流场不均匀对液体火箭发动机纵向振荡燃烧影响及控制

李龙飞; 杨宝庆; 葛树宏; 刘佩进; 刘新华

doi:10.13224/j.cnki.jasp.20210356

流场不均匀对液体火箭发动机纵向振荡燃烧影响及控制

doi: 10.13224/j.cnki.jasp.20210356

1.
西北工业大学航天学院，西安 710072
2.
中国航天科技集团有限公司西安航天动力研究所液体火箭发动机技术重点实验室，西安 710100

基金项目: 民用航天重点基础研究（D010201）

详细信息

作者简介:
李龙飞（1977-），男，研究员，博士生，研究领域为液体火箭发动机喷雾燃烧与燃烧不稳定性。E-mail：13809153816@163.com

中图分类号: V434.1
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- 被引次数: 0
出版历程
- 收稿日期: 2021-07-08
- 网络出版日期: 2022-09-30

Influence and control of non-uniform flow field on longitudinal combustion instability of liquid rocket engines

1.
School of Astronautics，Northwestern Polytechnical University，Xi’an 710072，China
2.
National Key Laboratory of Science and Technology on Liquid Rocket Engines，Xi’an Aerospace Propulsion Institute，China Aerospace Science and Technology Corporation，Xi’an 710100，China

摘要

摘要:
针对常温推进剂发动机推力室再生冷却和撞击式喷注器结构，分析了推力室身部与喷注器对接部位的流场特性，对流场均匀性进行了实验测量。结果表明：推力室身部再生冷却通道出口压力存在约0.15 MPa周向不均匀。身部出口节流显著提高局部流速，使喷注器面氧化剂湍流度和不均匀性增加，进而改变燃烧特性。通过撞击喷注单元雾化试验，获得了18 m/s的推进剂入口边界流速。基于喷注器流场均匀性，提出控制推进剂流速，降低不均匀性，进而抑制纵向高频燃烧不稳定性的控制方法。发动机热试结果表明，采用（15±1） m/s的推进剂入口流速，控制方法抑制了纵向高频燃烧不稳定性。
- 液体火箭发动机 /
- 推力室 /
- 撞击式喷注器 /
- 纵向燃烧不稳定性 /
- 不均匀性
Abstract:
The vortex instability and pressure oscillation in the flow field are one of the important reasons for the high frequency longitudinal combustion instability of liquid rocket engine. Considering the regenerative cooling channel and impinging jet injectors in the thrust chamber ofnormal temperature propellant rocket engine, the flow field of the connecting part between the thrust chamber body and the injector was analyzed, and its uniformity were measured experimentally. Results showed that the circumferential non-uniform pressure at outlet of regenerative cooling channel was about 0.15 MPa. The use of throttling at the outlet of the cylindrical section of the thrust chamber can significantly increase the local fluid velocity and the turbulence and non-uniformity of the oxidant at the injector, thereby changing the combustion characteristics. The atomization test of impact injection unit was carried out, and the propellant inlet boundary velocity of 18 m/s was obtained. Based on the flow field uniformity of the injector, a control method of suppressing the longitudinal high frequency combustion instability was proposedby controlling the propellant flow rate and reducing the non-uniformity. The engine thermal test results showed that the control method suppressed the longitudinal high frequency combustion instability of the thrust chamber at the propellant inlet flow rate of (15±1) m/s.
- liquid rocket engine /
- thrust chamber /
- impinging jet injector /
- longitudinal combustion instability /
- non-uniformity

HTML

图 1 试验条件下的振动加速度曲线

Figure 1. Curves of vibration acceleration under test conditions

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图 2 稳态和外部扰动条件下直流自击式喷注单元的雾化场

Figure 2. Atomization field of impinging jet injector under steady state and external disturbance conditions

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图 3 推力室局部结构图

Figure 3. Partial structure diagram of thrust chamber

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图 4 推力室压力测点分布示意图

Figure 4. Schematic diagram of pressure measuring point distribution in thrust chamber

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图 5 推力室不同测点的流体压力

Figure 5. Fluid pressure at different measuring points in thrust chamber

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图 6 推力室P7测点横截面压力与P8测点横截面速度

Figure 6. Pressure of P7 and velocity of P8 at different cross-sections of the thrust chamber

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图 7 热试验后喷注器表面积碳的比较

Figure 7. Comparison of carbon deposit on injector surface after thermal test

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图 8 热试验期间轴向、径向和切向的RMS振动曲线

Figure 8. RMS vibration curves of axial，radial and tangential directions during thermal test

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