Thermal Analysis and Design Optimization of Inconel 718 Convergent -Divergent Nozzle for High- Performance Propulsion System

This paper presents an investigation into the design and thermal analysis of a CD nozzle made from Inconel 718, an advanced material known for superior thermal and mechanical properties. The design of the nozzle was based on theoretical computation to achieve optimal performance in a high-temperature and high-pressure environment characteristic of propulsion systems. A detailed geometric model of the nozzle was developed in Autodesk Fusion 360 for complete simulations. Thermal analysis was done to ascertain the heat flow with critical thermal gradients and characteristics of heat flux, which were both necessary to ensure that there was structural integrity at work. Material response to thermal loads through thermal stress analysis is also used to check on the suitability of the design for conditions such as those encountered in rocket propulsion and high-speed jet engines. The results indicate that Inconel 718 nozzle design withstands the thermal stress and maintains efficient working performance. This paper adds valuable knowledge about the thermal performance behavior of CD nozzles to the domain, in which propulsion system design improvements would be enhanced in the engineering area of aerospace.