主动通气对螺旋桨尾流的影响

doi:10.12382/bgxb.2024.0905

摘要/Abstract

摘要：

针对气泡流对于螺旋桨尾流的影响,基于剪切应力传输k-ω(k为湍流动能,ω为湍流动能耗散率)分离涡模拟湍流模型与体积分数方程,结合滑移网格技术开展了螺旋桨在气泡流中尾流动力学特性的数值研究,对KP505桨绕流数值模型进行验证,基于多相来流中螺旋桨尾涡的演化机理,提出螺旋桨尾涡演化模型。研究结果表明:所提模型能够较为准确地模拟螺旋桨尾涡的演化过程,对螺旋桨尾流不稳定性的触发机理进行了揭示,径向通气位置影响螺旋桨的翼梢涡和桨毂涡强度与耗散,轴线处通气使桨毂涡膨胀,并使得翼梢涡在远场连通成为涡环,通气位置向翼梢移动,翼梢涡系加速扩张并迅速耗散;研究结果对为螺旋桨设计与制造具有一定的参考价值。

关键词: 通气气泡, 气液两相, 螺旋桨尾流, 不稳定性机理, 数值分析

Abstract:

In order to investigate the influence of bubbly flow on propeller wake,the wake dynamics characteristics of propellers in bubbly flow are numerically studied based on the SST k-ω DES turbulence model and volume fraction equation,and the sliding grid technique.The KP505 propeller flow numerical model is verified.A propeller wake evolution model is proposed based on the evolution mechanism of propeller wake in multiphase inflow.The results show that the proposed model can accurately simulate the evolution process of propeller wake and reveal the triggering mechanism of propeller wake instability.The radial ventilation position affects the strength and dissipation of the tip vortex and hub vortex of propeller.The ventilation at the axis causes the hub vortex to expand and connects the tip vortex to form a vortex ring in the far field.The ventilation position moves towards the wing tip,and the vortex system at the wing tip accelerates and rapidly dissipates.The results have certain reference value for the design and manufacturing of propellers.

Key words: air injection bubble, gas-liquid two-phase, propeller wake, instability mechanism, numerical analysis

王志博, 顾津菁, 钱浩城. 主动通气对螺旋桨尾流的影响[J]. 兵工学报, 2025, 46(9): 240905-.

WANG Zhibo, GU Jinjing, QIAN Haocheng. The Influence of Active Ventilation on Propeller Wake[J]. Acta Armamentarii, 2025, 46(9): 240905-.

图/表 19

图1 桨与气泡耦合设置

Fig.1 Coupling setting of propeller and bubble

表1 通气量设置

Table 1 Air injection setting

r/R	进速系数	通气质量流量/ (kg·s^-1)	通气流速/ (m·s^-1)
0	0.4	0	0
		0.0003	0.95
		0.001	3.18
		0.003	9.55
		0.005	15.92
		0.012	38.20

表2 通气位置设置

Table 2 Ventilation position setting

通气质量流量/ (kg·s^-1)	进速系数	r/R	通气口中心坐标/m
0.003	0.4	0	(0,0,0)
		0.2	(0,0.025,0)
		0.4	(0,0.05,0)
		0.6	(0,0.075,0)
		0.8	(0,0.1,0)
		1.2	(0,0.15,0)

图2 计算域及网格加密设计

Fig.2 Design of computational domain and mesh encryption

表3 不同网格方案及网格无关性验证

Table 3 Different grid schemes and grid independence verification

网格方案	叶片网格尺寸/H	边界层厚度/H	旋转体网格尺寸/H	交界面网格尺寸/H	网格数/10⁶	K_T	ΔK_T/%	10K_Q	ΔK_Q/%
1	0.0400	0.2000	0.0400	0.0800	1.79	0.2492	4.53	0.422	7.68
2	0.0141	0.0707	0.0141	0.0283	5.08	0.2407	0.96	0.409	4.36
3	0.0050	0.0250	0.0050	1.00%H	14.37	0.2398	0.59	0.401	2.32

图3 KP505敞水验证

Fig.3 The open water curve of KP505

表4 不同通气量下水气掺和作用下尾涡演化

Table 4 Volution of wake under the influence of water vapor mixing at different air injection flow rates

q/ (kg·s^-1)	J
q/ (kg·s^-1)	0.2	0.4	0.6	0.8
0
0.0003
0.0010
0.0030
0.0050
0.0120

图4 通气量对尾涡凝聚效应演化关系(J=0.4)

Fig.4 The evolutionary relationship between air injection flow rates and wake condensation effect(J=0.4)

图5 桨后轴线桨毂涡量衰减关系

Fig.5 The attenuation relationship of vortex in the hub of the rear axis of propeller

图6 螺旋桨气泡浸润的演化

Fig.6 Evolution of propeller bubble infiltration

图7 桨后气体分布(J=0.4)

Fig.7 Gas distribution behind the propeller(J=0.4)

图8 不同通气量下桨后轴线气体体积分数

Fig.8 Volume fraction of gas behind the propeller axis at different air injection flow rates

图9 桨毂涡对气泡的凝集稳定性

Fig.9 The stability of bubble agglomeration influenced by propeller hub vortex

图10 通气路径演化

Fig.10 Evolution of air injection pathways

图11 桨前喷气管轴线上的气体体积分数

Fig.11 Volume fraction of gas on the axis of the pipe

图12 x/D=-0.2面的进流属性

Fig.12 Inflow attribute of x/D=-0.2 surface

图13 不同位置下水气掺和作用下尾涡演化

Fig.13 Evolution of wake under the influence of water vapor mixing at different air injection positions

图14 不同通气位置对尾涡凝聚效应演化关系

Fig.14 The evolution relationship of tail vortex condensation effect at different air injection positions

图15 不同通气位置桨后轴线涡量变化

Fig.15 Vortex at the rear axis of the propeller at different air injection positions

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