ROCKET ENGINE NOZZLE COOLING

Abstract

Rockets are such fascinating machines that when we look up we feel how far our universe has expanded over the years. From the beginning of civilization humans always looked up in the sky and got inspired. Always wanted to fly and get into space to explore what lies ahead. Counter argues by philosophers that humans first need to focus on earth but few audacious men and women break the jinx and build vehicles after years of failures and hard work which takes humanity to another level. It is because of that fearless and moonshot vision that we achieved a lot in terms of communication and connectivity. Humans landed on moon & mars, sent satellites in orbit and sent rovers deep into space and all of this was and is possible because of thrust produced in tons due to propulsion. Modern rockets used in space missions have thrust generated of thousands of newtons. On an average countries and private rocket industries launch more than 100 rockets carrying satellites every year. Thrust generated due to burning of propellants and oxidiser results in huge temperature and heat generation. Most heat flux occurs near the proximity of the nozzle throat which needs cooling as combustion temperature and heat is a threat to structural metals. We have progressed so far and further deep space exploration needs better machines structurally to handle thermal temperature and also fuel efficiency and there comes cooling techniques. Different cooling techniques have been implemented and experiment is still in continuation to combine different such mechanisms to achieve better results. Scientists have inspired the future generation to continue R & D on cooling techniques with different nozzle designs, materials and cooling methods to achieve superior cooling experiences. In this dissertation rocket nozzle cooling methods have been discussed and efficacy on rocket chambers and nozzles. In this dissertation experimental and numerical modelling investigation has been performed and is also highlighted with results and discussions. A spacex falcon f9 rocket is made in cad also analysed with volume enclosure to find out thermal stress and maily a merlin 1d engine is designed and regenerative cooling is performed and results has been compared with combined regenerative + ablative & film cooling and the cooling results are shown along with thermal simulation analysis. This dissertation also brings in light of a critical research gap to be addressed in future.