Experimental Investigation of Shear Coaxial Cryogenic Jet Flames

Candel, Sébastien; Herding, G.; Synder, R.; Scouflaire, Philippe; Rolon, C.; Vingert, Lucien; Habiballah, Mohammed; Grisch, Frédéric; Péalat, M.; Bouchardy, P.; Stepowski, D.; Cessou, Armelle; Colin, P.

doi:10.2514/2.5346

Cited by 107 publications

(59 citation statements)

References 11 publications

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“…Special emphasis is placed on the analysis of the local structure of counter §ow di¨usion §ames using the combustion simulation laboratory COSILAB as this structure provides the basis for the pre-integrated §amelet library applied along with the laminar §amelet combustion model. As application and for validation, the A-60 case tested at the Mascotte test rig V03 operated at ONERA [37,38] is simulated using the commercial CFD solver ANSYS CFX. Here, hydrogen is injected at a supercritical state whereas for oxygen, the pressure is supercritical but the injection temperature is below its critical value.…”

Section: Discussionmentioning

confidence: 99%

“…Special emphasis is placed on calculations at the conditions of the RCM-3 test case, de¦ned at the 2nd International Workshop on Rocket Combustion Modeling [37,38]. This test case is used for the validation of the real gas CFD simulations presented in section 4.…”

Section: Counterflow Diffusion Flames At Supercritical Pressuresmentioning

confidence: 99%

“…As application, the A-60 case tested at the Mascotte test rig V03 operated at ONERA is used [37,38] which also allows for the validation of the obtained results. The experimental setup and the corresponding CFD model are summarized brie §y whereas the results are discussed in detail with respect to the §amelet solutions, the §ame shapes and the comparison with experimental ¦ndings.…”

Section: Applicationmentioning

confidence: 99%

See 2 more Smart Citations

Real gas CFD simulations of hydrogen/oxygen supercritical combustion

Pohl

Jarczyk

Pfitzner

et al. 2013

Progress in Propulsion Physics

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A comprehensive numerical framework has been established to simulate reacting §ows under conditions typically encountered in rocket combustion chambers. The model implemented into the commercial CFD Code ANSYS CFX includes appropriate real gas relations based on the volume-corrected PengRobinson (PR) equation of state (EOS) for the §ow ¦eld and a real gas extension of the laminar §amelet combustion model. The results indicate that the real gas relations have a considerably larger impact on the §ow ¦eld than on the detailed §ame structure. Generally, a realistic §ame shape could be achieved for the real gas approach compared to experimental data from the Mascotte test rig V03 operated at ONERA when the di¨erential di¨usion processes were only considered within the §ame zone.

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Section: Discussionmentioning

confidence: 99%

Section: Counterflow Diffusion Flames At Supercritical Pressuresmentioning

confidence: 99%

Section: Applicationmentioning

confidence: 99%

See 1 more Smart Citation

Real gas CFD simulations of hydrogen/oxygen supercritical combustion

Pohl

Jarczyk

Pfitzner

et al. 2013

Progress in Propulsion Physics

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“…2a has been consistently observed for LOX=H 2 injection [17][18][19][20]. However with a different fuel type such as CH 4 , a lifted flame anchoring in the turbulent mixing layer of evaporated LOX and gaseous fuel is also a possible flame anchoring mechanism (see Fig.…”

mentioning

confidence: 99%

Atomization and Flames in LOX/H2- and LOx/CH4- Spray Combustion

Yang

Cuoco²,

Oschwald³

2007

Journal of Propulsion and Power

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Hydrogen is a widely used rocket fuel and methane is particularly of interest in Europe as a promising substitute for H 2 . Experimental investigation of cryogenic reactive coaxial sprays with oxygen as an oxidizer and hydrogen and methane as fuels is conducted to prove whether concepts from the LOX=H 2 injector design can be transferred to LOX=CH 4 injection. The liquid oxygen has been atomized in shear coaxial atomizers, and the sprays and flames have been investigated by visualization methods such as shadowgraphy and imaging of the flame emission. LOX sprays are characterized for both propellants by the intact core lengths and droplet numbers, and the combustion is analyzed in terms of the flame anchoring mechanism and the flame spreading angle. The results for LOX=H 2 -and LOX=CH 4 -spray combustion are compared, and the influence of the injection conditions of the propellants on atomization and spray flame is discussed. Significant differences of the sprays and flames have been observed for the two propellant combinations at similar injection conditions, as defined by the Weber number and the momentum flux ratio. The flame stabilization process has shown a strong influence on the atomization and flame characteristics.

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“…These two effects combine to suggest that large-scale turbulent mixing becomes the slowest and therefore is the most influential process. Candel et al (1998) and Herding et al (1998) carried out extensive experiments on the jet flame formed from a single coaxial injector at elevated chamber pressure (5-10 arm) over a wide range of mass and momentum ratios. The injection temperature of hydrogen was fixed at 289 K, and that of oxygen was around 100 K. Several important diagnostic techniques were developed.…”

Section: 23 Experimental Study On High-pressure Cryogenic Propellanmentioning

confidence: 99%

Liquid-Propellant Rocket Engine Injector Dynamics and Combustion Processes at Supercritical Conditions

Yang¹

2004

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Experimental Investigation of Shear Coaxial Cryogenic Jet Flames

Cited by 107 publications

References 11 publications

Real gas CFD simulations of hydrogen/oxygen supercritical combustion

Real gas CFD simulations of hydrogen/oxygen supercritical combustion

Atomization and Flames in LOX/H2- and LOx/CH4- Spray Combustion

Liquid-Propellant Rocket Engine Injector Dynamics and Combustion Processes at Supercritical Conditions

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