Parametric Testing of a Unique Rotating Detonation Engine Design

Dyer, R.; Naples, Andrew; Kaemming, Thomas A.; Hoke, John; Schauer, Frederick

doi:10.2514/6.2012-121

Cited by 43 publications

(18 citation statements)

References 8 publications

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“…Additionally, there have recently been several numerical investigations into RDEs 3-7 as well as experiments with different configurations [8][9][10][11] for both hydrogen and hydrocarbon fuels. The numerical investigations have typically been twodimensional with hydrogen-air or hydrogen-oxygen, although preliminary three-dimensional results have also been demonstrated 5 .…”

Section: Introductionmentioning

confidence: 99%

Effect of Low Pressure Ratio on Exhaust Plumes of Rotating Detonation Engines

Schwer¹,

Kailasanath²

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Rotating Detonation Engines (RDEs) operating at low injection pressure compared to back pressure are attractive for air breathing engines due to the possibility to greatly simplify the compressor design.Typical RDE simulations that use a mixed subsonic/supersonic boundary at the exhaust plane may not provide an accurate description of the flow field within the expansion region of the combustion chamber. Previous simulations at high pressure showed that the addition of an exhaust plenum causes only minimal changes in the RDE flow field, most significantly at the exhaust plane. The current work examines the flow field and exhaust flow characteristics for low pressure RDEs and include both three-dimensionality effects and the effects of an exhaust plenum. Including three-dimensional effects resulted in a lower detonation wave velocity at low pressure ratios due to detonation wave failure at the inner wall, which was not captured in the twodimensional simulations. While the inclusion of an exhaust plenum to the solution did not change the basic shock wave structure that is set up in the low pressure ratio RDE, the specific strengths and location of the shock waves were different, and resulted in a lower pressure in the fill region of the RDE and thus a lower thermodynamic efficiency. The specific impulse varied by as much as 12.7% between the 2D and 3D results with an exhaust plenum for a pressure ratio of 2.5. Nomenclature a = ratio of micro-injector throat area to injection face area, non-dimensional = specific heat at constant pressure for species k, ergs/(gm K) = specific heat at constant volume for species k, ergs/(gm K) = total energy, ergs/cm 3 = pressure, dynes/cm 2 = mixture ideal gas constant, ergs/(gm K) = ideal gas constant for species k, ergs/(gm K) = temperature, K = induction time, s = velocity of gas, cm/s = reaction rate for reactant, gm/cm 3 = heat release per gram of reactant, ergs/gm = mixture specific heat ratio = specific heat ratio for species k = density, gm/cm 3 = density for species k, gm/cm 3 = induction parameter, gm/cm 3

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Section: Introductionmentioning

confidence: 99%

Effect of Low Pressure Ratio on Exhaust Plumes of Rotating Detonation Engines

Schwer¹,

Kailasanath²

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…The CRDW number was found to dependent on the mass flow rate, equivalence ratio and detonation combustor pressure [6,23,28]. Three different propagation patterns were found by Liu et al [24].…”

Section: Introductionmentioning

confidence: 72%

Experimental investigation on detonation combustion patterns of hydrogen/vitiated air within annular combustor

Wang

Liu

et al. 2015

Experimental Thermal and Fluid Science

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“…The two-dimensional test-rig can be readily reconfigured to replicate other arrangements such as that used by Dyer et al, 6 which has also be tested in the Detonation Engine Research Facility and has been observed to be influenced by mixing/detonation interaction. A schematic of the experiment is given in Figure 1 that shows the locations of the fuel and oxidizer plenums, as well the pertinent dimensions of the device.…”

Section: Experimental Set-upmentioning

confidence: 97%

Propellant Plenum Dynamics in a Two-dimensional Rotating Detonation Experiment

Fotia

Hoke

Schauer

2014

52nd Aerospace Sciences Meeting

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The impact that a detonation wave in a rotating detonation engine has on propellant plenum dynamics is studied through the use of a novel, optically accessible "two-dimenasional" rotating detonation test-rig. The experiment mimics the geometry of a conventional rotating detonation engine design while allowing simultaneous study of the detonation channel and propellant plenums via high-speed schlieren and conventional imaging. The key physical mechanisms that drive the interaction between the dynamics of the propellant plenums and the propagation of a rotating detonation wave are identified and discussed.

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Parametric Testing of a Unique Rotating Detonation Engine Design

Cited by 43 publications

References 8 publications

Effect of Low Pressure Ratio on Exhaust Plumes of Rotating Detonation Engines

Effect of Low Pressure Ratio on Exhaust Plumes of Rotating Detonation Engines

Experimental investigation on detonation combustion patterns of hydrogen/vitiated air within annular combustor

Propellant Plenum Dynamics in a Two-dimensional Rotating Detonation Experiment

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