DTIC ADA618745: Effect of Swirl on an pdf

DTIC ADA618745: Effect of Swirl on an

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In this study a series of three-dimensional unsteady reacting flow simulations are used to investigate the effect of swirl on the instability amplitude of a single-element gas-gas rocket combustor. The baseline combustor of interest is unstable because of a fuel cut-off event caused by the high-pressure waves in the combustor. Previous two-dimensional simulations have shown that swirl reduces the amplitude of the pressure oscillations compared with that of the baseline configuration. The current three-dimensional simulations show that swirl is indeed able reduce the amplitude of the instabilities, albeit not to the same extent observed in the two-dimensional simulations. We further observe that the enhanced mixing due to the swirling flow leads to a reduction in the recovery time associated with the fuel cut-off event, thereby allowing the combustor to experience a more continuous heat release. Nevertheless, unlike the two-dimensional case, the three-dimensional simulations show that the flame does not stay anchored to the dump-plane, which explains the higher relative amplitudes in this case

• Creator/s: Defense Technical Information Center
• Date: 7/1/2014
• Year: 2014
• Book Topics/Themes: DTIC Archive, , AIR FORCE RESEARCH LAB EDWARDS AFB CA AEROSPACE SYSTEMS DIRECTORATE, *GASES, *ROCKET ENGINES, AMPLITUDE, BASE LINES, COMBUSTORS, CONFIGURATIONS, FLAMES, FLOW, FUELS, HEAT, HIGH PRESSURE, INSTABILITY, MIXING, OSCILLATION, RECOVERY, REDUCTION, RELEASE, ROCKETS, SIMULATION, THREE DIMENSIONAL, TWO DIMENSIONAL, VARIABLE PRESSURE, WAVES

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