Design Criteria, Experimental Studies of Supersonic Shock Wave Interaction with Film Cooling, and High-Pressure Subscale Combustion Chamber of Film Cooling Liquid-Propellant Rocket Engines are all covered in this review study. Using earth-storable, space-storable, and cryogenic propellant combinations, the study establishes the applicability of film cooling to rocket engines in the high thrust range. The study's findings are given in this publication. Additionally, data from studies mixing different types of propellant were used to evaluate the analytical model's accuracy. Tests employing supersonic film cooling were done in the wind tunnel to investigate the impact of external shock waves on supersonic film cooling. The coolant injection was carried out at a supersonic speed. Furthermore, we discuss the important factors that impact film cooling, such as the efficacy of the injected film and the reduction in wall temperature. A high-pressure subscale combustion chamber was used in conjunction with a combination of cryogenic propellants to conduct the experimental investigation. It is critical to consider the increase in the coefficient of heat transfer.
Cherkupalli, Pradnya Engineer Graduate and Sandeep, Juluru Prof.
"Film Cooling Method In Liquid Rocket Engine,"
Graduate Research in Engineering and Technology (GRET): Vol. 1:
7, Article 8.
Available at: https://www.interscience.in/gret/vol1/iss7/8
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