火箭推进

补燃循环发动机深度节流过程中,系统参数大范围变化,低工况时喷注器压降和供应系统节流元件压降较低,容易出现推进剂供应系统与热力组件耦合的不稳定问题。针对10:1深度节流富氧补燃循环发动机,通过Nyquist稳定性分析方法,对发动机全工况范围内泵后供应系统和燃气系统耦合稳定性进行仿真研究。结果表明:富氧补燃循环发动机燃料供应路与燃气路形成的闭环系统在低工况时,稳定裕度较低,改善燃气发生器喷雾燃烧效果以缩短时滞、增加燃气停留时间、在靠近燃气发生器位置增加供应系统压降能提高系统稳定裕度。

During the deep-throttling process of staged combustion cycled engine, the system parameters vary in a large range. Under the low operating condition, the injection pressure drop and the pressure drop of feed system throttling element are relatively low, so the coupling instability between the propellant feed system and the thermal component is easy to occur. For the 10:1 deep-throttling oxygen-enriched staged combustion cycled engine, the coupling stability of the after-pump feed system and the gas system within the full operating range was studied by Nyquist stability analysis method. The results show that the stability margin of the closed-loop system composed of the fuel feed circuit and the gas circuit is low under low operating conditions of the oxygen-enriched staged combustion cycled engine. The system stability margin is able to be enhanced by improving the evaporation and combustion effect of the gas generator to shorten the time lag, increasing the gas residence time, and increasing the pressure drop near the gas generator.

引言
1 分析模型
2 稳定性计算结果分析
3 结论

图1 发动机系统原理图<br/>Fig.1 Schematic diagram of engine system

图1 发动机系统原理图
Fig.1 Schematic diagram of engine system

图2 供应系统与燃气系统组成闭合回路<br/>Fig.2 Closed loop of feed system and gas system

图2 供应系统与燃气系统组成闭合回路
Fig.2 Closed loop of feed system and gas system

图3 全工况液氧供应系统和燃气系统导纳<br/>Fig.3 Admittance of liquid oxygen feed system and gas system of all conditions

图3 全工况液氧供应系统和燃气系统导纳
Fig.3 Admittance of liquid oxygen feed system and gas system of all conditions

图4 全工况燃料供应系统和燃气系统导纳<br/>Fig.4 Admittance of fuel feed system and gas system of all conditions

图4 全工况燃料供应系统和燃气系统导纳
Fig.4 Admittance of fuel feed system and gas system of all conditions

图5 10%工况燃料供应系统和燃气系统导纳<br/>Fig.5 Admittance of fuel feed system and gas system at 10% condition

图5 10%工况燃料供应系统和燃气系统导纳
Fig.5 Admittance of fuel feed system and gas system at 10% condition

图6 10%工况燃料闭环系统Nyquist曲线<br/>Fig.6 Nyquist curve of fuel closed loop system at 10% condition

图6 10%工况燃料闭环系统Nyquist曲线
Fig.6 Nyquist curve of fuel closed loop system at 10% condition

图7 不同燃气停留时间燃料供应系统和燃气系统导纳<br/>Fig.7 Admittance of fuel feed system and gas system of different gas residence time

图7 不同燃气停留时间燃料供应系统和燃气系统导纳
Fig.7 Admittance of fuel feed system and gas system of different gas residence time

图8 不同燃气停留时间燃料闭环系统Nyquist曲线<br/>Fig.8 Nyquist curve of fuel closed loop system of different gas residence time

图8 不同燃气停留时间燃料闭环系统Nyquist曲线
Fig.8 Nyquist curve of fuel closed loop system of different gas residence time

图9 不同供应系统压降液氧供应系统和燃气系统导纳<br/>Fig.9 Admittance of liquid oxygen feed system and gas system of different supply system pressure drop

图9 不同供应系统压降液氧供应系统和燃气系统导纳
Fig.9 Admittance of liquid oxygen feed system and gas system of different supply system pressure drop

图10 不同供应系统压降燃料供应系统和燃气系统导纳<br/>Fig.10 Admittance of fuel feed system and gas system of different supply system pressure drop

图10 不同供应系统压降燃料供应系统和燃气系统导纳
Fig.10 Admittance of fuel feed system and gas system of different supply system pressure drop

图11 不同供应系统压降燃料闭环系统Nyquist曲线<br/>Fig.11 Nyquist curve of fuel closed loop system of different supply system pressure drop

图11 不同供应系统压降燃料闭环系统Nyquist曲线
Fig.11 Nyquist curve of fuel closed loop system of different supply system pressure drop

图12 不同节流圈位置燃料供应系统导纳<br/>Fig.12 Admittance of fuel feed system of different throttle position

图12 不同节流圈位置燃料供应系统导纳
Fig.12 Admittance of fuel feed system of different throttle position

图13 燃料管路不同位置流量响应幅值<br/>Fig.13 Flow response amplitude at different locations along fuel pipe

图13 燃料管路不同位置流量响应幅值
Fig.13 Flow response amplitude at different locations along fuel pipe

[1] BETTS E, FREDERICK R. A historical systems study of liquid rocket engine throttling capabilities[C]//46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.[S.l.]:AIAA:2010.
[2] GIULIANO V, LEONARD T, ADAMSKI W, et al. A deep throttling demonstrator cryogenic engine for NASA's lunar lander[C]//43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.[S.l.]:AIAA,2007.
[3] GIULIANO V J, LEONARD T G, LYDA R T, et al. Expanding the envelope of deep throttling technology in liquid oxygen/liquid hydrogen rocket engines for NASA exploration missions[Z]. 2010.
[4] 雷娟萍, 兰晓辉, 章荣军, 等. 嫦娥三号探测器7 500 N变推力发动机研制[J]. 中国科学(技术科学), 2014, 44(6): 569-575.
[5] DRESSLER G A. Summary of deep throttling rocket engines with emphasis on Apollo LMDE [R].AIAA 2006-5220.
[6] KIMURA T, SATO M, MASUOKA T, et al. Effects of deep throttling on rocket engine systems[C]//46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.[S.l.]:AIAA, 2010.
[7] 龚南妮,李春红. 大范围变工况液氧煤油燃气发生器热试研究[C]//第五届载人航天(国际)学术大会.西安:中国载人航天工程办公室,2018.
[8] CASIANO M J.Extensions to the time lag models for practical application to rocket engine stability design[D].Pennsylvania: Pennsylvania State University,2010.
[9] 邢理想, 杜大华, 李斌. 液氧/煤油补燃火箭发动机氧路低频动特性分析[J]. 火箭推进, 2009, 35(5): 24-28.

备注

引言

1 分析模型

2 稳定性计算结果分析

3 结论

期刊信息