Characteristic Scales in Supersonic Combustion

Li, Xiaopeng; Fan, Xuejun

doi:10.2514/6.2013-3725

Cited by 2 publications

(1 citation statement)

References 21 publications

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“…In the typical flight conditions of scramjets, the flame thickness δ l in the combustor is generally between Kolmogorov scale l k and Taylor scale l λ . δ l is close to l λ at low inlet pressure and temperature, but gradually tends towards l k with the increasing of inlet pressure and temperature [107]. In addition, compared with subsonic flows, the compressibility drives the transfer of kinetic energy from larger to smaller scales at a faster rate (i.e.…”

Section: B Turbulent Combustion Model and Reduced Kerosene Mechanismmentioning

confidence: 95%

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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Section: B Turbulent Combustion Model and Reduced Kerosene Mechanismmentioning

confidence: 95%

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

Self Cite

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New Results from Improved Pressure and Progress Variable Modeling of Turbulent Supersonic Combustion

Ladeinde

Lou

2017

53rd AIAA/SAE/ASEE Joint Propulsion Conference

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Characteristic Scales in Supersonic Combustion

Abstract: The characteristic length scales in supersonic combustion and the related influence factors were calculated and analyzed. In addition, using the hydrogen, ethylene and kerosene as fuels, the operating range of scramjet under the

Cited by 2 publications

References 21 publications

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

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

New Results from Improved Pressure and Progress Variable Modeling of Turbulent Supersonic Combustion

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