	62.10	95.50	72.79
10	45.89	100.00	61.36
11	44.15	99.98	60.11
12	43.23	99.01	59.18
13	9.26	17.04	11.48
14	9.13	16.75	11.31
15	9.00	16.40	11.12
16	29.73	94.52	48.26
17	28.29	93.88	47.04
18	27.81	92.98	46.44
19	12.01	27.33	16.39
20	12.25	28.00	16.75
21	12.50	28.90	17.20
22	6.00	20.60	10.20
23	5.36	19.72	9.47
24	5.75	20.05	9.84
25	11.90	35.61	18.68
26	11.20	34.20	17.80
27	10.76	32.90	17.09

Table 8 Range analysis table

参数	1	2	3	4	5	6	7	8	11
参数	A	B	A×B	A×B	C	A×C	A×C	B×C	B×C
K₁	662.39	446.38	386.64	302.87	387.51	381.9	383.73	384.22	384.15
K₂	356.3	294.03	464.83	422.69	384.29	387.04	383.82	384.91	386.23
K₃	133.42	411.7	426.55	426.55	380.31	383.17	384.56	382.98	381.73
$K ¯ 1$	73.60	49.60	42.96	33.65	43.06	42.43	42.64	42.69	42.68
$K ¯ 2$	39.59	32.67	51.65	46.97	42.70	43.00	42.65	42.77	42.91
$K ¯ 3$	14.82	45.74	47.39	47.39	42.26	42.57	42.73	42.55	42.41
R	58.77	16.93	8.69	13.74	0.80	0.57	0.09	0.21	0.50

Table 8 Range analysis table

参数	1	2	3	4	5	6	7	8	11
参数	A	B	A×B	A×B	C	A×C	A×C	B×C	B×C
K₁	662.39	446.38	386.64	302.87	387.51	381.9	383.73	384.22	384.15
K₂	356.3	294.03	464.83	422.69	384.29	387.04	383.82	384.91	386.23
K₃	133.42	411.7	426.55	426.55	380.31	383.17	384.56	382.98	381.73
$K ¯ 1$	73.60	49.60	42.96	33.65	43.06	42.43	42.64	42.69	42.68
$K ¯ 2$	39.59	32.67	51.65	46.97	42.70	43.00	42.65	42.77	42.91
$K ¯ 3$	14.82	45.74	47.39	47.39	42.26	42.57	42.73	42.55	42.41
R	58.77	16.93	8.69	13.74	0.80	0.57	0.09	0.21	0.50

Table 9 Analysis of variance table

方差来源、误差项和总和	变差平方和	自由度	均方	F	F_α	显著性
A	15673.18	2	7836.59	10829.63	F_0.01(2,8)=8.65	高度显著
B	1417.02	2	708.51	979.11	F_0.01(2,8)=8.65	高度显著
C	2.89	2	1.45	2.00	F_0.2(2,8)=1.98	有一定影响
A×B	2597.65	4	649.41	897.29	F_0.05(4,8)=7.01	高度显著
A×C	1.64	4	0.41	0.57	F_0.2(4,8)=1.92	无影响
B×C	1.34	4	0.33	0.46	F_0.2(4,8)=1.92	无影响
e	5.79	8	0.72
总和	19699.50	26

Table 10 Combustion efficiency under the corresponding level combinations of particle size and injection angle

组合	燃烧效率平均值/%
A1B1	71.80
A1B2	76.87
A1B3	72.13

Fig.7 Mach number contour plot under different gas injection angles

Fig.8 Temperature contour plots under different gas injection angles

Fig.9 Local temperature and streamline contour plots under different gas injection angles

Fig.10 Mass fraction contour plots of B2O3 under different gas injection angles

Table 11 Distribution of boron particle oxide layer thickness under different injection angles

燃气入射角/(°)	粒径/μm
燃气入射角/(°)
45
90
135

Table 12 Distribution of boron particle size under different injection angles

燃气入射角/(°)	粒径/μm
燃气入射角/(°)
45
90
135

Table 13 Distribution of boron particle temperature under different injection angles

燃气入射角/(°)	粒径/μm
燃气入射角/(°)
45
90
135

Table 14 Residence time and combustion efficiency at corresponding levels of particle size and injection angle

硼颗粒粒径/μm	入射角/ (°)	硼颗粒滞留时间/ms	碳颗粒滞留时间/ms	η_t/%
3	45	1.35	1.34	72.30
	90	1.38	1.31	77.01
	135	1.31	1.34	71.83
6	45	1.29	1.11	61.36
	90	1.07	1.10	11.48
	135	1.21	1.22	48.26
9	45	1.10	1.10	16.39
	90	1.06	1.07	10.20
	135	1.14	1.12	18.68

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