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International Heat Transfer Conference 16

ISSN: 2377-424X (online)
ISSN: 2377-4371 (flashdrive)

NUMERICAL INVESTIGATION ON THE PERFORMANCE OF TRANSPIRATION COOLING COMBINED WITH FILM COOLING

Rui Ding
Department of Thermal Science and Energy Engineering, University of Science and Technology of China, Hefei 230027, PR China

Fei He
Department of Thermal Science and Energy Engineering, University of Science and Technology of China, Jinzhai Road 96, Hefei 230027, PR China

Jianhua Wang
Department of Thermal Science and Energy Engineering, University of Science and Technology of China, Jinzhai Road 96, Hefei 230027, PR China

Longsheng Tang
Beijing Power Machinery Research Institute, Beijing 100074, PR China

Guangqi Dong
Beijing Power Machinery Research Institute, Beijing 100074, PR China

DOI: 10.1615/IHTC16.ctm.023577
pages 3823-3832


キーワード: Thermal management, Numerical simulation and super-computing, a new composite cooling method, transpiration cooling, film cooling

要約

Aimed at solving the thermal protection problem of a leading wedge under high Mach number, this study presents a new composite cooling method which combines transpiration cooling with film cooling. The leading wedge has a radius of 3mm, a wedge angle of 14 degree, and a length of 114mm. The active thermal protection of the leading wedge can be achieved by double mechanisms cooperatively: Transpiration cooling is arranged discontinuously from the head to the tail, which could resist the main part of the aerodynamic heat by the adequate heat exchange between coolant and solid in the millions of pores when coolant permeates through the porous structure; An evenly-covered film forms after the coolant spraying out of the porous surface and extends to the downstream, which could protect the interval area without transpiration cooling arranged To obtain a better understanding of the cooling performance and probe the law between cooling performance and influence factors, the fluid flow and heat transfer characteristics of the composite cooling process are numerically studied. The results show that: (1) The effective downstream film length increases almost linearly with coolant inlet velocity and transpiration cooling length, while their comprehensive cooling performances are quite different ; (2) Compared with a single transpiration cooling structure, the composite cooling structure can reduce the porous area by 28.1% and the coolant amount by 15.7% respectively. These conclusions provide the engineers of future hypersonic vehicles with a relatively comprehensive reference for optimal design of transpiration cooling system

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