Title:
Parametric study of liquid fuel jet in crossflow at conditions typical of aerospace applications

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dc.contributor.advisor Zinn, Ben T.
dc.contributor.author Reichel, Jonathan R. en_US
dc.contributor.committeeMember Lubarsky, Eugene
dc.contributor.committeeMember Seitzman, Jerry M.
dc.contributor.department Aerospace Engineering en_US
dc.date.accessioned 2008-06-10T20:39:08Z
dc.date.available 2008-06-10T20:39:08Z
dc.date.issued 2008-01-02 en_US
dc.description.abstract Due to the fact that cross flow fuel injection is widely used in gas turbine engines combustors, it is important to understand the mechanisms that control the spray breakup within the cross flow. In spite of a lot of work done in this field, very few studies have been carried out under conditions typical of aerospace applications. This thesis describes a series of experiments carried out to simulate these conditions in order to characterize the formation of spray within a high speed, high pressure and high temperature cross flow close to conditions typical of aerospace applications. Fuel spray characteristics were studied for Jet-A fuel injected into a crossflow (M=0.2 and M=0.35) of preheated (T=555K) air at a chamber pressure of 4 atm. It was seen that larger droplets could be found in the periphery of the spray while smaller droplets could be found closer to the injection plate. In most cases, the droplet velocities were seen to lag the incoming air flow velocity by 20-40% and a spray hat structure was created by the jet in crossflow near the injection wall most likely caused by vortex flow created around the liquid column (jet). The influence of Weber number was then studied. It was seen that shear breakup mechanism dominates at We greater than about 100. Droplets diameters were found to be in the range of 15-30 microns for higher values of We, while larger droplets (100-200 microns) were observed at Weber number of 33. The initial sharp-edged injector was then replaced by a smooth-edged injector having. Spray characteristics from the two injectors were compared. The spray produced by the smooth countersunk injector penetrated further into the test section away from the injector orifice by approximately 2mm. This injector also produced droplets with a significantly smaller mean diameter (D10). The average droplet velocities in the vertical direction deviated from the incoming air flow velocity to a lesser degree using the countersunk injector. Meanwhile, droplets from this injector had a higher average velocity in the direction of fuel injection between the core of the spray and the orifice wall. en_US
dc.description.degree M.S. en_US
dc.identifier.uri http://hdl.handle.net/1853/22590
dc.publisher Georgia Institute of Technology en_US
dc.subject Fuel spray characteristics diameter velocity cross en_US
dc.subject.lcsh Fuel pumps
dc.subject.lcsh Jet engines
dc.subject.lcsh Spraying
dc.title Parametric study of liquid fuel jet in crossflow at conditions typical of aerospace applications en_US
dc.type Text
dc.type.genre Thesis
dspace.entity.type Publication
local.contributor.advisor Zinn, Ben T.
local.contributor.corporatename College of Engineering
local.contributor.corporatename Daniel Guggenheim School of Aerospace Engineering
local.relation.ispartofseries Master of Science in Aerospace Engineering
relation.isAdvisorOfPublication 982cb5ab-69b0-484e-b11e-931f10649bd8
relation.isOrgUnitOfPublication 7c022d60-21d5-497c-b552-95e489a06569
relation.isOrgUnitOfPublication a348b767-ea7e-4789-af1f-1f1d5925fb65
relation.isSeriesOfPublication 09844fbb-b7d9-45e2-95de-849e434a6abc
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