A Pressure-Based Algorithm for Gaseous Hydrogen/Liquid Oxygen Jet Flame at Supercritical Pressure

Computational tools of turbulent combustion have practical applications for various fields including liquid rocket engines, but some numerical issues are still presented for solving supercritical combustion. In the present study, several of these numerical issues are studied and discussed. Turbulent...

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Bibliographic Details
Published inNumerical heat transfer. Part A, Applications Vol. 67; no. 5; pp. 547 - 570
Main Authors Park, Tae Seon, Kim, Seong-Ku
Format Journal Article
LanguageEnglish
Published Philadelphia Taylor & Francis Group 04.03.2015
Taylor & Francis Ltd
Subjects
Algorithms
Atmospheric pressure
Combustion
Computer programs
Cryogenic effects
Heat transfer
Liquid oxygen
Mathematical analysis
Mathematical models
Numerical analysis
Supercritical pressures
Temperature distribution
Turbulent flow
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Summary:Computational tools of turbulent combustion have practical applications for various fields including liquid rocket engines, but some numerical issues are still presented for solving supercritical combustion. In the present study, several of these numerical issues are studied and discussed. Turbulent flow and thermal fields of gaseous hydrogen/cryogenic liquid oxygen flame at supercritical pressure are simulated by a turbulence model. To realize real-fluid combustions, the modified Soave-Redlich-Kwong (SRK) equations of state (EOS) are implemented into the flamelet model with a look-up table as functions of mean and variance of mixture fraction, scalar dissipation rate, enthalpy, and pressure. For supercritical combustion flows, modified forms of the pressure implicit with splitting of operator (PISO) algorithm for solving the pressure-velocity linked equation are introduced. From a comparison of instantaneous temperature distributions for gaseous hydrogen/cryogenic liquid oxygen flame at supercritical pressure, the capability of each method based on the different solution sequence is examined and the effective sequence is explored. The results show that the updated mixture fraction reflected in the pressure correction loop is a critical factor for numerical stability. Also, the relative performance of six convection schemes for supercritical combustion is discussed.
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ISSN:1040-7782
1521-0634
DOI:10.1080/10407782.2014.937267