This Is AuburnElectronic Theses and Dissertations

Show simple item record

Life Prediction Analysis of a Subscale Rocket Engine Combustor using a Fluid-Thermal-Structural Model


Metadata FieldValueLanguage
dc.contributor.advisorFoster, Winfred
dc.contributor.advisorGross, Roberten_US
dc.contributor.advisorTippur, Hareeshen_US
dc.contributor.authorSarwade, Rohiten_US
dc.date.accessioned2008-09-09T21:19:05Z
dc.date.available2008-09-09T21:19:05Z
dc.date.issued2006-05-15en_US
dc.identifier.urihttp://hdl.handle.net/10415/519
dc.description.abstractThe focus of this thesis was on performing a non-linear transient fluid-thermal-structural analysis of the cooling jacket for a scale model rocket engine thrust chamber. The model was for a water cooled annular plug nozzle thruster. The objective of this work was to predict the number of firing cycles the chamber could undergo without failure. The analysis consisted of multiple temperature and pressure firing cycles representing startup, shutdown and steady state operation of the engine. Two separate numerical codes combining fluid, thermal and structural analyses were used to obtain the solution. Non-linear strains were observed after 20 firing cycles and failure was predicted to occur after 255 cycles.en_US
dc.language.isoen_USen_US
dc.subjectAerospace Engineeringen_US
dc.titleLife Prediction Analysis of a Subscale Rocket Engine Combustor using a Fluid-Thermal-Structural Modelen_US
dc.typeThesisen_US
dc.embargo.lengthNO_RESTRICTIONen_US
dc.embargo.statusNOT_EMBARGOEDen_US

Files in this item

Show simple item record