Publication:
Enhancement of fuel regression rate for hybrid rockets by introducing novel coaxial tube injector

dc.contributor.coauthorKahraman, Mehmet
dc.contributor.coauthorÖzkol, İbrahim
dc.contributor.departmentDepartment of Mechanical Engineering
dc.contributor.kuauthorKarabeyoğlu, Mustafa Arif
dc.contributor.schoolcollegeinstituteCollege of Engineering
dc.date.accessioned2024-11-09T22:59:02Z
dc.date.issued2020
dc.description.abstractLow fuel regression rate is one of major drawback of hybrid rocket motors. A new scalable injector concept is proposed in this study to provide an enhancement for fuel regression rate. As different than the classical head-end axial injectors, offered injector called Coaxial Tube Injector-CTI is lying through the fuel grain centre and could capable to inject oxidizer both axial and radial directions. Fuel used in this study is paraffin with some polymeric additives and the oxidizer is N2O (L) under the gaseous oxygen supercharge. 30 hot firings were conducted, and results revealed that the CTI configuration provides deterministic increase in fuel regression rate which is 5.3 times higher than paraffin motor with axial injector. This great enhancement gives ability to the designer to change the motor sizing sharply according to the requirements. Verifying regression rate enhancement with CTI configuration under the insight of hot firings provides to develop a non-dimensional, scalable regression rate relation. Conducted tests revealed that the radial fluxes have great contribution to the regression rate rather than the axial fluxes and non-dimensional equation was developed under this information. Influence of each parameters in non-dimensional equation were determined by curve-fit effort. Developed scalable regression rate equation was used to design the internal ballistic of motors for last two tests to verify the equation and results showed the developed rule works well. Consequently, very high regression rates could be achieved with proposed CTI configuration and non-dimensional regression rate relation was developed for CTI configuration as a design tool for scale-up systems.
dc.description.indexedbyScopus
dc.description.openaccessYES
dc.description.publisherscopeInternational
dc.description.sponsoredbyTubitakEuN/A
dc.description.volume2020
dc.identifier.doi10.2514/6.2020-3733
dc.identifier.isbn978-162410602-6
dc.identifier.scopus2-s2.0-85091297737
dc.identifier.urihttps://doi.org/10.2514/6.2020-3733
dc.identifier.urihttps://hdl.handle.net/20.500.14288/7826
dc.keywordsParaffins
dc.keywordsPropulsion
dc.keywordsRockets
dc.keywordsAxial injectors
dc.keywordsFuel regression rates
dc.keywordsHybrid rocket motors
dc.keywordsInternal ballistic
dc.keywordsNon-dimensional equations
dc.keywordsPolymeric additives
dc.keywordsRadial direction
dc.keywordsRegression rate
dc.keywordsFuel additives
dc.language.isoeng
dc.publisherAmerican Institute of Aeronautics and Astronautics
dc.relation.ispartofAIAA Propulsion and Energy 2020 Forum
dc.subjectEngineering
dc.titleEnhancement of fuel regression rate for hybrid rockets by introducing novel coaxial tube injector
dc.typeConference Proceeding
dspace.entity.typePublication
local.contributor.kuauthorKarabeyoğlu, Mustafa Arif
local.publication.orgunit1College of Engineering
local.publication.orgunit2Department of Mechanical Engineering
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