高马赫数燃烧室离散孔燃料膜热防护和减阻特性

doi:10.7527/S1000-6893.2023.29075

Abstract

Abstract:

To investigate the influence of hydrocarbon fuel chemical reactions on the film cooling and drag reduction characteristics of discrete holes， we selected four types of discrete hole configurations： Cylindrical Hole （CH）， Multiple Hole （MH）， Double Jet Hole （DJH）， and Contraction Expansion Hole （CEH）. A numerical study of discrete hole film in a high Mach number combustor was conducted to compare the effects of hydrocarbon fuel chemical reactions on the film cooling and drag reduction characteristics of different discrete holes. The results indicate that chemical reactions of hydrocarbon fuels reduce the momentum of the cooling jet near the wall and weaken the intensity of the vortex structure formed by the cooling jet. However， these chemical reactions improve the film cooling efficiency of discrete holes through endothermic cracking reactions， leading to an expanded spanwise coverage of the film cooling. Specifically， the double jet hole and contraction expansion hole exhibit a large spanwise velocity component and extensive cooling coverage. Furthermore， the drag reduction effect of hydrocarbon fuel combustion in the boundary layer contributes to a reduction in wall shear stress， while combustion itself leads to a decrease in vortex structure dissipation. However， the mixing process， which is dominated by vortex structures， is reduced due to a decrease in the degree of mixing， ultimately weakening the drag reduction performance of combustion. The drag reduction effects of the multiple hole and contraction expansion hole are calculated to be 27.4% and 18%， respectively.

Key words: supersonic film cooling, hydrocarbon fuel, discrete film hole, drag reduction, boundary layer combustion

CLC Number:

V235.2

Dingyuan WEI, Silong ZHANG, Jianfei WEI, Jingying ZUO, Xin LI, Wen BAO. Thermal protection and drag reduction characteristics of discrete hole film cooling in high Mach number combustor[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529075-529075.

Figures/Tables 26

Fig.1

Fig.2

Table 1

Table 2

Boundary conditions

入口

条件

静压

P/MPa

总压

P_t/MPa

总温

T_t/K

流量

m/（kg·s^-1）

介质

主流

0.229

0.703

3 311

$Y N 2$ =0.77，

$Y O 2$ =0.23

冷却流

0.229

700

0.002 27

Y C 10 H 22

=1.0

Table 2

Table 3

Fig.3

Fig.4

Fig.5

Table 4

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Table 5

Average wall shear stress under different conditions

类型	$τ w, N F ¯$ /Pa	$τ w, N R ¯$ /Pa	$τ w, R ¯$ /Pa	降幅/%
圆柱型孔	897.8	1 044.4	687.6	23.4
交错叉排孔	900.9	991.4	653.3	27.4
交叉射流孔	901	1 023.2	661	26.6
收缩扩张孔	894.1	1 093.2	732.6	18.0

Table 5

Table 6

Global skin⁃friction resistance coefficient near wall and drag reduction efficiency statistics

类型	$C f, N F$	$C f, N R$	$C f, R$	$R$	$G$	$S$
圆柱型孔	0.003 25	0.003 55	0.002 58	0.204	0.058	-3.317
交错叉排孔	0.003 27	0.003 50	0.002 44	0.255	0.074	-3.180
交叉射流孔	0.003 27	0.003 53	0.002 38	0.273	0.079	-3.198
收缩扩张孔	0.003 29	0.003 66	0.002 57	0.219	0.043	-4.872

Table 6

Fig.16

Fig.17

Fig.18

Fig.19

Fig.20

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类型	L	α/（°）	β/（°）	l	w
圆柱型孔	5D	30
交错叉排孔	5D	30		3D	D
交叉射流孔	5D	30	30	3D	D
收缩扩张孔	5D	30	6.5	2D	0.2D

网格	网格单元N	特征网格尺寸h/（10^-4 m）	细化因子r
1	758 460	6.848 8
2	1 577 230	5.365 7	1.3
3	3 550 410	4.094 2	1.3

入口条件	马赫数Ma	静压P/MPa	静温T/K	介质
主流	1.95	0.319	297	空气
冷却流	1.0	1.25	297	空气

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Thermal protection and drag reduction characteristics of discrete hole film cooling in high Mach number combustor

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