BUILD AND TEST A SMALL SCALE LIQUID ROCKET ENGINE

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dc.contributor.advisorBhattarai, Nawaraj
dc.contributor.authorPaudel, Bijay
dc.contributor.authorSah, Dhaneshwar
dc.contributor.authorDas, Dipak
dc.contributor.authorTeli, Pritam Sah
dc.date.accessioned2024-08-13T06:40:29Z
dc.date.available2024-08-13T06:40:29Z
dc.date.issued2024-03
dc.descriptionA liquid rocket engine is a type of propulsion system that uses liquid propellants, typically a fuel and an oxidizer, stored separately in tanks and then mixed and burned in a combustion chamber to produce thrust. Liquid rocket engines are widely used in various space exploration missions, satellite launches, and military applications due to their high performance and controllability.
dc.description.abstractA liquid rocket engine is a type of propulsion system that uses liquid propellants, typically a fuel and an oxidizer, stored separately in tanks and then mixed and burned in a combustion chamber to produce thrust. Liquid rocket engines are widely used in various space exploration missions, satellite launches, and military applications due to their high performance and controllability. In this paper the components of a liquid rocket engine i.e nozzle, combustion chamber and fuel injector were designed and tested. Two fuels LPG and kerosene were combusted with gaseous oxygen to generate thrust. The components were simulated in ANSYS to test their performance. Pressure fed system was adopted to pressurize kerosene and LPG didn’t needed to be pressurized as it was already stored under pressure. Multiple test results were recorded and exhaust plume was analyzed. The thrust of magnitude 12N and 30N was measured in two tests and in other tests only exhaust plume was analyzed. Both the tests had to stopped midway due to chamber and injector failure due to high temperature produced in chamber. The yellow flame was observed in the exhaust plume which is caused by the glow of hot unburnt carbon particles produced due to incomplete combustion. So, further works on materials, manufacturing process and cooling is required.
dc.identifier.urihttps://hdl.handle.net/20.500.14540/22678
dc.language.isoen
dc.publisherI.O.E
dc.subjectLiquid Rocket Engine
dc.subjectNozzle
dc.subjectCombustion Chamber
dc.subjectFuel Injector
dc.titleBUILD AND TEST A SMALL SCALE LIQUID ROCKET ENGINE
dc.typeTechnical Report
local.academic.levelOther
local.institute.titleInstitute of Engineering
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