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Title: Numerical investigation on Staged transverse injection in a Scramjet combustor and its mixing Augmentation using expansion ramp
Researcher: Sundararaj, K
Guide(s): Dhandapani, S
Keywords: Finite volume based code
Shear stress transport
Upload Date: 29-Oct-2014
University: Anna University
Completed Date: 01/06/2008
Abstract: This work involves an application of the computational fluid newlinedynamics to a problem associated with the flow inside the supersonic newlinecombustor region of a scramjet engine An existing supersonic combustor newlinemodel canonical model consisting of the staged transverse injection behind a newlinerearward facing step was simulated for various flow conditions to investigate newlinethe flow in detail A method for augmenting the mixing of air and the fuel in newlinethe canonical model was suggested by introducing the expansion ramps on newlineboth the sides of the injectors and its effectiveness was tested by numerical newlinemethods The intent was to promote streamwise vorticity by modifying newlinegeometry to improve the mixing characteristics in the combustor newlineThe combustor models were simulated using the finite volume newlinebased code FLUENT and the governing equations were solved by means of a newlinecoupled explicit method using shear stress transport SST K turbulence newlinemodel newline
Pagination: xxii, 162p.
Appears in Departments:Faculty of Mechanical Engineering

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02_certificate.pdf5.8 kBAdobe PDFView/Open
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04_acknowledgement.pdf7.15 kBAdobe PDFView/Open
05_content.pdf386.82 kBAdobe PDFView/Open
06_chapter1.pdf82.28 kBAdobe PDFView/Open
07_chapter2.pdf138.88 kBAdobe PDFView/Open
08_chapter3.pdf17.17 MBAdobe PDFView/Open
09_chapter4.pdf634.94 kBAdobe PDFView/Open
10_chapter5.pdf5.93 MBAdobe PDFView/Open
11_chapter6.pdf18.51 kBAdobe PDFView/Open
12_reference.pdf25.56 kBAdobe PDFView/Open
13_publication.pdf7.48 kBAdobe PDFView/Open
14_vitae.pdf6.6 kBAdobe PDFView/Open

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