超声速喷管扩张型面对水下喷气推进振荡特性的影响

doi:10.12382/bgxb.2024.0103

摘要/Abstract

摘要：

为研究超声速喷管扩张型面对水下火箭推进喷管多相流动与推进性能的影响,对具有不同扩张段型面的锥形和抛物型喷管在变深度静水环境、过膨胀条件下的流动过程进行数值模拟。基于流体体积多相流模型建立水下超声速燃气射流计算模型,详细分析扩张型面类型和关键参数对喷管近场流动结构、流动分离特征和推力振荡特性的影响规律。研究结果表明:深水工作喷管内的分离激波结构高度不稳定,扩张段分离点处还可能呈现气-液分离,喷管推力在满流值的基础上振荡;抛物型喷管内存在流动分离模式的动态转换,受限激波分离下气-液分离现象不显著,与型面参数相比,型面类型的影响更为突出,抛物型喷管的推力振荡比锥形喷管更缓和,且在大水深下的差异更明显;在90m水深下,不同型面喷管平均推力的最大差异达到基准抛物型喷管的10.13%。

关键词: 水下喷气推进, 超声速燃气射流, 喷管型面, 流动分离, 推力振荡

Abstract:

The effect of the divergent section contour of supersonic nozzle on the multiphase flow and propulsion performance of underwater rocket propulsion nozzle is studied by a series of numerical simulations.The underwater flow processes of conical and parabolic nozzles with different divergent section contours under still water,variable depth and over-expanded conditions are simulated.A numerical model of underwater supersonic gas jet is established based on the volume of fluid(VOF)multiphase model.The influence laws of the contour types and key parameters of divergent section on the nozzle near-field flow structure,flow separation characteristics,and thrust oscillation characteristics are analyzed.The results show that the separation shock structure in the nozzle operating in deep water is highly unstable.The gas-liquid separation may also occur at the separation point in the divergent section,and the nozzle thrust oscillates on the basis of the full-flow value.There is a dynamic transition of flow separation patterns in parabolic nozzles,and the gas-liquid separation phenomenon is not significant under the restricted shock separation(RSS)pattern.The effect of contour type is more pronounced than that of contour parameters,with the parabolic nozzles having more moderate thrust oscillations than the conical nozzles,and the difference is more significant at greater water depths.At a depth of 90 m,the maximum difference in average thrust of the nozzles with different contours reaches 10.13% of that of the basic parabolic nozzle.

Key words: underwater jet propulsion, supersonic gas jet, nozzle contour, flow separation, thrust oscillation

中图分类号:

TJ610.1

王德友, 李世鹏, 郭宝俊, 张北辰, 王宁飞. 超声速喷管扩张型面对水下喷气推进振荡特性的影响[J]. 兵工学报, 2025, 46(2): 240103-.

WANG Deyou, LI Shipeng, GUO Baojun, ZHANG Beichen, WANG Ningfei. Effect of Divergent Section Contour of Supersonic Nozzle on Oscillation Characteristics of Underwater Jet Propulsion[J]. Acta Armamentarii, 2025, 46(2): 240103-.

图/表 22

图1 计算域及边界条件

Fig.1 Computational domain and boundary conditions

图2 水下火箭发动机推力计算示意图

Fig.2 Schematic diagram of thrust calculation of underwater rocket motor

图3 网格划分

Fig.3 Meshing

表1 锥形喷管参数设置

Table 1 Parameter setting for conical nozzles

参数	C-1	C-2	C-3	C-4	C-5
β/(°)	9	12	15	18	21
L/mm	158.24	118.14	93.96	77.73	66.05

表2 抛物型喷管参数设置

Table 2 Parameter setting for parabolic nozzles

参数	P-1	P-2	P-3	P-4	P-5
θ_n/(°)	26	30	30	30	34
θ_e/(°)	5	1	5	9	5
L/mm	77.73	77.73	77.73	77.73	77.73

图4 燃气泡初始演化过程形貌对比

Fig.4 Comparison of gas bubble morphologies during initial evolution

图5 燃气泡顶点位置变化规律对比

Fig.5 Location-time curves of gas bubble vertex

图6 不同NPR下喷管扩张段壁面压力分布与马赫数云图

Fig.6 Wall pressure distributions and Mach number contours of nozzle divergent section under different NPRs

图7 典型时刻下基准锥形喷管近场流动结构

Fig.7 Flow structures near the basic conical nozzle at typical moments

图8 深度90m工况t=10ms时刻锥形喷管近场流动结构

Fig.8 Flow structures near the conical nozzles at 10ms at 90m depth

图9 抛物型喷管不同分离模式下的内部激波结构[36]

Fig.9 Internal shock structures in a parabolic nozzle during different separation patterns[36]

图10 典型时刻下基准抛物型喷管近场流动结构

Fig.10 Flow structures near the basic parabolic nozzle at typical moments

图11 深度90m工况首次颈缩时刻不同喷管燃气泡形貌(t=6.7ms)

Fig.11 Gas bubble morphologies at the first necking time for different nozzles at 90m depth

图12 深度90m工况基准抛物型喷管扩张段壁面压力分布

Fig.12 Wall pressure distributions in divergent section for the basic parabolic nozzle at 90m depth

图13 压力监测点位置分布

Fig.13 Locations of pressure probing points

图14 锥形喷管激波分离点振荡规律

Fig.14 Oscillation patterns of shock separation point for conical nozzle

图15 抛物型喷管激波分离点振荡规律

Fig.15 Oscillation patterns of shock separation point for parabolic nozzle

图16 基准锥形和抛物型喷管推力变化规律

Fig.16 Nozzle thrust-time curves of the basic conical and parabolic nozzles

图17 深度90m工况各基准喷管推力分量频谱分析

Fig.17 Thrust component spectrum analysis for basic nozzles at 90m depth

图18 深度90m工况不同喷管推力增量变化规律

Fig.18 Change rule of nozzle thrust increment at 90m depth

表3 锥形喷管平均推力特性

Table 3 Average thrusts of conical nozzles

扩张型面	平均喷管推力/kN
扩张型面	满流	H=50m	H=90m
C-1	6.399	7.091	7.863
C-2	6.397	7.019	8.035
C-3	6.345	6.968	7.876
C-4	6.342	6.923	7.818
C-5	6.311	6.804	7.795

表4 抛物型喷管平均推力特性

Table 4 Average thrusts of parabolic nozzles

扩张型面	平均喷管推力/kN
扩张型面	满流	H=50m	H=90m
P-1	6.399	6.813	7.421
P-2	6.374	6.732	7.385
P-3	6.395	6.774	7.296
P-4	6.405	6.825	7.488
P-5	6.382	6.839	7.500

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