Reduced reaction mechanisms for numerical calculations in combustion of hydrocarbon fuels

Kundu, K.P.; Penko, Paul F.; Yang, Shu

doi:10.2514/6.1998-803

Cited by 29 publications

(15 citation statements)

References 2 publications

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“…8 Jachimowski's mechanism contains 14 species, 33 reactions, includes nitrogen chemistry, and was speci cally developed for applicationto high-speedcombustionmodeling. The Jet-A reaction mechanism used in this study is a subset of the full reaction mechanism from Kundu et al 9 The reaction mechanism consists of 17 species and 14 reactions and was chosen because it has been validatedby Chang 10 and Lewis and Chang. 11 The ambient air composition is assumed to be 78% nitrogen, 21% oxygen, and 1% argon by volume.…”

Section: Solution Methodologymentioning

confidence: 99%

“…The Jet-A fuel reaction mechanism is modeled using a reduced reaction mechanism developed by Kundu et al, 9 where the Jet-A fuel is modeled as C 12 H 23 with a density of ½ f D 855 kg/m 3 . The reduced mechanism consists of 17 species and 14 reactions and was chosen because it has been validated for scramjet applications by Chang 10 and Lewis and Chang 11 and shown to have good agreement with the full mechanism for both ignition times and pressure rise for a number of different equivalence ratios.…”

Section: Application: Hydrocarbon Missile Scramjet Enginementioning

confidence: 99%

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Quasi-One-Dimensional High-Speed Engine Model with Finite-Rate Chemistry

O'Brien

Starkey

Lewis

2001

Journal of Propulsion and Power

112

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The quasi-one-dimensional equations of uid motion are coupled with the equations for nite-rate chemistry to model high-speed engine ow elds. The model was developed for rapid vehicle design and optimization, where a wide range of engine inlet conditions may be encountered. Incorporating the timescales of fuel mixing and ignition are crucial for accurate prediction of combustor performance, especially for nonhydrogen fuels and off-design conditions (where equilibrium assumptions are invalid). The effects of area change, friction, mass injection, fuel mixing, and heat transfer to the combustor walls are included. The resulting model is compared to experimental results for hydrogen-fueled scramjet engines to demonstrate the ability to predict wall pressure pro les and fuel ignition point. Application to a rocket-based combined-cycle engine and a hydrocarbon scramjet missile engine are discussed. The model presented predicts peak pressure and fuel ignition accurately, as well as ow eld pressures in regions where boundary-layer separation is not present. Nomenclaturehydraulic diameter, m f st = stoichiometric fuel/air ratio g = gravitational acceleration, m/s 2 h = enthalpy per unit mass, J/kg I sp = speci c impulse, s L = length, m M = Mach number M W = molecular weight, kg/kmol M W = mixture molecular weight, kg/kmol P m = mass ow rate, kg/s P w = wetted perimeter, m Pr = Prandtl number p = pressure, N/m 2 P Q = heat-transfer rate, J/s R u = universal gas constant, J/(kmol-K) T = temperature, K; thrust, N U = velocity, m/s V = volume, m 3 X = mole fraction x = axial coordinate, m N x = nondimensional axial coordinate Y = mass fraction°= ratio of speci c heats 1x = control volume increment of x " = ratio of gas injection velocity to freestream velocitý = ef ciency ½ = density, kg/m 3 . Associate Fellow AIAA. Á = equivalence ratio P ! = molar production rate, kmol/(s-m 3 ) Subscripts added = species added for mass/fuel injection aw = adiabatic wall comb = combustor e = end eff = effective f = total fuel available i = i th species inj = injection mix = mixing o = total or stagnation conditions r = available for reaction s = start st = stoichiometric conditions w = wall x; 1x = control volume descriptors 1 = freestream conditions Superscripts 00 = per unit area 000 = per unit volume ¤ = evaluated at the reference temperature

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Section: Solution Methodologymentioning

confidence: 99%

Section: Application: Hydrocarbon Missile Scramjet Enginementioning

confidence: 99%

Quasi-One-Dimensional High-Speed Engine Model with Finite-Rate Chemistry

O'Brien

Starkey

Lewis

2001

Journal of Propulsion and Power

112

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“…A reduced reaction mechanism of 16 species with 23 reaction steps (derived by Kundu et al [38]) is employed for kerosene reactions. Second-order upwind of spatial discretization is employed in all cases.…”

Section: Dual-radial Swirler (Original)mentioning

confidence: 99%

Predicting Lean Blowout Limit of Combustors Based on Semi-Empirical Correlation and Simulation

Zhao

2016

Journal of Propulsion and Power

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A method named characteristic curve of flame volume is achieved for lean blowout predictions on the basis of the improved Lefebvre's model and simulated reacting flows. Three main issues are presented: 1) Based on the results from combustion visualization experiments, Lefebvre's model is improved regarding its universality for combustor configurations. The flame volume near lean blowout V flame;LBO obtained from simulated reacting flow is introduced into the model. 2) Characteristic curve of flame volume is a functional curve of flame volume V flame and fuel/air ratio q in a certain combustor and is presented as an "S" pattern, with q ranging from stable operation to nearly engine-off conditions. The region where the fuel/air ratio ranges from 3 to 10 in characteristic curve of flame volume is the unstable combustion region, and nearly all of the lean blowout points fall in this region. 3) According to the relationship between characteristic curve of flame volume expressed as q fV flame and the improved Lefebvre's model expressed as q LBO f m V flame;LBO , a method named characteristic curve of flame volume is proposed for lean blowout predictions. By the comparison with experimental data on 26 combustors, the lean blowout fuel/air ratios obtained by the characteristic curve of flame volume method fit well with that obtained by experiments, having maximum and average errors of 24.2 and 7.0% between predictions and measurements.

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“…The gas phase is described using the Eulerian formulation, while the liquid fuel droplets are tracked by the Lagrangian formulation. The 16-species 23-step kerosene (C 12 H 23 ) reaction developed by Kundu et al [26] is used in the study.…”

mentioning

confidence: 99%

Modeling of Spray Combustion with a Steady Laminar Flamelet Model in an Aeroengine Combustion Chamber Based on OpenFOAM

Xiao

Wang

Lai

et al. 2018

International Journal of Aerospace Engineering

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The development of high-performance aeroengine combustion chambers strongly depends on the accuracy and reliability of efficient numerical models. In the present work, a reacting solver with a steady laminar flamelet model and spray model has been developed in OpenFOAM and the solver details are presented. The solver is firstly validated by Sandia/ETH-Zurich flames. Furthermore, it is used to simulate nonpremixed kerosene/air spray combustion in an aeroengine combustion chamber with the RANS method. A comparison with available experimental data shows good agreement and validates the capability of the new developed solver in OpenFOAM.

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Reduced reaction mechanisms for numerical calculations in combustion of hydrocarbon fuels

Cited by 29 publications

References 2 publications

Quasi-One-Dimensional High-Speed Engine Model with Finite-Rate Chemistry

Quasi-One-Dimensional High-Speed Engine Model with Finite-Rate Chemistry

Predicting Lean Blowout Limit of Combustors Based on Semi-Empirical Correlation and Simulation

Modeling of Spray Combustion with a Steady Laminar Flamelet Model in an Aeroengine Combustion Chamber Based on OpenFOAM

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