自燃推进剂直流互击式喷嘴高压燃烧试验

doi:10.7527/S1000-6893.2023.29507

Abstract

Abstract:

To guide the design of thrust chamber injectors for high chamber pressure orbits and attitude control rocket engines， we conduct combustion tests of NTO/MMH unlike doublet injectors at high pressure using the chrome bronze heat sink combustor. The effects of the mixing ratio， ratio of injection orifice diameter， Rupe number， impinging angle and chamber pressure on the characteristic velocity and combustion efficiency are obtained. The results show that， increase in the mixing ratio， ratio of injection orifice diameter， Rupe number or impinging angle leads to initial increase， then constant， and final decrease in the characteristic velocity and combustion efficiency. With the increase of the chamber pressure， the characteristic velocity and combustion efficiency first increase significantly and then remain unchanged. A mixing ratio between 1.71 and 2.31， injection orifice diameter 1.2 and 1.4， Rupe number 0.68 and 1.28， impinging angle 70°and 80°， and chamber pressure over 3 MPa indicate a high combustion efficiency level of 0.97-0.98.

Key words: orbit and attitude control rocket engine, unlike doublet injector, hypergolic propellant, combustion, Rupe number, combustion efficiency

CLC Number:

V434

Feng ZHANG, Yi SUN, Shuai SHANG, Baoe YANG. High pressure combustion experiment for hypergolic propellant unlike doublet injectors[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529507.

Figures/Tables 16

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References 21

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编号	孔径比	撞击角/（°）
No.1	1.0	80
No.2	1.1	80
No.3	1.2	80
No.4	1.3	80
No.5	1.4	80
No.6	1.5	80
No.7	1.6	80
No.8	1.3	60
No.9	1.3	70
No.10	1.3	90

编号	圆柱段直径/mm	燃烧室特征长度/m	喉部直径/mm
No.Ⅰ	30	1.5	2.86
No.Ⅱ	30	1.5	3.14
No.Ⅲ	30	1.5	3.5
No.Ⅳ	30	1.5	4.02
No.Ⅴ	30	1.5	4.94

编号	混合比	氧化剂流量/（g·s^-1）	燃料流量/（g·s^-1）	燃烧室压力/MPa	氧化剂喷注压降/MPa	燃料喷注压降/MPa	鲁泊数	实际特征速度/（m·s^-1）	燃烧效率
1-1	1.55	14.08	9.06	3.98	1.09	1.82	1.50	1 654.8	0.953
1-2	1.71	14.64	8.54	4.12	1.18	1.59	1.23	1 710.1	0.979
1-3	1.86	15.10	8.13	4.11	1.24	1.45	1.05	1 702.2	0.974
1-4	2.10	15.68	7.46	4.09	1.32	1.23	0.82	1 700.5	0.980
1-5	2.31	16.36	7.07	4.05	1.45	1.11	0.68	1 663.1	0.970
1-6	2.54	17.10	6.72	3.94	1.57	1.01	0.56	1 591.4	0.943

编号	孔径比	氧化剂流量/（g·s^-1）	燃料流量/（g·s^-1）	燃烧室压力/MPa	氧化剂喷注压降/MPa	燃料喷注压降/MPa	鲁泊数	实际特征速度/（m·s^-1）	燃烧效率
2-1	1.0	16.02	8.54	3.95	3.42	1.63	0.47	1 547.37	0.886
2-2	1.1	15.62	8.15	4.03	2.38	1.48	0.60	1 631.18	0.934
2-3	1.2	15.28	8.20	4.14	1.71	1.51	0.82	1 696.40	0.971
1-3	1.3	15.10	8.13	4.11	1.24	1.45	1.05	1 702.20	0.974
2-4	1.4	15.50	8.24	4.21	0.99	1.54	1.28	1 706.19	0.976
2-5	1.5	15.35	8.02	4.11	0.62	1.42	1.52	1 692.03	0.969
2-6	1.6	15.52	8.04	4.10	0.51	1.44	1.81	1 674.30	0.959

编号	撞击角/（°）	氧化剂流量/ （g·s^-1）	燃料流量/ （g·s^-1）	燃烧室压力/MPa	氧化剂喷注压降/MPa	燃料喷注压降/MPa	鲁泊数	实际特征速度/（m·s^-1）	燃烧效率
3-1	60	15.54	8.61	4.20	1.38	1.61	1.11	1 673.24	0.957
3-2	70	15.40	8.41	4.21	1.31	1.52	1.08	1 701.17	0.973
1-3	80	15.1	8.13	4.11	1.24	1.45	1.05	1 702.2	0.974
3-3	90	15.31	8.26	4.04	1.25	1.49	1.05	1 649.10	0.944

High pressure combustion experiment for hypergolic propellant unlike doublet injectors

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编号	燃烧室压力/MPa	氧化剂流量/（g·s^-1）	燃料流量/（g·s^-1）	氧化剂喷注压降/MPa	燃料喷注压降/MPa	鲁泊数	实际特征速度/（m·s^-1）	燃烧效率
5-1	2.06	15.90	8.38	1.38	1.55	1.00	1 626.16	0.935
5-2	3.10	15.18	8.40	1.26	1.56	1.11	1 693.63	0.970
1-3	4.11	15.10	8.13	1.24	1.45	1.05	1 702.2	0.974
5-3	5.08	15.25	8.10	1.28	1.44	1.02	1 706.24	0.975
5-4	6.20	15.04	8.02	1.22	1.42	1.03	1 715.19	0.979

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