Detonation Initiation of Hydrocarbon-Air Mixtures in a Pulsed Detonation Engine

Schauer, Frederick; Miser, C. L.; Tucker, Kevin; Bradley, Royce; Hoke, John

doi:10.2514/6.2005-1343

Cited by 37 publications

(20 citation statements)

References 6 publications

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“…Although early numerical studies gave disparate and often contradictory values for performance parameters, 16 there is now substantial agreement, 17,18 between numerical simulations and experimental measurements for selected mixtures. In parallel, researchers have also experimentally investigated the static multicycle performance of single 3,19−22 and multiple 23,24 detonation tubes. Although there is good agreement between some experimental multicycle data 23,25 and single-cycle estimates, 13 numerical simulations 26 also showed that the multicycle performance can be substantially different from the single-cycle performance.…”

Section: A Vmentioning

confidence: 99%

Model for the Performance of Airbreathing Pulse-Detonation Engines

Wintenberger

Shepherd

2006

Journal of Propulsion and Power

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A simplified flowpath analysis of a single-tube airbreathing pulse detonation engine is described. The configuration consists of a steady supersonic inlet, a large plenum, a valve, and a straight detonation tube (no exit nozzle). The interaction of the filling process with the detonation is studied, and it is shown how the flow in the plenum is coupled with the flow in the detonation tube. This coupling results in total pressure losses and pressure oscillations in the plenum caused by the unsteadiness of the flow. Moreover, the filling process generates a moving flow into which the detonation has to initiate and propagate. An analytical model is developed for predicting the flow and estimating performance based on an open-system control volume analysis and gasdynamics. The existing single-cycle impulse model is extended to include the effect of filling velocity on detonation tube impulse. Based on this, the engine thrust is found to be the sum of the contributions of detonation tube impulse, momentum, and pressure terms. Performance calculations for pulse detonation engines operating with stoichiometric hydrogen-air and JP10-air are presented and compared to the performance of the ideal ramjet over a range of Mach numbers. Nomenclature

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Section: A Vmentioning

confidence: 99%

Model for the Performance of Airbreathing Pulse-Detonation Engines

Wintenberger

Shepherd

2006

Journal of Propulsion and Power

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“…As with the aforementioned studies on the droplet size effect, in order to investigate the initial droplet concentration effect, JP-10 d and average c JP-10 v are also shown below Figure 7, and similar values of JP-10 vapour molar fractions for all cases were also obtained. As is shown in Figure 7, most of the velocities reach up to above 1600 m/s, and the velocity in the stoichiometric JP-10/air mixture is almost equal to, but still slightly lower than, the CJ velocity presented by Schauer et al [31]. .…”

Section: Droplet Concentration Effect On Detonation Velocitymentioning

confidence: 58%

“…The simulation results of various initial JP-10 concentrations with a homogeneous droplet diameter of 50 μm were compared with previous experimental and numerical results [31][32][33]. As indicated in Figure 7, the detonation velocity reaches the maximum value at a stoichiometric JP-10/air (90 g/m 3 ) mixture.…”

Section: Droplet Concentration Effect On Detonation Velocitymentioning

confidence: 90%

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Numerical Simulations of the Effects of Droplet Size and Concentration on Vapour-Droplet JP-10/Air Detonations

Liu¹,

Zhou²

2018

Cent. Eur. J. Energ. Mater.

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Two-dimensional simulations were conducted for JP-10 mono-dispersed vapour-droplet detonation in air, based on the detonation mechanism for clouds and validation of the extending critical droplet size limits in previous tests. In the simulations, the discrete phase model combined with the droplet evaporation and droplet breakup models was used. Utilizing a wide range of mono-dispersed droplet sizes and initial droplet concentrations, all cases of JP-10 droplets with a certain amount of pre-vaporized fuel can successfully achieve the deflagration to detonation transition. Detonation velocities at the equivalent concentration with droplet diameters no larger than 50 μm are in good agreement with the theoretical detonation velocities. The effects of droplet size and initial droplet concentration on the detonation behaviour were also investigated. Detonation velocities attained with droplet diameters below 50 μm appear to decrease very slightly with droplet size, but are almost equal to the velocity in gases. When the droplet diameter is above 50 μm, there is a decrease in simulated detonation velocity compared with fine droplets, and no secondary pressure peak was observed. For fuel-rich combustion, detonation velocities decrease rapidly with an increase in initial droplet concentration, and post-wave pressure fluctuation was obviously irregular, caused by the secondary local explosion of the droplets.

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“…Подробные исследования инициирования и поддержания детонации в PDE, работающем на угле-водородном топливе, выполнены в работах [57][58][59]. Создание самоподдерживающейся детонационной волны требует сокращения дистанции, на которой происходит переход от медленного горения к детона-ции (Deflagration to Detonation Transition, DDT).…”

Section: простейший детонационный двигатель -Pdeunclassified