ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Thermal protection and drag reduction characteristics of discrete hole film cooling in high Mach number combustor
Received date: 2023-05-31
Revised date: 2023-06-25
Accepted date: 2023-12-05
Online published: 2023-12-21
Supported by
National Natural Science Foundation of China(52176037)
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.
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 AERONAUTICAET ASTRONAUTICA SINICA, 2024 , 45(11) : 529075 -529075 . DOI: 10.7527/S1000-6893.2023.29075
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