抽吸位置对固冲发动机进气道性能的影响

牛雨鹏; 武志文; 张智慧; 陈鹏鑫; 张伊乔; 张旭

doi:10.13224/j.cnki.jasp.20220507

抽吸位置对固冲发动机进气道性能的影响

doi: 10.13224/j.cnki.jasp.20220507

北京理工大学宇航学院，北京 100081

详细信息

作者简介:
牛雨鹏（1998-），男，硕士生，主要从事固体火箭冲压发动机进气道研究。E-mail：905213467@qq.com

通讯作者:
武志文（1978-），男，教授、博士生导师，博士，主要从事固体燃料冲压发动机研究。E-mail：bitwzw@bit.edu.cn

中图分类号: V211.48
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出版历程
- 收稿日期: 2022-07-14
- 网络出版日期: 2024-01-22

Effect of suction position on inlet performance of solid rocket ramjet

School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China

摘要

摘要:
对于设计马赫数为3的固冲发动机，用二维数值模拟的方法研究了一次燃气流量可调，即背压变化的范围较大的进气道，在不同位置设置抽吸孔对进气道不起动马赫数、抗反压能力以及总压恢复系数的影响。在内压缩段设置抽吸孔使进气道的不起动马赫数由2.7降低为2.4，抗反压能力提高了12.28%；外压缩段抽吸使进气道的不起动马赫数由2.7降为2.6，抗反压能力没有提高；而喉道段抽吸的进气道抗反压能力提高了11.24%，不起动马赫数没有变化。内压缩段和喉道段抽吸可以在一定工况下提高总压恢复，尤其是喉道段抽吸可以提高超额定工况下的总压恢复系数。最后提出了一种提高进气道在马赫数为3～5工况下运行的性能提升方案，在马赫数为4～5工况下总压恢复平均提高了5%左右。
- 固冲发动机进气道 /
- 抽吸位置 /
- 起动特性 /
- 抗反压能力 /
- 性能提升
Abstract:
For a solid rocket ramjet with design Mach number of 3, two-dimensional numerical simulation was used to study the effects of suction holes at different locations on the unstart Mach number, anti-back pressure capability and total pressure recovery coefficient of an inlet with adjustable primary gas flow, i.e. a large range of back pressure changes. By setting suction holes in the inner compression section, the unstart Mach number of the inlet was reduced from 2.7 to 2.4, and the anti-back pressure capability was increased by 12.28%; The unstart Mach number of the inlet decreased from 2.7 to 2.6 due to the suction of the outer compression section, and the anti-back pressure capability was not improved; however, the anti-back pressure capability of throat suction inlet was increased by 11.24%, and the unstart Mach number did not change. The internal compression section and throat section suction can improve the total pressure recovery under certain working conditions, especially the total pressure recovery coefficient under over rated working conditions. Finally, a scheme to improve the performance of the inlet under Mach number of 3—5 was proposed, and the total pressure recovery under Mach number of 4—5 was increased by about 5% on average.
- solid rocket ramjet inlet /
- suction position /
- starting characteristics /
- anti back pressure capacity /
- performance improvement

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图 1 进气道模型

Figure 1. Inlet model

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图 2 上壁面压力分布

Figure 2. Pressure distribution on the upper side wall

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图 3 下壁面压力分布

Figure 3. Pressure distribution on the lower side wall

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图 4 构型1的进气道模型及网格

Figure 4. Inlet model and grid of configuration 1

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图 5 构型1在不同马赫数的流场

Figure 5. Flow field of configuration 1 at different Mach numbers

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图 6 构型1在不同马赫数下的性能参数

Figure 6. Performance parameters of configuration 1 at different Mach numbers

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图 7 构型1在不同背压下的流场

Figure 7. Flow field of configuration 1 under different back pressures

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图 8 构型1在不同背压下的性能参数

Figure 8. Performance parameters of configuration 1 under different back pressures

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图 9 构型2的进气道模型及网格

Figure 9. Inlet model and grid of configuration 2

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图 10 构型2在不同马赫数下的流场

Figure 10. Flow field of configuration 2 at different Mach numbers

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图 11 构型2在不同背压下的流场图

Figure 11. Flow field diagram of configuration 2 under different back pressures

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图 12 构型3的进气道模型及网格

Figure 12. Inlet model and grid of configuration 3

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图 13 构型3在不同马赫数下的流场

Figure 13. Flow field of configuration 3 at different Mach numbers

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图 14 构型3在不同背压下的流场图

Figure 14. Flow field diagram of configuration 3 under different back pressure

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图 15 构型4的进气道模型及网格

Figure 15. Inlet model and grid of configuration 4

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图 16 构型4在不同马赫数下的流场

Figure 16. Flow field of configuration 4 at different Mach numbers

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图 17 构型4在不同背压下的流场图

Figure 17. Flow field diagram of configuration 4 under different back pressures

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图 18 构型1、构型2、构型4在Ma_∞=4.5工况下的流场

Figure 18. Flow field of configurations 1, configurations 2, configurations 4 under Ma_∞=4.5 condition

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图 19 构型1、构型2、构型4在Ma_∞=5工况下的流场

Figure 19. Flow field of configurations 1, configurations 2, configurations 4 under Ma_∞=5 condition

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图 20 两种方案的总压恢复系数对比

Figure 20. Comparison of total pressure recovery between two schemes

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表 1 进气道参数

Table 1. Inlet parameters

参数	数值
进气道内部宽度/mm	100
喉道段高度h/mm	50
进气道总长度L/mm	1600
来流入射角α/（°）	0
二级压缩面角度δ₂/（°）	21.5
唇口角度δ₃/（°）	9.5
喉道段扩张角δ₄/（°）	5
设计马赫数Ma_d	3

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表 2 4种构型进气道性能对比

Table 2. Comparison of inlet performance of four configurations

构型	不起动马赫数	极限反压比	总压恢复系数		出口流量/（kg/s）
构型	不起动马赫数	极限反压比	Ma_∞=3	Ma_∞=4	Ma_∞=3	Ma_∞=4
构型1	2.7	19.22	0.577	0.335	0.89	1.20
构型2	2.4	21.58	0.574	0.345	0.83	1.13
构型3	2.6	18.63	0.556	0.337	0.83	1.13
构型4	2.7	21.38	0.555	0.33	0.82	1.17

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表 3 不同构型的性能参数

Table 3. Performance parameters of different configurations

构型	Ma_∞=4		Ma_∞=4.5		Ma_∞=5
构型	总压恢复系数	流量系数	总压恢复系数	流量系数	总压恢复系数	流量系数
构型1	0.1724	1.0003	0.1946	0.9976	0.1746	0.9941
构型2	0.1705	0.9313	0.1603	0.9431	0.1599	0.9415
构型4	0.1481	0.9735	0.1995	0.9864	0.1742	0.9911

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