Large Eddy Simulation based Studies of Reacting and Non-reacting Transverse Jets in Supersonic Crossflow

Kim, Sin; Donde, Pratik; Raman, Venkat; Lin, Kuo-Cheng; Carter, Campbell

doi:10.2514/6.2012-482

Cited by 14 publications

(7 citation statements)

References 35 publications

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“…In addition, it is an important precursor to the formation of soot particles. Ethylene is in itself a highly reactive agent and can, together with methane (CH 4 ), be considered a surrogate for the endothermically cracked military jet propellant JP-7. , Ethylene can be used as fuel in different types of combustors, such as the subsonic, nonpremixed annular combustor by Bauerheim et al, representing a simplified gas turbine combustor, or the high-speed ramjet discussed by Hitch et al and the supersonic ramjet (scramjet). − …”

Section: Introductionmentioning

confidence: 99%

“…There is a growing interest in using hydrocarbon fuels, ,,− and especially ethylene, − in ramjet- and scramjet combustors, as the main fuel, as one component of a high-energy density multifuel mixture, or simply as a product of JP-type fuel cracking and decomposition. Most supersonic combustors use hydrogen fuel due to its low ignition time, but hydrocarbon fuels have the advantage of high density and the ease of use and maintenance.…”

Section: Introductionmentioning

confidence: 99%

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Small Skeletal Kinetic Reaction Mechanism for Ethylene–Air Combustion

2017

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Ethylene is a fuel considered for high-speed ram- and scramjet combustion applications, mainly because of the short ignition delay time resulting from its high reactivity. Further research and development on these combustion systems would benefit from simulations of large eddy (LES) type, which allow some chemical detail to accurately predict combustion characteristics and pollutant formation. In the present work, a chemical kinetic mechanism suitable for LES is presented, consisting of 66 irreversible reactions between 23 species. The mechanism is extensively validated for combustion characteristics related to ignition and flame propagation over a wide range of pressure, temperature, and equivalence ratios that previously published mechanism of this size have not covered. Agreement with a detailed reference mechanism is good for ignition delay, flame temperature, and laminar burning velocities. In addition, overall concentration profiles of major stable products are in overall good agreement with a reference mechanism. The skeletal mechanism shows an overall good performance in combination with a numerical stability and short computation time, making it highly suitable for combustion LES.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Small Skeletal Kinetic Reaction Mechanism for Ethylene–Air Combustion

2017

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“…those based on HyperShot I&II [3][4][5][6][7][8][9][10] or SCHOLAR cases [11][12][13][14][15][16], with a few based on pure hydrocarbons (e.g. ethylene [42,72], methane [73,74] and acetone [75]), however few are based kerosene [76][77][78][79]. Kerosene is a more economic and practical fuel for scramjets cruising at Mach number 4-8, which is the short-term goal of hypersonic flight in the next few decades.…”

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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“…Apart from this, another important phenomenon contributing towards the mixing enhancement is the shock-shear layer interaction. The shock generated at the ramp (wedge) leading edge undergoes reflection and continuously interacts with the supersonic shear layer leading to the generation of vorticity through the baroclinic torque mechanism [18][19][20][21][22]. Menon & Genin [23] in their study with injection through wedge observed that mixing in nonreacting cases is mainly due to unsteadiness and enhanced level of turbulence in the shear layer.…”

Section: Introductionmentioning

confidence: 99%

Investigation of strut-ramp injector in a Scramjet combustor: Effect of strut geometry, fuel and jet diameter on mixing characteristics

Soni

2017

J Mech Sci Technol

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The strut based injector has been found to be one of the most promising injector designs for supersonic combustor, offering enhanced mixing of fuel and air. The mixing and flow field characteristics of the straight (SS) & tapered strut (TS), with fixed ramp angle and height at freestream Mach number 2 in conjunction with fuel injection at Mach 2.3 have been investigated numerically and reported. In the present investigation, hydrogen (H2) and ethylene (C2H4) are injected in oncoming supersonic flow from the back of the strut, where jet to freestream momentum ratio is maintained at 0.79 and 0.69 for H2 & C2H4, respectively. The predicted wall static pressure and species mole fractions at various downstream locations are compared with the experimental data for TS case with 0.6 mm jet diameter and found to be in good agreement. Further, the effect of jet diameter and strut geometry on the near field mixing in strut ramp configuration is discussed for both the fuel. The numerical results are assessed based on various parameters for the performance evaluation of different strut ramp configurations. The SS configuration for both the injectant is found to be an optimum candidate, also it is observed that for higher jet diameter larger combustor length is required to achieve satisfactory near field mixing.

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Large Eddy Simulation based Studies of Reacting and Non-reacting Transverse Jets in Supersonic Crossflow

Cited by 14 publications

References 35 publications

Small Skeletal Kinetic Reaction Mechanism for Ethylene–Air Combustion

Small Skeletal Kinetic Reaction Mechanism for Ethylene–Air Combustion

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

Investigation of strut-ramp injector in a Scramjet combustor: Effect of strut geometry, fuel and jet diameter on mixing characteristics

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