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Computing supersonic non-premixed turbulent combustion by an SMLD flamelet progress variable model.

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Title: Computing supersonic non-premixed turbulent combustion by an SMLD flamelet progress variable model.
Authors: Coclite, A.1,2 alessandro.coclite@poliba.it, Cutrone, L.2,3 l.cutrone@cira.it, Gurtner, M.4 gurtner@lfa.mw.tum.de, De Palma, P.1,2 pietro.depalma@poliba.it, Haidn, O.J.4 haidn@lfa.mw.tum.de, Pascazio, G.1,2 giuseppe.pascazio@poliba.it
Source: International Journal of Hydrogen Energy. Jan2016, Vol. 41 Issue 1, p632-646. 15p.
Subjects: Probability density function, Scramjet engines, Gas mixtures, Chemical stability, Parameter estimation
Abstract: This paper presents a statistically more likely distribution (SMLD) approach for the evaluation of the presumed probability density function (PDF) in flamelet progress variable (FPV) models for non-premixed supersonic combustion. The numerical simulation of the NASA Langley Research Center supersonic H 2 –Air combustion chamber is performed using two approaches: the first one is a standard FPV model, built presuming the functional shape of the PDFs of the mixture fraction, Z , and of the progress parameter, Λ ; the second approach employs the SMLD technique to presume the joint PDF of Z and Λ . The standard and FPV-SMLD models have been developed using the low Mach number assumption. In both cases, the temperature is evaluated by solving the total-energy conservation equation, providing a more suitable approach for the simulation of supersonic combustion. By comparison with experimental data, the proposed SMLD model is shown to provide a clear improvement with respect to the standard FPV model, especially in the auto-ignition and stabilization regions of the flame. [ABSTRACT FROM AUTHOR]
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Database: Engineering Source
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Abstract:This paper presents a statistically more likely distribution (SMLD) approach for the evaluation of the presumed probability density function (PDF) in flamelet progress variable (FPV) models for non-premixed supersonic combustion. The numerical simulation of the NASA Langley Research Center supersonic H 2 –Air combustion chamber is performed using two approaches: the first one is a standard FPV model, built presuming the functional shape of the PDFs of the mixture fraction, Z , and of the progress parameter, Λ ; the second approach employs the SMLD technique to presume the joint PDF of Z and Λ . The standard and FPV-SMLD models have been developed using the low Mach number assumption. In both cases, the temperature is evaluated by solving the total-energy conservation equation, providing a more suitable approach for the simulation of supersonic combustion. By comparison with experimental data, the proposed SMLD model is shown to provide a clear improvement with respect to the standard FPV model, especially in the auto-ignition and stabilization regions of the flame. [ABSTRACT FROM AUTHOR]
ISSN:03603199
DOI:10.1016/j.ijhydene.2015.10.086