Analysis of advanced cooling strategies for rocket engines conveying ternary hybrid nanofluids with second slip conditions and melting heat transfer

Effective cooling in rocket engines is essential to prevent overheating and ensure efficient performance under extreme operating conditions. This study presents a comprehensive investigation into advanced cooling strategies for rocket engines utilizing ternary hybrid nanofluids specifically Graphene-Aluminum Oxide-Silicon Dioxide (Graphene-Al₂O₃-SiO₂) dispersed in kerosene and Copper-Aluminum Oxide-Silicon Dioxide (Copper-Al₂O₃-SiO₂) dispersed in kerosene under the influence of second-order velocity slip and melting heat transfer. The mathematical model also includes the buoyancy forces and random particle motion. The model incorporates non-linear partial differential equations, which are transformed using similarity variables and solved numerically. The dimensionless ordinary differential equations are solved using the collocation weighted residual technique (CWRT) with the help of Mathematica 11.3 software, and provide a deep discussion. Results indicate that fluid temperature increases significantly with melting and the first thermal slip parameters. The second solutal slip parameters have a notable influence on the mass transfer coefficients. Among the studied nanofluids, Graphene-Al₂O₃-SiO₂/kerosene demonstrates superior performance compared to Copper-Al₂O₃-SiO₂/kerosene, making it a more effective choice for applications like rocket engine cooling and fuel systems. The results establish the potential of kerosene-based ternary hybrid nanofluids as efficient coolants for next-generation aerospace propulsion systems.