Study on Three-dimensional Rotating Detonation Flow Field Structures Based on Large Eddy Simulation

doi:10.12382/bgxb.2022.0470

Abstract

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

CLC Number:

V231.2⁺2

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.

Figures/Tables 18

Fig.1 Computational model of RDE

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

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

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

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

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

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

Fig.6 Vorticity contours of different slices for Case 4

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

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

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

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

Fig.11 Vorticity contours of different slices for Case 2

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

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

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

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

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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