Finite element modeling and analysis of heat transfer in a 122-mm diameter solid rocket nozzle

• Main Authors: Gantina, Hendra, Saputra, M. Dito
• Format: Conference Proceeding
• Language: English
• ISSN: 0094-243X; 1551-7616
• DOI: 10.1063/5.0004770

This paper presents the modeling and analysis process of heat transfer that occurs between a solid rocket combustion gas flow with a nozzle. Heat transfer is carried out through convection and radiation which is assumed to occur together and then transferred through conduction on the wall of the nozzle. The nozzle has an outer diameter of 122 mm and consists of 2 different materials, AISI 4340 as the case and graphite as the insert. The load in the form of heat flux is originating from the gas flow from the propellant combustion which enters the nozzle at a temperature of 3000 K for 4.9 seconds. Modeling and analysis were done using MSC. Patran software as the pre-post processor and MSC. Nastran software as a solver based on finite element method. The analysis showed a comparison of the thermal load contribution due to convection and radiation where convection has the dominant portion but the thermal load produced by radiation cannot be neglected. The expected final result of the analysis was the temperature distribution on the wall of the nozzle as long as the nozzle operates.