Large-Eddy/Reynolds-Averaged Navier–Stokes Simulations of Reactive Flow in Dual-Mode Scramjet Combustor

Fulton, Jesse; Edwards, Jack R.; Hassan, Hassan A.; McDaniel, James C.; Goyne, Christopher P.; Rockwell, Robert D.; Cutler, Andrew D.; Johansen, Craig T.; Danehy, Paul M.

doi:10.2514/1.b34929

Cited by 66 publications

(30 citation statements)

References 32 publications

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“…10,11 However, the technique presents drawbacks. For example, the conventional setup including three incident laser beams imposes a high level of complexity for a successful experiment.…”

mentioning

confidence: 98%

Direct Coherent Raman Temperature Imaging and Wideband Chemical Detection in a Hydrocarbon Flat Flame

Bohlin

Kliewer

2015

J. Phys. Chem. Lett.

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A single-shot coherent Raman imaging technique has been developed for spatially correlated one-dimensional high-fidelity gas-phase thermometry and multiplex chemical detection in flames. The technique utilizes two-beam phase matching, operating a single ultrashort pump/Stokes excitation pulse (7 fs) and a narrowband picosecond probe pulse (70 ps), interrogating a Raman active window of ∼4200 cm(-1) with ∼0.3 cm(-1) spectral resolution. The measurement geometry is formed intersecting the two beams shaped as laser-sheets and the one-coordinate spatial information is retrieved with a linespread function of <40 μm. The advance provides the possibility for the multiplexed measurement of all combustion relevant major species simultaneously with gaseous temperature monitored over a several millimeter field of view. The current technique is optimized in a premixed hydrocarbon flat-flame. At the flame-front, it is shown that direct imaging renders the temperature profile within ∼1% inaccuracy, whereas typical point-wise raster scanning may have relative systematic deviations up to 15% due to spatial averaging effects.

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“…10,11 However, the technique presents drawbacks. For example, the conventional setup including three incident laser beams imposes a high level of complexity for a successful experiment.…”

mentioning

confidence: 98%

Direct Coherent Raman Temperature Imaging and Wideband Chemical Detection in a Hydrocarbon Flat Flame

Bohlin

Kliewer

2015

J. Phys. Chem. Lett.

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“…From the literature, the most preferred modeling cases are the HyperShot I&II [3][4][5][6][7][8][9][10] and SCHOLAR [11][12][13][14][15][16], due a large degree to their relative complete data on experimental setup and measurements 2 American Institute of Aeronautics and Astronautics for model validation. Simulations based on the experimental cases tested on some other scramjet combustor facilities, such as the DLR scramjet combustor [17,18], the University of Virginia's Supersonic Combustion Facility (SCF) [18][19][20][21] and the CUBRC Combustion Duct [22], are also growing vigorously. To date, promising work on modeling those experimental cases is still under way to validate the physical models and shock/turbulence capturing algorithms for supersonic combustion, as well as to improve the computational efficiency [23][24][25].…”

Section: Introductionmentioning

confidence: 99%

Full-scale Detached Eddy Simulation of kerosene fueled scramjet combustor based on skeletal mechanism

Yao¹,

Wang²,

Lu³

et al. 2015

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

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Large Eddy Simulation (LES) of kerosene fueled scramjet combustor is generally scare in the literature, due mainly to the formidable computational cost arisen by complex kerosene mechanism. In this study, the skeletal reduction of a detailed reaction mechanism (2185 species/8217 steps) of aviation kerosene is conducted using directed relation graph with error propagation and sensitivity analysis (DRGEPSA) method, resulting a skeletal mechanism consisting of 39 species/153 elemental reactions for China Daqing RP-3 aviation kerosene. The comparisons of adiabatic flame temperature, total heat release, ignition delay and laminar flame speed predicted by the skeletal mechanism show an overall good accordance with the original detailed reaction mechanism. Then a three-dimensional Detached Eddy Simulation (DES) modeling based on the skeletal kerosene mechanism is employed for the numerical analysis of a full-scale scramjet combustor, which has been experimentally tested in a long-time direct connect supersonic combustion test platform (abbreviated as DTZ) assembled in Chinese Academy of Sciences (CAS). Pressure and heat flux measurement systems are attached to the combustor assembly to monitor the real-time combustion performance and provide validation data for the numerical modeling. Three cases with fuel equivalence ratios from 0.8, 1.0 to 1.2 and the same crossflow conditions at Mach 2.0 are modeled. The time-averaged static pressure and heat flux are in generally good agreement with the experiment with the peak heat flux slightly underpredicted. The instantaneous and/or time-averaged pressure, momentum, temperature and turbulence fields, which are difficult to be measured, are analyzed to reveal the main flow and combustion physics, especially those related to the flame distribution and holding. The combustion is identified as in ramjet mode for the investigated cases. With the increasing of fuel equivalence ratio, the shock train propagates upstream in the isolator and the interaction between the upstream and downstream combustion assumes different patterns.

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“…At about Z ¼ Z st ¼ 0.0285, the OH reaches a maximum, after which it starts to decrease. It means that, adequate mixing is desirable for high efficiency combustion, but too large mixing rates lead to heat and radical losses, such that chemical reactions are suppressed or even can no longer self-sustaining [32]. The relatively dispersive distribution of OH radical in Fig.…”

Section: Structure Of the Supersonic Turbulent Flamementioning

confidence: 98%

Large eddy simulation of flame structure and combustion mode in a hydrogen fueled supersonic combustor

Huang

Qin

et al. 2015

International Journal of Hydrogen Energy

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Large-Eddy/Reynolds-Averaged Navier–Stokes Simulations of Reactive Flow in Dual-Mode Scramjet Combustor

Cited by 66 publications

References 32 publications

Direct Coherent Raman Temperature Imaging and Wideband Chemical Detection in a Hydrocarbon Flat Flame

Direct Coherent Raman Temperature Imaging and Wideband Chemical Detection in a Hydrocarbon Flat Flame

Full-scale Detached Eddy Simulation of kerosene fueled scramjet combustor based on skeletal mechanism

Large eddy simulation of flame structure and combustion mode in a hydrogen fueled supersonic combustor

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