Nonequilibrium combustion model for fuel-rich gas generators

Foelsche, Robert; Keen, J. M.; Solomon, W. C.; Buckley, P.; Corporan, Edwin

doi:10.2514/3.23796

Cited by 30 publications

(6 citation statements)

References 6 publications

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“…A number of studies compared various aromatic compounds in surrogates and concluded that alkyl-substituted aromatics were the best aromatic components [16,[24][25][26][27][28][29]. Xylenes, n-propylbenzene, n-butyl benzene, and αmethyl naphthalene have all been considered as representatives of the aromatic class, for instance, in Refs.…”

Section: Introductionmentioning

confidence: 99%

A component library framework for deriving kinetic mechanisms for multi-component fuel surrogates: Application for jet fuel surrogates

Narayanaswamy

Pitsch

Pepiot

2016

Combustion and Flame

113

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Surrogate fuels are often used in place of real fuels in computational combustion studies. However, many different choices of hydrocarbons to make up surrogate mixtures have been reported in the literature, particularly for jet fuels. To identify the best choice of surrogate components, the capabilities of different surrogate mixtures in emulating the combustion kinetic behavior of the real fuel must be examined. To allow extensive assessment of the combustion behavior of these surrogate mixtures against detailed experimental measurements for real fuels, accurate and compact kinetic models are most essential. To realize this goal, a flexible and evolutive component library framework is proposed here, which allows mixing and matching between surrogate components to obtain short chemical mechanisms with only the necessary kinetics for the desired surrogate mixtures. The idea is demonstrated using an extensively validated multicomponent reaction mechanism developed in stages [Blanquart et al., Combust. Flame (2009), Narayanaswamy et al., Combust. Flame (2010, 2014, 2015)], thanks to its compact size and modular assembly. To display the applicability of the component library framework, (i) a jet fuel surrogate consisting of n-dodecane, methylcyclohexane, and m-xylene, whose kinetics are described in the multi-component chemical mechanism is defined, (ii) a chemical model for this surrogate mixture is derived from the multi-component chemical mechanism using the component library framework, and (iii) the predictive capabilities of this jet fuel surrogate and the associated chemical model are assessed extensively from low to high temperatures in well studied experimental configurations, such as shock tubes, premixed flames, and flow reactors.

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Section: Introductionmentioning

confidence: 99%

A component library framework for deriving kinetic mechanisms for multi-component fuel surrogates: Application for jet fuel surrogates

Narayanaswamy

Pitsch

Pepiot

2016

Combustion and Flame

113

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“…In order to predict the composition of the combustion gas during fuel-rich combustion of kerosene in the gas generator, the modified perfectly stirred reactor (PSR) model was employed by Foelsche et al 12 The original PSR model is limited for analysis of typical gas generator conditions because the model does not include spatial gradients for the properties. Notably, the temperature distribution caused by the flame kernel and the delay of fuel evaporation are not considered in this model; thus, the two-temperature and droplet evaporation models were coupled to the PSR model.…”

Section: Methods Of Numerical Studymentioning

confidence: 99%

“…In order to reflect this behavior, the two-temperature zone model, which separates the chemical reaction and the reactor temperature, has been used in the PSR model. 12,16 The ''chemical temperature'' comprises the temperature in the high temperature stoichiometric region affected by the O 2 fraction, the reactor temperature at the exit, and the residence time. This temperature must be attained to initiate the high-enthalpy reaction near the injector region.…”

Section: Methods Of Numerical Studymentioning

confidence: 99%

“…14 The governing equations for the mass and energy balance are represented in the PSR as presented below. 12 Mass balance equation…”

Section: Methods Of Numerical Studymentioning

confidence: 99%

“…The fuel properties of B and t l are calculated from empirical correlations. 12 Therefore, the residence time in the PSR model was revised by subtracting the maximum droplet lifetime from the input reactor residence time as follows…”

Section: Methods Of Numerical Studymentioning

confidence: 99%

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Modeling of kerosene combustion under fuel-rich conditions

Song

2017

Advances in Mechanical Engineering

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The turbo-pump and turbine are driven by liquid fuel fed into a gas generator, where the fuel is oxidized with a liquid oxidizing agent. For stable operation of the turbine, the combustion temperature of the gas generator must be maintained below 1000 K. The thermodynamic characteristics of kerosene oxidation in the gas generator must be understood to optimize the design and operation conditions of the liquid-fueled rocket engine system. Herein, the 3-species surrogate mixture model for kerosene was selected, and the detailed Dagaut's kerosene oxidation mechanism consisting of 225 chemical species and 1800 reversible chemical reactions was utilized. The exit gas temperature and product gas composition in the gas generator under fuel-rich conditions were simulated by applying the perfectly stirred reactor model. The perfectly stirred reactor model was used in combination with the liquid spray model for evaporation of the droplets and the two-temperature model for evaluation of the flame temperature separately from the locally averaged reactor temperature. The theoretical prediction of the gas species fraction and soot yield could be improved by applying the tar cracking mechanism, where the reaction characteristics under high temperature were taken into account.

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Prediction of non-equilibrium kinetics of fuel-rich kerosene/LOX combustion in gas generator

Lee

2007

J Mech Sci Technol

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Gas generator is the device to produce high enthalpy gases needed to drive turbo-pump system in liquid rocket engine. And, the combustion temperature in gas generator should be controlled below around 1,000K to avoid any possible thermal damages to turbine blade by using either fuel rich combustion or oxidizer rich combustion. Thus, nonequilibrium chemical reaction dominates in fuel-rich combustion of gas generator. Meanwhile, kerosene is a compounded fuel with various types of hydrocarbon elements and difficult to model the chemical kinetics. This study focuses on the prediction of the non-equilibrium reaction offuel rich kerosene/LOX combustion with detailed kinetics developed by Dagaut using PSR (Perfectly Stirred Reactor) assumption. In Dagaut's surrogate model for kerosene, chemical kinetics of kerosene consists of 1,592 reaction steps with 207 chemical species. Also, droplet evaporation time is taken into account in the PSR calculation by changing the residence time of droplet in the gas generator. Frenklach's soot model was implemented along with detailed kinetics to calculate the gas properties of fuel rich combustion efflux. The results could provide very reliable and accurate numbers in the prediction of combustion gas temperature, species fraction and material properties.

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Nonequilibrium combustion model for fuel-rich gas generators

Cited by 30 publications

References 6 publications

A component library framework for deriving kinetic mechanisms for multi-component fuel surrogates: Application for jet fuel surrogates

A component library framework for deriving kinetic mechanisms for multi-component fuel surrogates: Application for jet fuel surrogates

Modeling of kerosene combustion under fuel-rich conditions

Prediction of non-equilibrium kinetics of fuel-rich kerosene/LOX combustion in gas generator

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