Heat transfer mechanisms of laminar flames of hydrogen + oxygen

Cremers, Mfg Marcel; Remie, MJ Martin; Schreel, Kram Koen; Goey, de Lph Philip

doi:10.1016/j.combustflame.2004.08.004

Cited by 16 publications

(13 citation statements)

References 14 publications

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“…The temperature-dependent heat flux from a reactive hydrogen-oxygen mixture with applied strain rate of a ¼ 6,000 s À1 to the plate is taken as convective boundary condition at x ¼ 0 and is given by Cremers et al [33]. At x ¼ D the convective heat flux is also a function of the local surface temperature TðDÞ, but now the heat transfer coefficient is constant, leading to a convective heat loss of q conv ðDÞ ¼ h½TðDÞÀT amb ] with h ¼ 100 W=m 2 K and T amb ¼ 300 K. The plate is assumed to be gray with varying absorption coefficient k. The refraction index is taken constant at a value of n r ¼ 1 when no reflection is taken into account, and as n r ¼ 1:46 when reflection is taken into account.…”

Section: F G Cremers Et Almentioning

confidence: 99%

Solution of the Integrated Radiative Transfer Equation for Gray and Nongray Media

Cremers

Remie

Schreel

et al. 2006

Numerical Heat Transfer, Part A: Applications

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In this article a spectrally resolved solution of the integrated radiative transfer equation for the discrete transfer method with linear temperature interpolation is presented. Combined with the discrete ordinate method, the radiative heat fluxes are determined for use in the finite-volume energy equation. The spectral dependence of the absorption coefficient is approximated as a series of bands of constant value and scattering is neglected. The method is shown to be computationally efficient when applied to a course mesh typical for conduction problems and at the same time to be accurate for both optically thin and thick media, including semitransparent media.

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Section: F G Cremers Et Almentioning

confidence: 99%

Solution of the Integrated Radiative Transfer Equation for Gray and Nongray Media

Cremers

Remie

Schreel

et al. 2006

Numerical Heat Transfer, Part A: Applications

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“…However, it is well-known, see e.g. [15], that for the relatively fast oxy-fuel flames, the gas at the stagnation plane is not in local chemical equilibrium. Therefore, the term equilibrium TCHR is somewhat misleading.…”

Section: Introductionmentioning

confidence: 98%

“…For flames based on mixtures of a fuel and air TCHR is often neglected and the total heat transfer is approximately equal to the convective heat transfer. However, for relatively hot oxy-fuel flames TCHR cannot be neglected, and is for example being held responsible for an enhancement of the convective heat transfer rate of a factor of 2 for a H 2 -O 2 -flame [15].…”

Section: Introductionmentioning

confidence: 99%

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Thermochemical heat release of laminar stagnation flames of fuel and oxygen

Cremers

Remie

Schreel

et al. 2010

International Journal of Heat and Mass Transfer

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“…The time of the defl agration propagation of the fl ame τ d was calculated by the formula of [9], τ d = r/S l , where S l = (ρ u /ρ b )u l . To determine the laminar rate of combustion u l and the ratio of the densities of the unburnt and burnt gases, the data given in [11,12] were used. An analysis of Fig.…”

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confidence: 99%

Ignition of Hydrogen–Oxygen Mixtures Behind the Incident Shock Wave Front

Павлов

Gerasimov

2016

J Eng Phys Thermophy

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Experimental investigation of the ignition of a stoichiometric hydrogen-oxygen mixture behind an incident shock wave in a shock tube at pressures p = 0.002-0.46 MPa and temperatures T = 500-1000 K is carried out. The existence of three limits of ignition typical of the ignition of hydrogen-oxygen mixtures in a spherical vessel is noted. It is shown that at pressures p ≥ 0.1 MPa the ignition of a hydrogen-oxygen mixture begins at a much lower temperature than the ignition of a hydrogen-air mixture. The measured induction times agree well with theoretical estimates.Introduction. Investigation of the ignition of hydrogen-oxygen mixtures in shock tubes behind the incident shock wave front is of both theoretical and practical interest. In particular, the creation of hypersonic passenger airplanes requires the development of new effi cient engines burning hydrogen fuel [1]. The supersonic character of fl ow of a gaseous mixture behind the incident shock wave front explains the attractiveness of the use of a shock tube for carrying out experiments related to the practical implementation of hydrogen ignition under conditions of a hypersonic fl ight [2]. The majority of research works concerned with the study of the process of ignition of combustible mixtures in shock tubes were carried out behind refl ected shock waves where the gas is at rest relative to the shock tube walls [3]. In a recent work [4], measurement of the limits of ignition and times of induction of hydrogen-air mixtures was made behind incident shock waves, as well as a comparison of the obtained results with the results of experiments conducted behind refl ected shock waves. Studies reporting on experimental works associated with ignition of hydrogen-oxygen mixtures behind refl ected shock waves are very few [5][6][7], whereas the data that would have been obtained behind incident shock waves are lacking completely.The aim of the present work is to determine the ignition limits and induction times in stoichiometric hydrogenoxygen mixtures behind the incident shock wave front and to compare the results obtained with those related to pertinent experiments with hydrogen-air mixtures.Experimental. Experiments on studying the process of ignition of hydrogen-oxygen mixtures were carried out on a shock tube (inner radius r = 28.5 mm) consisting of a high-pressure chamber of length 1 m and a low-pressure chamber of length 4.5 m separated by a diaphragm. The low-pressure chamber is fi lled with a test gas and the high-pressure one, with a propelling gas. When the diaphragm is ruptured, in the low-pressure chamber a shock wave starts to propagate, as well as to compress and heat the mixture being investigated. The test facility is equipped with systems of evacuation, preparation, and bleeding-in of gas mixtures, instrumentation for recording emission and absorption spectra, measuring the shock wave velocity, and recording the pressure profi le. The schematic diagram of the facility and description of the measuring equipment are given in [4].Experiments were carri...

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Heat transfer mechanisms of laminar flames of hydrogen + oxygen

Cited by 16 publications

References 14 publications

Solution of the Integrated Radiative Transfer Equation for Gray and Nongray Media

Solution of the Integrated Radiative Transfer Equation for Gray and Nongray Media

Thermochemical heat release of laminar stagnation flames of fuel and oxygen

Ignition of Hydrogen–Oxygen Mixtures Behind the Incident Shock Wave Front

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