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

Show full item record

Please use this identifier to cite or link to this item: http://hdl.handle.net/1853/22590

Title: Parametric study of liquid fuel jet in crossflow at conditions typical of aerospace applications
Author: Reichel, Jonathan R.
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.
Type: Thesis
URI: http://hdl.handle.net/1853/22590
Date: 2008-01-02
Publisher: Georgia Institute of Technology
Subject: Fuel spray characteristics diameter velocity cross
Fuel pumps
Jet engines
Spraying
Department: Aerospace Engineering
Advisor: Committee Chair: Ben Zinn; Committee Member: Eugene Lubarsky; Committee Member: Jerry Seitzman
Degree: M.S.

All materials in SMARTech are protected under U.S. Copyright Law and all rights are reserved, unless otherwise specifically indicated on or in the materials.

Files in this item

Files Size Format View
reichel_jonathan_r_200805_mast.pdf 2.644Mb PDF View/ Open

This item appears in the following Collection(s)

Show full item record