Article ID | Journal | Published Year | Pages | File Type |
---|---|---|---|---|
4991271 | Applied Thermal Engineering | 2017 | 29 Pages |
Abstract
Regenerative cooling is considered one of the most prospective thermal protection techniques in hypersonic vehicles. However, the non-uniform flow distribution in the cooling channels has the potential to lead the combustion chamber to overheat. In the present study, the regenerative cooling channels designed in a variety of non-uniform patterns are proposed. The conjugated flow and heat transfer behaviors of coolant and solid combustion chamber are numerically investigated. The scaling factor (Ω), i.e., height/width ratio, channel inlet/outlet manifold configuration, and relative angle (Ï) of the inlet/outlet tube on flow and heat transfer characteristics are discussed. The numerical prediction is in reasonable agreement with previous numerical and experimental data. Results reveal that the basic configuration (Ω = 1) contributes dramatic non-uniform flow in the channels near the inlet tube. The non-uniformity becomes more evident in the case of Ï = 60°. The scaling factor (Ω) exerts stronger influence on flow distribution in channels and the reformed case of Ω = 0.9 for Ch-1-4 gives the best flow uniformity and temperature distribution. The flow distribution is less sensitive to the outlet manifold than the inlet manifold.
Related Topics
Physical Sciences and Engineering
Chemical Engineering
Fluid Flow and Transfer Processes
Authors
Tingting Jing, Guoqiang He, Wenqiang Li, Fei Qin, Xianggeng Wei, Yang Liu, Zhiyuan Hou,