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dc.contributor.authorSim, Jaeheon
dc.contributor.authorBadra, Jihad A.
dc.contributor.authorIm, Hong G.
dc.date.accessioned2016-03-23T08:50:34Z
dc.date.available2016-03-23T08:50:34Z
dc.date.issued2016-01-02
dc.identifier.citationJaeheon Sim, Jihad A. Badra, and Hong G. Im. "Hollow-Cone Spray Modeling for Outwardly Opening Piezoelectric Injector", 54th AIAA Aerospace Sciences Meeting, AIAA SciTech, (AIAA 2016-1452).
dc.identifier.doi10.2514/6.2016-1452
dc.identifier.urihttp://hdl.handle.net/10754/603517
dc.description.abstractLinear instability sheet atomization (LISA) breakup model has been widely used for modeling hollow-cone spray. However, the model was originally developed for inwardlyopening pressure-swirl injectors by assuming toroidal ligament breakups. Therefore, LISA model is not suitable for simulating outwardly opening injectors having string-like structures at wide spray angles. Furthermore, the varying area and shape of the annular nozzle exit makes the modeling difficult. In this study, a new spray modeling was proposed for outwardly opening hollow-cone injector. The injection velocities are computed from the given mas flow rate and injection pressure regardless of ambiguous nozzle exit geometries. The modified Kelvin-Helmholtz and Rayleigh-Taylor (KH-RT) breakup model is used with adjusted initial Sauter mean diameter (SMD) for modeling breakup of string-like liquid film spray. Liquid spray injection was modeled using Lagrangian discrete parcel method within the framework of commercial CFD software CONVERGE, and the detailed model was implemented by user defined functions. It was found that the new model predicted the liquid penetration length and local SMD accurately for various fuels and chamber conditions.
dc.publisherAmerican Institute of Aeronautics and Astronautics (AIAA)
dc.relation.urlhttp://arc.aiaa.org/doi/10.2514/6.2016-1452
dc.titleHollow-Cone Spray Modeling for Outwardly Opening Piezoelectric Injector
dc.typeConference Paper
dc.contributor.departmentClean Combustion Research Center
dc.contributor.departmentComputational Reacting Flow Laboratory (CRFL)
dc.contributor.departmentMechanical Engineering Program
dc.contributor.departmentPhysical Science and Engineering (PSE) Division
dc.identifier.journal54th AIAA Aerospace Sciences Meeting
dc.conference.date4-8 January 2016
dc.conference.name54th AIAA Aerospace Sciences Meeting
dc.conference.locationSan Diego, California, USA
dc.eprint.versionPost-print
dc.contributor.institutionSaudi Aramco
dc.contributor.sponsorThis work was sponsored by the Fuel Technology Division at Saudi Aramco R&DC. The work at King Abdullah University of Science and Technology (KAUST) was funded by KAUST and Saudi Aramco under the FUELCOM program. We also acknowledge the help and support from Saurav Mitra and Sarangarajan Vijayraghavan from Convergent Science Inc. (CSI).
kaust.personSim, Jaeheon
kaust.personIm, Hong G.
refterms.dateFOA2018-06-13T11:31:19Z
dc.date.published-online2016-01-02
dc.date.published-print2016-01-04


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