Abstract
One of the essential issues for spacecraft is maintaining the combustion chamber wall from exceeding acceptable temperatures. The cooling channels' thermal resistance and flow topology can be augmented by adding ribs to the heated surface. The present work proposed a Novel X-shape rib to enhance the thermal efficiency of hydrogen regenerative-cooling channels. The numerical investigation was carried out for the cooling system with rectangular and trapezoidal X-shape ribs at various attack angles (30°,45°, and 60°). The investigation findings demonstrated that both X-shape rib constructions optimized the cooling system's thermal efficiency. Since the trapezoidal X-shape ribs' chamfering angle reduces the resistance to coolant flow, the pressure loss of these ribs is less than rectangular ribs. Additionally, the heat transfer rate is maximum for 30° X-shape ribs, decreasing gradually with the increase of the X-shape rib's attack angle. Furthermore, compared to a smooth channel, the rectangular 30° X-shape ribs enhance the thermal efficiency by 44% while reducing the wall temperature by 24%.
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