Combustion Gas Radiation Analysis for Space Propulsion Test Rig
Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Numerical heat transfer analysis and simulation is one of the important tasks which should be performed prior to an experimental testing of any propulsion system. Successful analysis will help to investigate possible problems and errors which could occur during the real test. This will give a chance to improve the system and to perform a successful practical test. This project is focused on the SPTR which is under development by Cranfield Space Research Center. Heat transfer analysis to the injector of a liquid propellant rocket engine is the primary task of the project. The particular case is very much interested in the radiant heat transfer from hot gases and convective re-circulation of the hot gases since the heat transfer to the injector is a combination of both. Initially various existing methods for predicting thermal radiation from transparent hot gases has been studied. During the next phase of the project a convenient method has been selected in order to develop a computer model for the CFD analysis of combustion gas radiation and hot gas re-circulation in the SPTR. Background calculations for determining expected flame temperature has been done in order to validate the procedure for the computer modelling. Various results have been analysed for different model configurations and determined the appropriate one for the analysis. Finally the obtained results are validated using calculated expected values and results obtained from AFAL Specific Impulse Program for the similar case. A significant role of radiation heat transfer to the total heat transfer is identified at the injector wall and nozzle exit during analysis. Various heat transfer quantities such as total temperature, radiation temperature, effects of combustion products and effects of hot gas re-circulation in the combustion chamber for the SPTR are investigated.
Place, publisher, year, edition, pages
2016. , 91 p.
Technology, CFD, Emissivity, Injector, Excitation Energy, Spectrum, Radiation, Combustion, Propulsion
IdentifiersURN: urn:nbn:se:ltu:diva-51041Local ID: 844fdfaa-3118-4eac-9621-fcd821626a58OAI: oai:DiVA.org:ltu-51041DiVA: diva2:1024404
Subject / course
Student thesis, at least 30 credits
Space Engineering, master's level
Validerat; 20160407 (global_studentproject_submitter)2016-10-042016-10-04Bibliographically approved