Thermal cracking of Norpar-13 under near-critical and supercritical conditions

Sheu, Jang‐Ping; Zhou, Ning; Krishnan, Anantha; Jones, E. G.; Katta, Viswanath R.

doi:10.2514/6.1998-3758

Cited by 18 publications

(11 citation statements)

References 13 publications

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“…(34) is found in the temperature range of approximately 800-960 K. Table 4 presents results of coefficient A and activation energy E a for the current study and for the thermal cracked decane and dodecane (the two main components for common aviation kerosene) reported by refs. [5] and [8]. It is found that the parameters obtained by kerosene thermal cracking are close to those by decane or dodecane cracking even though kerosene consists of hundreds of hydrocarbon components.…”

Section: The Reaction Ratementioning

confidence: 72%

“…The present result provides a reference of reaction parameters for analytical study and numerical simulation of kerosene thermal cracking at supercritical conditions. [8] Dodecane [8] Decane [5] E (kcal/mol) 67. …”

Section: The Reaction Ratementioning

confidence: 99%

“…Despite of lack in the cracking details, the lumped model reduces the complexity of reactions and has been widely used for engineering problems. Sheu et al [8] developed a three-step lumped model for Norpar-13 cracking based on the experimental data of a heated tube system. They incorporated it into a 2-dimensional computation and the calculated wall temperatures were in good agreements with the measurements.…”

Section: Introductionmentioning

confidence: 99%

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Thermal cracking of aviation kerosene for scramjet applications

Zhong

Fan

Gong

et al. 2009

Sci. China Ser. E-Technol. Sci.

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Thermal cracking of China No.3 aviation kerosene was studied experimentally and analytically under supercritical conditions relevant to regenerative cooling system for Mach-6 scramjet applications. A two-stage heated tube system with cracked products collection/analysis was used and it can achieve a fuel temperature range of 700-1100 K, a pressure range of 3.5-4.5 MPa and a residence time of approximately 0.5-1.3 s. Compositions of the cracked gaseous products and mass flow rate of the kerosene flow at varied temperatures and pressures were obtained experimentally. A one-step lumped model was developed with the cracked mixtures grouped into three categories: unreacted kerosene, gaseous products and residuals including liquid products and carbon deposits. Based on the model, fuel conversion on the mass basis, the reaction rate and the residence time were estimated as functions of temperature. Meanwhile, a sonic nozzle was used for the control of the mass flow rate of the cracked kerosene, and correlation of the mass flow rate gives a good agreement with the measurements.thermal cracking, aviation kerosene, lumped model, scramjet applications

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Section: The Reaction Ratementioning

confidence: 72%

Section: The Reaction Ratementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Thermal cracking of aviation kerosene for scramjet applications

Zhong

Fan

Gong

et al. 2009

Sci. China Ser. E-Technol. Sci.

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“…6,7 Compared with detailed chemical kinetics, the global model is more practical for multidimensional CFD simulations of heat transfer on reacted fuel flow. 8,9 Ward et al 10,11 developed a unique global mechanism named proportional product distributions chemical model (the PPD model). The PPD model was sufficiently accurate when the conservation of the fuel was lower than 20%.…”

Section: Introductionmentioning

confidence: 99%

Simulation of heat transfer of mildly-cracked n-decane in a tube with 3-dimensional equation of state look-up table

Liu

Liang

Pan

2014

11th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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The objective of this paper is to develop a numerical method to simulate mildly cracked fuel flow and heat transfer at supercritical pressures. The thermodynamic and transport properties determined by temperature, pressure, and mass fraction of each component were simplified to the function of temperature, pressure and conversion rate. These properties were reconstructed by a three-dimensional equation of state (EOS) look-up table. The three-dimensional EOS table look-up method was two orders of magnitude faster than SUPERTRAPP database. This method was validated and could improve the efficiency of design for active cooling system of scramjet engine. NomenclatureInner diameter of the tube, m E a = Activation energy, J mol -1 f = Molecular weight kg mol -1 G = Mass flow rate per unit areakg m -2 s -1 H p = Enthalpy, J kg -1 H s = Sensible enthalpy, J kg -1 H f = Formation enthalpy, J kg -1 k A = Arrhenius rate constant M R = Reactant M P = Product M W = Molecular weight, g mol -1 nc = Number of species p = Pressure, Pa q w = Wall heat flux, W m -2 R = Gas constant, J mol -1 K -1 T = Temperature, K y = product mass fraction of an indiviual product species Y = mass fraction Greek λ = Thermal conductivity, W m -1 K -1 ν = Arrhenius rate constant ξ = Conversion of reactant Subscript i = species * Graduate Student, Downloaded by KUNGLIGA TEKNISKA HOGSKOLEN KTH on July 30, 2015 | http://arc.aiaa.org | AIAA Aviation av = Average Dimensionless number Bo * = Buoyancy parameter, Gr * Re 3.425 P r 0.8 Gr * = Grashof number, gD 4 qw υ 2 λT P r = Prandtl number, µcp λ q + = Reduced heat flux, qw GcpT Re = Reynolds number, GD µ

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“…By studying the kerosene in high heat flux and high flow rate conditions theoretically and experimentally, Luo Yu-Shan obtained its heat transfer characteristics under subcritical and supercritical pressure conditions, and established the critical heat flux relational expression under fixed pressure and at fixed inlet temperature, only considering mass flow rate [8] . While conventional fuels such as kerosene and JP-7 are prone to coking, normal paraffin hydrocarbon fuels are used as primary fuels in the thermal protection of the scramjet engine in current research [9][10][11][12] . Studies mainly focus on the pyrolysis, coking at high temperature and the relating heat transfer characteristics.…”

Section: Introductionmentioning

confidence: 99%

Deterioration in heat transfer of endothermal hydrocarbon fuel

et al. 2011

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Numerical studies under supercritical pressure are carried out to study the heat transfer characteristics in a single-root coolant channel of the active regenerative cooling system of the scramjet engine, using actual physical properties of pentane. The relationships between wall temperature and inlet temperature, mass flow rate, wall heat flux, inlet pressure, as well as center stream temperature are obtained. The results suggest that the heat transfer deterioration occurs when the fuel temperature approaches the pseudo-critical temperature, and the wall temperature increases rapidly and heat transfer coefficient decreases sharply. The decrease of wall heat flux, as well as the increase of mass flow rate and inlet pressure makes the starting point of the heat transfer deterioration and the peak point of the wall temperature move backward. The wall temperature increment induced by heat transfer deterioration decreases, which could reduce the severity of the heat transfer deterioration. The relational expression of the heat transfer deterioration critical heat flux derives from the relationship of the mass flow rate and the inlet pressure.

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Thermal cracking of Norpar-13 under near-critical and supercritical conditions

Cited by 18 publications

References 13 publications

Thermal cracking of aviation kerosene for scramjet applications

Thermal cracking of aviation kerosene for scramjet applications

Simulation of heat transfer of mildly-cracked n-decane in a tube with 3-dimensional equation of state look-up table

Deterioration in heat transfer of endothermal hydrocarbon fuel

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