Effects of Entry Conditions on Cracked Kerosene-Fueled Supersonic Combustor Performance

Fan, Xuejun; Gong, Yu; Li, Jianguo; Yue, Lianjie; Zhang, Xinyu; Sung, Chih-Jen

doi:10.1080/00102200701386198

Cited by 17 publications

(3 citation statements)

References 9 publications

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“…In this study, the fuel temperature can vary from 300 to 800 K as a result of convective heat transfer. Although a further increase in fuel temperature is possible, it was not attempted here because significant thermal cracking was noted [21] to occur at fuel temperatures higher than 800 K. In addition, the Reynolds number of the fuel flow, defined by the tube inner diameter and fuel local properties, ranged from 3000 to 500,000 in the present investigation, whereas the wall heat flux was in the range of 1-30 W=cm 2 .…”

Section: Experimental Specifications a Experimental Facilitymentioning

confidence: 79%

Heat Transfer of Aviation Kerosene at Supercritical Conditions

Zhong¹,

Fan²,

Gong³

et al. 2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The heat transfer characteristics of China no. 3 kerosene were investigated experimentally and analytically under conditions relevant to a regenerative cooling system for scramjet applications. A test facility developed for the present study can handle kerosene in a temperature range of 300-1000 K, a pressure range of 2.6-5 MPa, and a mass flow rate range of 10-100 g=s. In addition, the test section was uniquely designed such that both the wall temperature and the bulk fuel temperature were measured at the same location along the flowpath. The measured temperature distributions were then used to analytically deduce the local heat transfer characteristics. A 10-component kerosene surrogate was proposed and employed to calculate the fuel thermodynamic and transport properties that were required in the heat transfer analysis. Results revealed drastic changes in the fuel flow properties and heat transfer characteristics when kerosene approached its critical state. Convective heat transfer enhancement was also found as kerosene became supercritical. The heat transfer correlation in the relatively low-fuel-temperature region yielded a similar result to other commonly used jet fuels, such as JP-7 and JP-8, at compressed liquid states. In the high-fuel-temperature region, near and beyond the critical temperature, heat transfer enhancement was observed; hence, the associated correlation showed a more significant Reynolds number dependency.

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Section: Experimental Specifications a Experimental Facilitymentioning

confidence: 79%

Heat Transfer of Aviation Kerosene at Supercritical Conditions

Zhong¹,

Fan²,

Gong³

et al. 2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…Buoyancy is excluded in order to investigate the basic characteristics of convective heat transfer of the kerosene at supercritical pressure. Since the thermal cracking of the China RP-3 aviation kerosene occurs obviously when the temperature is over 850 K [15], the maximum wall temperature is restricted to below 850 K in this study.…”

Section: Boundary Conditionsmentioning

confidence: 99%

Convective heat transfer characteristics of China RP-3 aviation kerosene at supercritical pressure

Huai

Cai

et al. 2011

Applied Thermal Engineering

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a b s t r a c tRegenerative cooling of aviation kerosene plays an important role for thermal protection of scramjet engines. Since the thermophysical properties of kerosene change acutely near the pseudo-critical point, heat convective in kerosene pipe flow is complicated. Here the convective heat transfer characteristics of China RP-3 aviation kerosene at a supercritical pressure are numerically studied using the finite volume method. The RNG k-e two-equation turbulence model with enhanced wall treatment is considered. The heat transfer with different constant wall heat fluxes is analyzed, and a correlation of heat transfer enhancement is obtained. The effect of mass flow rate on the convective heat transfer with a varying wall heat flux condition at the supercritical pressure is also investigated. Because of the special thermophysical properties of the kerosene at supercritical pressure, the Nussult number is only related to the Reynolds number after the heat transfer is enhanced. The simulation results are compared with the empirical formulas in the literature.

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“…The heating system has been used for our previous studies [10,11,13,14] . For the present study, the fuel pressure was in the range of 3.5-4.5 MPa, higher than the critical pressure (~2.4 MPa) of the kerosene and the fuel temperature varied from 700 to 1050 K. The fuel residence time was estimated as approximately 0.5-1.3 s, depending on operation conditions.…”

Section: Introductionmentioning

confidence: 99%

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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Effects of Entry Conditions on Cracked Kerosene-Fueled Supersonic Combustor Performance

Cited by 17 publications

References 9 publications

Heat Transfer of Aviation Kerosene at Supercritical Conditions

Heat Transfer of Aviation Kerosene at Supercritical Conditions

Convective heat transfer characteristics of China RP-3 aviation kerosene at supercritical pressure

Thermal cracking of aviation kerosene for scramjet applications

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