Development and Testing of a Modular Rotating Detonation Engine

Shank, Jason; King, Paul I.; Karnesky, J.; Schauer, Frederick; Hoke, John

doi:10.2514/6.2012-120

Cited by 77 publications

(37 citation statements)

References 1 publication

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“…The solution procedure for the conservation equations (1)(2)(3)(4)9) in both codes is the FCT-algorithm of Boris and Book 30 which is especially well suited for high-speed flows. The version of the algorithm used is described in detail in NRL/MR/6410--93-7192 31 and will not be repeated here for brevity.…”

Section: Solution Proceduresmentioning

confidence: 99%

“…The numerical studies have focused on an overall description of the flow-field within an RDE combustion chamber 3,6 , although some have focused on more practical aspects, such as numerical work regarding RDE nozzles by Yi et al 25 . The experimental studies have been focused mainly on mapping out operational regimes for different configurations, however, more recent setups may allow for more detailed study 9 . We have developed a similar code for simulating two-dimensional and three-dimensional RDE combustion chambers using the same algorithms that have been applied very successfully for our PDE and general detonation research [12][13][14][15][16][17] .…”

Section: Introductionmentioning

confidence: 99%

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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: Solution Proceduresmentioning

confidence: 99%

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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“…Figure 1 provides a schematic arrangement of the plumbing and instrumentation diagram (P&ID) for the device. We are indebted to the Detonation Engine Research Facility at AFRL for donating a functional predet that creates the desired DDT event [24]. Major elements in the P&ID include two fastresponse solenoid valves (LeeCo models IEPA2411241H and IEPA2 411141H), a mixing and ignition chamber, and a deflagration-to-detonation transition (DDT) tube.…”

Section: Experimental Facilitymentioning

confidence: 99%

Transient response of a liquid injector to a steep-fronted transverse pressure wave

Lim

2017

Shock Waves

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Motivated by the dynamic injection environment posed by unsteady pressure gain combustion processes, an experimental apparatus was developed to visualize the dynamic response of a transparent liquid injector subjected to a single steep-fronted transverse pressure wave. Experiments were conducted at atmospheric pressure with a variety of acrylic injector passage designs using water as the working fluid. High-speed visual observations were made of the injector exit near field, and the extent of backflow and the time to refill the orifice passage were characterized over a range of injection pressures. A companion transient one-dimensional model was developed for interpretation of the results and to elucidate the trends with regard to the strength of the transverse pressure wave. Results from the model were compared with the experimental observations.

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“…The solution procedure for the conservation equations (1)(2)(3)(4)9) is the FCT-algorithm of Boris and Book 29 which is especially well suited for high-speed flows. The version of the algorithm used for the RDE3D code is described in detail in NRL/MR/6410--93-7192 30 and will not be repeated here for brevity.…”

Section: A Rde3dmentioning

confidence: 99%

Modeling Exhaust Effects in Rotating Detonation Engines

Schwer¹,

Kailasanath²

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Rotating detonation engines (RDEs) represent an alternative to the extensively studied pulse detonation engines (PDEs) for obtaining propulsion from the high efficiency detonation cycle. The current work focuses on the effect of adding an exhaust plenum to the RDE simulation. The addition of an exhaust plenum causes only minimal changes in the RDE flow field, most significantly at the exhaust plane. The specific impulse varied by less than 1% between modeling with and without an exhaust plenum, showing that using a mixed boundary condition for the exhaust instead of an exhaust plenum is valid. The exhaust plume for three different RDEs is also described. The highest plume temperatures are found after the circulation zone behind the centerbody, although the temperature profiles vary greatly depending on the RDE size. Finally, the effect of a simple conical nozzle extending from the centerbody on the exhaust is investigated. This nozzle reduces the size of the recirculation zone and reduces the temperature in the plume, however, it has very little effect on the flow field inside the RDE or at the exhaust plane. For the hydrogen/air RDE with 10 atm injection pressure and 1 atm back pressure, the specific impulse varied from 4930 s to 4980 s for all cases examined in this paper. 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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Development and Testing of a Modular Rotating Detonation Engine

Cited by 77 publications

References 1 publication

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

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

Transient response of a liquid injector to a steep-fronted transverse pressure wave

Modeling Exhaust Effects in Rotating Detonation Engines

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