基于大涡模拟方法的三维旋转爆轰流场结构研究

doi:10.12382/bgxb.2022.0470

摘要/Abstract

摘要：

为研究环形燃烧室中边界层、黏性、湍流模拟方法对旋转爆轰流场结构的影响,采用开源计算流体动力学软件OpenFOAM,以氢气为燃料、空气为氧化剂,基于大涡模拟(Large Eddy Simulation,LES)方法、RANS方法、Euler方法,分别结合滑移和无滑移边界,对三维旋转爆轰发动机模型进行数值模拟,分析对比不同计算方法下旋转爆轰流场结构。着重讨论以LES方法得到的流场结构。研究结果表明:当采用滑移边界时内、中、外截面的流场温度无太大差异,当采用无滑移边界时内外壁面温度高于中间截面,边界层会影响近壁区域气体的流动速度,导致内外壁面爆轰波高度低于中间截面,还会影响燃烧产物的流动状态轴向截面上爆轰波波头产生变形;不同湍流计算方法得到的旋转爆轰流场结构存在相似性,黏性是影响旋转爆轰流场结构的主要原因。研究结果对于揭示边界层和黏性对旋转爆轰的影响机制具有一定的科学意义。

关键词: 大涡模拟, 旋转爆轰燃烧室, 数值模拟, 流场结构

Abstract:

In order to study the characteristics of rotating detonation flow field in annular combustor and the effects of boundary layer, viscosity and turbulence simulation methods on the flow field structure, the open source computational fluid dynamics software OpenFOAM is used to simulate the three-dimensional model of rotating detonation engine (RDE) with hydrogen as fuel and air as oxidant. The characteristics of rotating detonation flow field obtained by Euler equation, large eddy simulation (LES) method and Reynolds-averaged Navier-Stokes (RANS) method are compared and analyzed. The flow field structure from LES simulation is emphatically discussed. The results show that the temperatures of flow fields in the inner, middle and outer sections exhibit no appreciable difference when the slip boundary is applied. However, when the no-slip boundary is utilized, the temperatures of the inner and outer walls are higher than that of the middle section, and the boundary layer will affect the flow velocity of gas in a region close to the wall. As a result, the height of detonation wave on the inner and outer walls is lower than that in the middle section. The boundary layer also affects the flow state of the combustion products, leading to the deformation of wave front on the axial section. The rotating detonation flow field structures obtained by different turbulence simulation methods are similar, indicating that the viscosity is the main factor affecting the rotating detonation flow field structure. The findings are highly significant in terms of elucidating the mechanism by which the viscosity and the boundary layer affect the rotating detonation process.

Key words: large eddy simulation, rotating detonation combustor, numerical simulation, flow field structure

中图分类号:

V231.2⁺2

雷特, 武郁文, 徐高, 邱彦铭, 康朝辉, 翁春生. 基于大涡模拟方法的三维旋转爆轰流场结构研究[J]. 兵工学报, 2024, 45(1): 85-96.

LEI Te, WU Yuwen, XU Gao, QIU Yanming, KANG Chaohui, WENG Chunsheng. Study on Three-dimensional Rotating Detonation Flow Field Structures Based on Large Eddy Simulation[J]. Acta Armamentarii, 2024, 45(1): 85-96.

图/表 18

图1 RDE计算模型

Fig.1 Computational model of RDE

表1 工况设置

Table 1 Case setting

工况	计算方法	边界条件
1	Euler	滑移边界
2	LES	滑移边界
3	RANS	无滑移边界
4	LES	无滑移边界

图2 不同网格尺寸下燃烧室入口的周向压力分布

Fig.2 Pressure distribution along the circumferential direction of Combustion chamber entrance with the change of grid size

图3 不同网格尺寸下旋转爆轰温度场分布

Fig.3 Temperature distribution with the change of grid size during the stead propagation of rotating detonation wave

表2 不同网格尺寸下的爆轰特性参数

Table 2 Detonation characteristic parameters with the change of grid size

网格尺寸/ mm	爆轰波峰值压力/MPa	相对偏差/ %	爆轰波传播速度/(m·s^-1)	相对偏差/ %
0.20	5.83		1688.33
0.10	7.18	18.8	1751.93	3.63
0.08	7.52	4.52	1768.08	0.91

图4 工况4燃烧室径向不同截面处温度和压力云图

Fig.4 Temperature and pressure contours of different slices for Case 4

图5 工况4燃烧室径向不同截面处压力梯度云图

Fig.5 Pressure gradient contours of different slices for Case 4

图6 工况4燃烧室径向不同截面处涡量云图

Fig.6 Vorticity contours of different slices for Case 4

图7 工况4入口周向压力分布

Fig.7 Pressure distribution along the inlet circumferential direction for Case 4

图8 工况2燃烧室径向不同截面处温度和压力云图

Fig.8 Temperature and pressure contours of different slices for Case 2

图9 工况2和工况4近壁面处温度分布对比(θ=30°,z=3.5mm、4.0mm)

Fig.9 Comparison of temperature distributions near the wall for Cases 2 and 4(θ=30°, z=3.5mm and 4.0mm)

图10 工况2和工况4气流轴向速度沿径向分布

Fig.10 Axial velocities for Cases 2 and 4(the intersecting line of surface θ=30° and surface z=4.0mm)

图11 工况2不同截面的涡量云图

Fig.11 Vorticity contours of different slices for Case 2

图12 工况2入口周向压力分布

Fig.12 Pressure distribution along the inlet circumferential direction for Case 2

图13 工况1和工况3不同截面的温度云图

Fig.13 Temperature contours of different slices for Cases 1 and 3

图14 工况1和工况3燃烧室入口周向压力分布

Fig.14 Pressure distributions along the inlet circumferential direction for Cases 1 and 3

图15 工况3和工况4轴向速度比值(θ=30°与z=4.0mm相交直线)

Fig.15 Axial velocity ratios for Cases 3 and 4(the intersecting line of surface θ=30°and surface z=4.0mm)

表3 不同工况下爆轰波特性参数

Table 3 Characteristic parameters of detonation wave in different cases

工况	平均峰值压力/ MPa	平均峰值温度/K	平均传播速度/ (m·s^-1)
工况1	9.16	2794.1	1803.09
工况2	7.45	2680.6	1752.17
工况3	7.54	2645.4	1759.28
工况4	7.08	2654.9	1751.93

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