Microjet based noise control of supersonic jets on carrier decks
Name
880718455-MIT.pdf
Description
Full printable version
Size
21.83 MB
Format
Adobe PDF
Checksum (MD5)
58e24b1989dcfd00a787d58af585e9c0
Author(s)
Ragaller, Paul Aaron
Advisor(s)
Anuradha Annaswamy.
Date Issued
2014
Publisher
Massachusetts Institute of Technology
Abstract
The effectiveness of ground plane water microjet control on the noise generated by a supersonic, ideally expanded, Mach 1.5, impinging jet was determined. Using a converging-diverging nozzle with a design Mach number of 1.5, the jet was operated at temperatures ranging from 60 to 1700°F. Six microjets were installed in the ground plane in a circular configuration at a radial spacing of 1.53 nozzle diameters, and an angle of 0 and 300 to tangential. Baseline and control temperature readings at the ground plane and acoustic readings at the sideline angles of 70, 80 and 900 were obtained with the microjets operating at pressures ranging from 200 to 900 psig. Additionally, in order to determine the fluid-mechanical mechanisms responsible for the control effect on the noise, high-speed images and video were obtained and analyzed. From measurements of the average and fluctuating ground plane temperature measurements, it was found that modifications to the High Temperature Supersonic Jet Facility at Florida State University allowed for measurements of impinging jet characteristics that were congruent with previous studies. Ground plane microjets were found to be effective in reducing feedback tones as a result of the impinging geometry of the jet. They were also effective at reducing the broadband spectral noise for lower temperatures. At temperatures higher than 600°F, however, an increase in the broadband noise was produced as a result of water microjets. At microjet injection pressures at and above 800 psig, additional noise suppression was achieved for the cold operating condition. From obtained high-speed images and video, it was found that the breakup of the microjet in the shear layer (of the shear variety), and the entrainment of fine mist into the inception of the shear layer was responsible for the reduction in strength and size of large-scale vortical structures. At higher pressures, additional noise suppression is produced as a combined result of the breaking of the feedback loop and the microjet's ability to penetrate to the high-speed side of the shear layer.
Description
Thesis: Ph. D., Massachusetts Institute of Technology, Department of Mechanical Engineering, 2014.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 131-134).
Subjects
Mechanical Engineering.
MIT Department
Massachusetts Institute of Technology. Department of Mechanical Engineering
Terms of Use
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