PHYSICS OF LAMINAR PREMIXED CH4 − O2 FLAMES AT CRYOGENIC CONDITIONS - A COMPUTATIONAL STUDY

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dc.contributor.advisorLarsson, Johanen_US
dc.contributor.authorGopal, Abisheken_US
dc.contributor.departmentMechanical Engineeringen_US
dc.contributor.publisherDigital Repository at the University of Marylanden_US
dc.contributor.publisherUniversity of Maryland (College Park, Md.)en_US
dc.date.accessioned2019-10-01T05:40:52Z
dc.date.available2019-10-01T05:40:52Z
dc.date.issued2019en_US
dc.description.abstractWith increased commercial spaceflight activity, methane has found adoption in the next generation of liquid rocket engines (LREs). In a liquid rocket engine with cryogenic propellants, such as methane and oxygen, the propellants are stored in their tanks at low temperatures. As they are injected into the combustion chamber at high pressures, the fluid is close to its thermodynamic critical point where there are drastic changes in fluid properties like density, heat capacity, surface tension, and solubility. The ideal gas law is inapplicable at such extreme conditions, and real gas thermodynamic and transport properties are required to accurately model the combustion physics at supercritical conditions. Much of the previous work applying real gas models in computational simulations of reacting flows have focused on non-premixed flames or cold-flow mixing configurations. In this study, we investigate the effects of real gas property estimation on planar, unstretched, laminar premixed methane-oxygen flames at transcritical conditions. The computational framework used in this study integrates real gas property estimation into the steady-state, freely-propagating flame solver available in the Cantera combustion suite. The Peng-Robinson equation of state provides thermodynamic property closure. High-pressure transport properties are modeled by the Chung and Takahashi correlations, respectively. The effects on laminar flame structure are presented. We find that enhanced real gas reactant densities have a significant impact on flame propagation, lowering flame speeds by a factor of ∼ 5 near the critical region. Real gas caloric properties lower mass burning rates by 10%. The consequence of using low-pressure transport properties with the Peng-Robinson EOS at variable Lewis numbers is discussed.en_US
dc.identifierhttps://doi.org/10.13016/u5lw-oj2f
dc.identifier.urihttp://hdl.handle.net/1903/25148
dc.language.isoenen_US
dc.subject.pqcontrolledMechanical engineeringen_US
dc.subject.pqcontrolledComputational physicsen_US
dc.subject.pqcontrolledAerospace engineeringen_US
dc.subject.pquncontrolledEquation of Stateen_US
dc.subject.pquncontrolledHigh-pressure flamesen_US
dc.subject.pquncontrolledMethane-Oxygen premixed flamesen_US
dc.subject.pquncontrolledPeng-Robinsonen_US
dc.subject.pquncontrolledReal gas flamesen_US
dc.subject.pquncontrolledSupercritical reacting flowsen_US
dc.titlePHYSICS OF LAMINAR PREMIXED CH4 − O2 FLAMES AT CRYOGENIC CONDITIONS - A COMPUTATIONAL STUDYen_US
dc.typeDissertationen_US

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