International Journal of Advancements in Technology
Open Access

Abstract

Modern rockets used in space missions have thrust generated of thousands of newtons. Thrust generated due to burning of propellants and oxidiser results in huge temperature and heat generation. Most heat flux occurs near proximity of nozzle throat which needs cooling as combustion temperature and heat is a threat to structural metals. This paper reviews different cooling methods and efficacy on rocket chambers and nozzles. In this paper experimental and numerical modelling investigation done by researchers is also highlighted with results and discussions. This paper also brings in light of critical research gap to be addressed by future generations. A rocket nozzle must absorb a wide range of loads caused by thermal expansion and contraction, as well as shocks from startup pressurisation and flight accelerations. A rocket engine nozzle is provided that is capable of dampening nozzle vibrations generated during operation. The nozzle has an annular closed chamber surrounding it near the gas exhaust end. Within the chamber, there is a dense but unrestricted particulate mass capable of frictional movement.

Author Info

Received: 02-Jul-2022, Manuscript No. IJOAT-22-001-PreQc-22; Editor assigned: 05-Jul-2022, Pre QC No. IJOAT-22-001-PreQc-22 (PQ); Reviewed: 20-Jul-2022, QC No. IJOAT-22-001-PreQc-22; Revised: 27-Jul-2022, Manuscript No. IJOAT-22-001-PreQc-22 (R); Published: 08-Aug-2022

Copyright: This is an open access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.