Finite-rate chemistry effects in a Mach 2 reacting flow

Cheng, T. S.; Wehrmeyer, Joseph A.; Pitz, Robert W.; Jarrett, O.; Northam, G. B.

doi:10.2514/6.1991-2320

Cited by 18 publications

(16 citation statements)

References 16 publications

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“…Simultaneous measurement of temperature and species concentration in high speed reacting flow has made the Cheng et al [22,23] experiment very special in supersonic reacting code validation and many authors [18,[24][25][26][27][28][29][30] has taken this experiment a validation case for their numerical studies. In the experiment of Cheng et al [22,23], a pure hydrogen jet is injected at sonic speed into a vitiated supersonic (M a = 2) coflow.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Simulation of Hydrogen Air Supersonic Coaxial Jet

Dharavath

Manna

Chakraborty

2016

J. Inst. Eng. India Ser. C

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In the present study, the turbulent structure of coaxial supersonic H 2 -air jet is explored numerically by solving three dimensional RANS equations along with two equation k-e turbulence model. Grid independence of the solution is demonstrated by estimating the error distribution using Grid Convergence Index. Distributions of flow parameters in different planes are analyzed to explain the mixing and combustion characteristics of high speed coaxial jets. The flow field is seen mostly diffusive in nature and hydrogen diffusion is confined to core region of the jet. Both single step laminar finite rate chemistry and turbulent reacting calculation employing EDM combustion model are performed to find the effect of turbulencechemistry interaction in the flow field. Laminar reaction predicts higher H 2 mol fraction compared to turbulent reaction because of lower reaction rate caused by turbulence chemistry interaction. Profiles of major species and temperature match well with experimental data at different axial locations; although, the computed profiles show a narrower shape in the far field region. These results demonstrate that standard two equation class turbulence model with single step kinetics based turbulence chemistry interaction can describe H 2 -air reaction adequately in high speed flows.

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Section: Introductionmentioning

confidence: 99%

“…Supersonic combustion with hydrogen fuel is studied extensively both experimentally [3][4][5][6] and numerically [7][8][9][10][11][12] in the literature. These studies mostly measure and compare the wall properties (surface pressure and heat flux) and exit profiles for various flow parameters.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Hydrogen Air Supersonic Coaxial Jet

Dharavath

Manna

Chakraborty

2016

J. Inst. Eng. India Ser. C

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“…3, with three different grids. The surface pressure was non-dimensionalised by P nozzle = 0.917´10 5 Pa. But for the small region near the entry, the bottom wall surface pressure remains constant.…”

Section: Simulation Of the Mixing Casementioning

confidence: 99%

“…Selected methods, that have been used to enhance the mixing process in the Scramjet engines, are summarised and reported by Seiner 3 , et al With the advent of powerful computers, robust numerical algorithm, CFD is complementing difficult to perform experiment and playing a very major role in the development of scramjet combustor through analysis of various thermochemical parameters obtained from the numerical simulation. Supersonic combustion with hydrogen fuel has been studied extensively both experimentally [4][5][6][7] and numerically [8][9][10][11][12][13] in the literature. Despite many years of research, large number of issues related to description of combustion in supersonic turbulent reactive flows remains unanswered.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Supersonic Combustion with Parallel Injection of Hydrogen Fuel

Murty¹,

Chakraborty²,

Mishal³

2010

DSJ

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Thermochemical exploration of mixing and combustion of parallel hydrogen injection into supersonic vitiated air stream in a divergent duct is presented. Three-dimensional Navier Stokes equations along with twoequation turbulence models and Eddy dissipation concept (EDC)-based combustion models are solved using commercial CFD software. Chemical reaction for H 2 -air system is modelled by two different simple chemical kinetic schemes namely; infinitely fast rate kinetics as well as the single-step finite rate kinetics. Grid convergence of the solution is demonstrated and a grid convergence index-based error estimate has been provided. Insight into the mixing and combustion of high-speed turbulent reacting flow is obtained through the analysis of various thermochemical variables. Very good comparisons are obtained for the exit profiles for various fluid dynamical and chemical variables for the mixing case. For reacting case, the comparison between the experimental and the numerical values are reasonable. Parametric studies were carried out to study the effect of different turbulence models and turbulent Schmidt numbers. It is seen that Wilcox k-w turbulence model performed better than the other two-equation turbulence models in its class. Strong dependence of flow behaviour on turbulent Schmidt number was observed. The results indicate that simple chemical kinetics is adequate to describe the H 2 -air reaction in the scramjet combustor.

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“…For this situation, signal averaging for 20 sec was required to obtain a reasonable S/N. The use of a high power (200mJ /pulse), UV (248 nm) excimer laser to gain a v 4 advantage in Raman cross-section has been employed to perform diagnostics on a Mach 2 supersonic combustor [5]. The atmospheric densities provided by this combustor, coupled with the opportunity to use fast gathering optics ("'f/l) to focus light from a point in the combustor to the slit of a polychromator, allowed single shot measurements of the major species densities (N2, 02, H2 and H20) to be made.…”

Section: Spontaneous Raman Scatteringmentioning

confidence: 99%

Absorption, Scattering, and Fluorescence Techniques for Hypersonic Flow Measurements

Exton

1993

New Trends in Instrumentation for Hypersonic Research

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ABSTRACT. This paper presents an overview of the primary nonintrusive diagnostic techniques being developed by the NASA Langley Research Center to address the validation needs of Computational Fluid Dynamic (CFD) codes. The techniques include absorption in the UV and IR, Laser Induced Fluorescence, and a number of scattering techniques including Rayleigh, spontaneous Raman, and several coherent Raman spectroscopies. Most of the techniques are highly specialized, require complex data interpretation, and can satisfy only a few of the CFD needs. For these reasons, the evolving trend in flowfield diagnostics appears to favor a mode in which the diagnostic researcher, the experimental aerodynamicist, and the CFD community jointly define experiments based on the aeronautical requirements and on available diagnostic techniques.

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Finite-rate chemistry effects in a Mach 2 reacting flow

Cited by 18 publications

References 16 publications

Numerical Simulation of Hydrogen Air Supersonic Coaxial Jet

Numerical Simulation of Hydrogen Air Supersonic Coaxial Jet

Numerical Simulation of Supersonic Combustion with Parallel Injection of Hydrogen Fuel

Absorption, Scattering, and Fluorescence Techniques for Hypersonic Flow Measurements

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