RBCC Rocket Nozzle: Modelling and Dynamic Analysis

The ejector mode concept in rocket-based combined cycles presents an opportunity to derive thrust from atmospheric air, thereby diminishing fuel consumption and reducing overall rocket launch costs. This project concentrates on crafting a three-dimensional rocket nozzle featuring the ejector effect. The design involves a diverging section passing through a non-axisymmetric gate or clover on the outer perimeter, creating a void for air intake into the center of an annular rocket exhaust stream. The primary objective is to pinpoint the optimal design among three configurations with varying clover numbers (3, 4, and 5). Flow analyses, utilizing numerical simulations and a predefined Mach number distribution, were conducted, incorporating viscous simulations with the k- turbulence model. Results reveal that the nozzle with 4 clovers outperforms those with 3 or 5 clovers, aligning closely with predefined outlet Mach numbers and demonstrating effectiveness.

Autorentext

Dr. A Kalyan Charan, an Assistant Professor at Matrusri Engineering College, he has 15 years of teaching experience, published 25 technical papers, and successfully completed 5 research projects and he is a life member of ISTE, SAE INDIA, IEI, and ISRD