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- W2130310109 abstract "Uni-element liquid rocket experiments were completed for two different swirl coaxial injector configurations and a shear coaxial injector configuration using liquid oxygen/gaseous methane propellants. Several different non-intrusive optical techniques such as OH planar laser induced fluorescence, OH* chemiluminescence, laser light scattering and shadowgraph imaging, were employed to observe flame position and liquid core structure. All measurements were made in the near injector region of the chamber for steady state chamber pressures of approximately 4.14 MPa and propellant mass flowrates of 0.118 kg/s and 0.039 kg/s for liquid oxygen (LOX) and gaseous methane respectively. The two swirl injectors studied varied in the size of the methane annulus, maintaining the LOX post diameter constant. The shear coaxial injector was identical in size to the swirl injector with the smallest fuel annulus but the liquid flow was not swirled. The application of optical diagnostics, particularly those involving simultaneous measurements using two different techniques, provided detail information on the spray and flame structure for each injector. OH radicals were observed to be located in fuel rich areas of the flow while OH* chemiluminescence resided very close to the edge of LOX core as determined by light scattering measurements. Differences in the OH-PLIF signal location in this study and previous studies using hydrogen (H2) and LOX were explained by differences in injector geometry and mixing processes. The flow structures, atomization process and mixing were found to have a major effect on the location of OH-PLIF, OH* chemiluminescence and the combustion efficiency." @default.
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- W2130310109 date "2006-01-09" @default.
- W2130310109 modified "2023-09-27" @default.
- W2130310109 title "Shear and Swirl Coaxial Injector Studies of LOX/GCH4 Rocket Combustion Using Non-Intrusive Laser Diagnostics" @default.
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- W2130310109 doi "https://doi.org/10.2514/6.2006-757" @default.
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