Propellant Plenum Dynamics in a Two-dimensional Rotating Detonation Experiment

Fotia, Matthew; Hoke, John; Schauer, Frederick

doi:10.2514/6.2014-1013

Cited by 26 publications

(8 citation statements)

References 6 publications

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“…From the above observations, we have enough information to propose a mechanism behind the amplitude modulated spatially non-homogenous instability in an RDC. Fotia et al [39], in their two-dimensional experimental RDC study, have noted that the trailing shock wave (attached to the bottom of the detonation wave, as established by Schwer and Kailasanath [40]) moves at about 60% of the detonation wave speed. Owing to this relative velocity between the detonation wave in the combustor and the trailing shock wave in the reactants plenum, they postulated a "pressure beating" event when the next detonation wave lap interacts with the trailing shock wave in the plenum from the prior lap.…”

Section: Detonation-induced Lfi: Spatially Non-homogenous Oscillationsmentioning

confidence: 94%

Types of Low Frequency Instabilities in Rotating Detonation Combustors

Anand

Gutmark

2018

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Rotating detonation combustors (RDC) offer a significant prospective increase in stagnation pressure across it owing to the presence of one or more rotating detonation waves spinning inside the combustor at the kilohertz regime. Naturally, considerable research impetus has been directed towards this technology in recent years to understand the driving mechanics to harness the associated potential of pressure gain combustion (PGC). One such area of focus has been the off-design operating modes of these devices which cause a myriad of instabilities. The current paper is focused towards the discussion of one such instability regime-low frequency instabilities (LFI)-in RDCs. We review three types of LFIs in RDCs based on prior findings, and propose mechanisms for the same.

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Section: Detonation-induced Lfi: Spatially Non-homogenous Oscillationsmentioning

confidence: 94%

Types of Low Frequency Instabilities in Rotating Detonation Combustors

Anand

Gutmark

2018

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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“…The detonation wave/fuel plenum interaction and the potential coupling between the two were further examined by Fotia et al 7 where a two-dimensional test-section was used in a single-pass operation configuration.…”

Section: Andmentioning

confidence: 99%

Experimental Study of Performance Scaling in Rotating Detonation Engines Operated on Hydrogen and Gaseous Hydrocarbon Fuel

Fotia¹,

Schauer²,

Hoke³

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Thrust stand testing is conducted on rotating detonation engines of various annular detonation channel widths and the impact of different scaling parameters on the performance of the devices is discussed. A focus is given in this work to identifying the relationship between the appropriate flow variables to facilitate comparison between geometries and the experimentally obtained specific impulses and specific thrusts, as well as an examination of stagnation pressure usage, through corrected thrust. Operation on both hydrogen and gaseous hydrocarbon fuel is presented.A comparison is made between the resulting propulsive performances found for similar rotating detonation engine geomtries.

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“…The formation and stable propagation of RDW are strongly dependent on the injection condition. Local reactant injected from the plenum will be blocked by RDW due to its high pressure behind the leading shock wave [14][15][16]. The reactant intake depends on the local pressure in combustor and the inflow cannot recover until RDW skims over.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Mixing Characteristic for CH4/Air in Rotating Detonation Combustor

Jin

Meng

et al. 2020

Applied Sciences

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The mixing process of fuel and oxidizer is a very critical factor affecting the real operating performance of non-premixed rotating detonation combustor. In this paper, a two-dimensional numerical study is carried out to investigate the flow and mixing characteristics of CH 4 /air in combustor with different injection structures. On this basis, the effect of CH 4 /air mixing on the critical ignition energy for forming detonation is theoretically analyzed in detail. The numerical results indicate that injection strategies of CH 4 and air can obviously affect the flow filed characteristic, pressure loss, mixing uniformity and local equivalence ratio in combustor, which further affect the critical ignition energy for forming detonation. In the study for three different mass flow rates (the mass flow rates of air are 12.01 kg/s,8.58 kg/s and 1.72 kg/s, respectively), when air is radially injected into combustor (fuel/air are injected perpendicular to each other), although the mixing quality of CH 4 and air is improved, the total pressure loss is also increased. In addition, the comparative analysis also shows that the increase of mass flow rate of CH 4 /air can decrease the difference of the critical ignition energy for forming detonation at a constant total equivalence ratio. The ignition energy decreases with the decrease of the total flow rate and then increases gradually.

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Propellant Plenum Dynamics in a Two-dimensional Rotating Detonation Experiment

Cited by 26 publications

References 6 publications

Types of Low Frequency Instabilities in Rotating Detonation Combustors

Types of Low Frequency Instabilities in Rotating Detonation Combustors

Experimental Study of Performance Scaling in Rotating Detonation Engines Operated on Hydrogen and Gaseous Hydrocarbon Fuel

Numerical Investigation of Mixing Characteristic for CH4/Air in Rotating Detonation Combustor

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