Investigation of Heat Transfer and Coking Characteristics of Hydrocarbon Fuels

Liang, Keming; Yang, B.; Zhang, Zhongli

doi:10.2514/2.5342

Cited by 70 publications

(20 citation statements)

References 2 publications

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“…For similar wall temperatures and flow rates, it is clearly seen that increasing the bulk fluid temperature by use of the preheater increases the overall heat transfer in the test section. This increase in heat transfer for higher bulk temperature fluids has been shown for aviation kerosenes previously, 4 and is attributed to higher Reynolds numbers accompanying higher temperatures. For constant velocity and hydraulic diameter, the increase in Reynolds number between Set 1 and Set 3 is dominated by the ratio of absolute viscosities (µ Set1 /µ Set3 ), leading to large Reynolds number increases for moderate temperature increases.…”

Section: A Heat Transfer Resultssupporting

confidence: 79%

Pharmacological Studies of NOP Receptor Agonists as Novel Analgesics

Ko¹

2008

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)Air Force Research Laboratory (AFMC) AFRL/RZS SPONSOR/MONITOR'S Pollux Drive NUMBER(S)Edwards AFB CA 93524-7048 AFRL-RZ-ED-TP-2008-259 DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution unlimited (PA #08259A). SUPPLEMENTARY NOTESFor presentation at the 44 th AIAA Joint Propulsion Conference, Hartford, CT, 20-23 July 2008. ABSTRACTIn an effort to enable reusable, high-performing liquid rocket engines, a comprehensive experimental and numerical investigation of the thermal performance (thermal stability and heat transfer characteristics) of RP-2 is underway at the Air Force Research Laboratory (AFRL), Edwards AFB, CA. In the current work, the High Heat Flux Facility (HHFF) was used to provide initial RP-2 thermal performance information under conditions simulative of those encountered in the cooling channels of a real engine. RP-2 was thermally stressed while flowing through circular copper tube test sections. Short-duration thermal stressing tests provided heat transfer information which closely followed existing empirical correlations for RP-1. Effects of wall temperature, bulk temperature, and flow rate on heat transfer were observed and were consistent with expected behavior. Longer-duration tests at elevated wall temperatures provided the first steps in elucidating the conditions under which solid carbon deposits form. The test sections were analyzed post-test with optical and scanning electron microscope and carbon deposition burn-off for signs of coke formation. The results from these analyses indicate the presence of solid carbon deposition for high-wall temperature tests exceeding 30 min. in duration, although further testing is required to make more conclusive comparisons. In an effort to enable reusable, high-performing liquid rocket engines, a comprehensive experimental and numerical investigation of the thermal performance (thermal stability and heat transfer characteristics) of RP-2 is underway at the Air Force Research Laboratory (AFRL), Edwards AFB, CA. In the cu...

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Section: A Heat Transfer Resultssupporting

confidence: 79%

Pharmacological Studies of NOP Receptor Agonists as Novel Analgesics

Ko¹

2008

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“…In particular, for the use in cooling systems, the threshold value of coolant-side wall temperatures is limited by coking considerations. For methane the widely quoted value is 970 K, higher than propane (700 K) and kerosene (590 K) [4]. Moreover, the heat transfer performance of methane is higher compared to other hydrocarbon fuels as a result of its high thermal conductivity, speci¦c heat, and low viscosity.…”

Section: Introductionmentioning

confidence: 95%

“…The investigations presented are performed at the newly built institute£s test facility for GCH 4 and GOx, designed for interface pressures up to 50 bar.…”

Section: Test Specimen and Experimental Setupmentioning

confidence: 99%

Injector characterization for a gaseous oxygen-methane single element combustion chamber

Celano

Silvestri

Schlieben

et al. 2016

Progress in Propulsion Physics

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The results from an experimental investigation on an oxygenmethane single-injector combustion chamber are presented. They provide detailed information about the thermal loads at the hot inner walls of the combustion chamber at representative rocket engine conditions and pressures up to 20 bar. The present study aims to contribute to the understanding of the thermal transfer processes and to validate the in-house design tool Thermtest and a base for an attempt to simulate the §ame behavior with large-eddy simulation (LES). Due to the complex §ow phenomena linked to the use of cryogenic propellants, like extreme variation of §ow properties and steep temperature gradients, in combination with intensive chemical reactions, the problem has been partially simpli¦ed by injecting gaseous oxygen (GOx) and gaseous methane (GCH 4 ). external combustion chamber width, m c speci¦c heat capacity, J/(kg·K)' E in total energy entering the control volume, W ' E out total energy leaving the control volume, W

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“…In particular, the deterioration has been outlined with hydrogen, 19 methane, propane and liquefied natural gas. 20,21 However, it was observed in studies which were not carried out to investigate the deterioration phenomenon, rather their purpose was to investigate the cooling capabilities and coking characteristics of the coolant fluid (coking for hydrocarbons). Nevertheless, these experimental works demonstrate the risk of a deteriorated heat transfer in regenerative cooling channel configurations.…”

Section: Introductionmentioning

confidence: 97%

On the Onset of Heat Transfer Deterioration in Supercritical Coolant Flow Channels

Urbano

Nasuti

2012

43rd AIAA Thermophysics Conference

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The deterioration of forced convection heat transfer can affect channel flows of supercritical fluids, and therefore has to be taken in consideration when dealing with regenerative cooling of liquid rocket engines. A threshold value of the ratio between the heat flux and the specific mass flow rate is identified as the main parameter controlling the heat transfer deterioration onset. The threshold parameter depends on the specific thermodynamic conditions of the coolant and in particular on its pressure level. In the present study, a parametric numerical analysis has been carried out on the flow of supercritical methane in heated channels, for an assigned inlet temperature level and varying the inlet pressure. A correlation for the threshold parameter as a function of pressure is then proposed on the basis of the obtained results. Nomenclature A Helmholtz free energy [J/kg] Bo * Jackson Buoyancy parameter: Bo * = Gr * /(Re 3.425 D P r 0.8 ) G specific mass flow rate [kg/s/m 2 ] Gr * Grashof Number based on the heat flux: Gr * = gβq w D 4 /(kν 2 ) N u Nusselt Number: Dh c /k b P r Prandtl Number: µ b c p,b /k b R gas constant [J/kg/K] Re Reynolds Number: ρu b D/µ b a reduced Helmholtz free energy a = A/(RT ) c p specific heat at constant pressure [J/kg/K] D channel cross section diameter [m] F parabolized vector of fluxes in the streamwise direction g sea level gravitational acceleration constant, g = 9.81 m/s 2 G, H vectors of fluxes in the transverse directions h enthalpy [J/kg] h c heat transfer coefficient [conductivity [W/m/K] m mass flow rate [kg/s] P pressure term vector for PNS p pressure [Pa] Q source terms vector q +reduced heat flux, q + = (q w /G)/(c p /β) * PhD Student,

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Investigation of Heat Transfer and Coking Characteristics of Hydrocarbon Fuels

Cited by 70 publications

References 2 publications

Pharmacological Studies of NOP Receptor Agonists as Novel Analgesics

Pharmacological Studies of NOP Receptor Agonists as Novel Analgesics

Injector characterization for a gaseous oxygen-methane single element combustion chamber

On the Onset of Heat Transfer Deterioration in Supercritical Coolant Flow Channels

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