Study on Spray Atomization Combustion Performance of Liquid Rocket Engine

doi:10.3969/j.issn.1009-086x.2025.04.018

Abstract

Abstract:

In order to control the combustion field reasonably， it is necessary to analyze the atomization quality in the combustion chamber and the ignition delay period of the propellant during the efficient propulsion of the liquid rocket. The three-dimensional atomization combustion field model is using the ICEM module， and the atomization characteristics of centrifugal nozzle under different conditions are analyzed by DPM discrete phase model. The EDC combustion model is coupled to analyze the combustion development process and ignition delay characteristics of n-decane， n-octane and aviation kerosene. The results show that with the increase of nozzle pressure， the penetration distance of droplets increases while D32 decreases.. When the nozzle diameter increases from 1.2 mm to 1.8 mm， the axial velocity of the droplet decreases and the atomization angle increases. With the increase of back pressure， the collision and aggregation effect between droplets is obviously enhanced， and the aerodynamic effect is weakened， resulting in the increase of D₃₂. The length of ignition delay period in the combustion field is positively correlated with the ambient temperature and back pressure.

Key words: centrifugal nozzle, discrete phase model, atomization characteristics, injection pressure, Sauter diameter, combustion chamber

摘要：

液体火箭高效推进时，为合理控制燃烧场，必须对燃烧室内的雾化质量和推进剂的着火延迟期进行分析。利用ICEM模块建立了三维雾化燃烧场模型，采用DPM离散相模型分析了离心式喷嘴在不同条件下的雾化特性；耦合了EDC燃烧模型，对正癸烷、正辛烷及航空煤油进行了燃烧发展过程分析与着火延迟特性研究。结果表明：随着喷嘴压力的升高，液滴在相同时间内贯穿距增大、D₃₂减小；当喷嘴直径从1.2 mm增至1.8 mm时，液滴轴向速度降低，雾化角增加；背压增加时液滴间碰撞聚合效应明显增强，气动作用减弱致使D₃₂变大；燃烧场中着火延迟期长度与环境温度、背压总体上呈正相关。

关键词: 离心式喷嘴, 离散相模型, 雾化特性, 喷射压力, 索特尔直径, 燃烧室

CLC Number:

TJ763

Jianyu CHEN, Xin LU, Xu WANG. Study on Spray Atomization Combustion Performance of Liquid Rocket Engine[J]. Modern Defense Technology, 2025, 53(4): 169-176.

陈建宇, 陆欣, 王旭. 液体火箭发动机喷射雾化燃烧性能研究[J]. 现代防御技术, 2025, 53(4): 169-176.

Figures/Tables 14

Fig. 1 Calculation grid diagram

Table 1 Coefficients of standard k-ε model

变量	$c ε 1$	$c ε 2$	$c ε 3$	$c s$	$P r k$	$P r ε$
值	1.44	1.92	-1.0	1.5	1.0	1.3

Table 1 Coefficients of standard k-ε model

变量	$c ε 1$	$c ε 2$	$c ε 3$	$c s$	$P r k$	$P r ε$
值	1.44	1.92	-1.0	1.5	1.0	1.3

Table 2 Simulation conditions

项目	雾化	燃烧
环境气体	空气	空气
环境温度/K	300	900~1100
喷射压力/MPa	1.5，2.0，2.5，3.0，3.5，4.0	2.0
喷嘴直径/mm	1.2，1.4，1.6，1.8	1.2
背压/MPa	0.2，0.5，0.8，1.1	0.1
液体工质	水	正癸烷，正辛烷，航空煤油
环境压力/MPa	0.1	0.1

Fig. 2 Droplet particle distribution at 3 ms

Fig. 3 Comparison of simulation results and experimental results of droplet D32

Fig. 4 Variation of penetration with time under different pressures

Fig. 5 Changes of D32 with time under different pressures

Fig. 6 Variation of penetration with time under different nozzle diameters

Fig. 7 Change trend of atomization cone angle with nozzle diameter

Fig. 8 Velocity cloud diagram of atomization field under different back pressure conditions

Fig. 9 D32 under different back pressure conditions

Fig. 10 Development process of atomization combustion

Fig. 11 Comparison of ignition delay time of different propellants

Fig. 12 Comparison of ignition delay period under different back pressure conditions

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