Flow and thermal analyses of regenerative cooling in non-uniform channels for combustion chamber

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 (ω) 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 ω = 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.