Enhancing Open National Combustion Code and Application of Energy Efficient Engine Combustor

Radiation heat transfer in a gas slab with properties characteristics of a jet engine combustor

“…Independently of the RTE solver, accurately accounting for the spectral behavior of the participating species entails a considerably increase on the computational time. Although Miki et al [1,2] made use of massive parallel computation of Pleiades at NASA Advanced Supercomputing facilities, solving the radiation heat transfer with the line-by-line method is prohibitive, and even accurate spectral models such as the cumulative wavenumber [16], absorption distribution function (ADF) [17,18], spectral-line moment-based [19], spectral-line-weighted-sum-of-gray gases [20][21][22][23], full-spectrum k-distribution [24,25], and variations of these last two models [26][27][28][29][30], would be excessively computer time consuming.…”

“…Regarding commercial aviation, there is a great interest in improving their fuel consumption efficiency and durability, which is desirable for economic reasons as well as for reduction of environmental pollution. Therefore, a series of experimental and numerical studies about jet engines have been conducted during the past twenty years [1][2][3][4][5][6][7][8][9][10]. One major issue is the formation of hot streaks [1,2], which are high-temperature spots that occur on the turbine blade surfaces and have considerable impact on the engine lifetime.…”

“…Therefore, a series of experimental and numerical studies about jet engines have been conducted during the past twenty years [1][2][3][4][5][6][7][8][9][10]. One major issue is the formation of hot streaks [1,2], which are high-temperature spots that occur on the turbine blade surfaces and have considerable impact on the engine lifetime. Another important issue is combustion dynamics, which is close related to fuel consumption and hot streaks formation.…”

“…An important effort to achieve highly-fidelity comprehensive coupled unsteady simulations of combustor-turbine is being accomplished in NASA John. H. Glenn Research Center (GRC), as presented by Miki et al [1,2]. The group is using the publicly available version of the NASA National Combustion Code (NCC) [11], called OpenNCC.…”

“…It is a state-of-the-art code which comprises finite rate chemistry with turbulence-chemistry interaction models, a probability density function transport model, a eddy-breakup model, a linear-eddy model, and a spray Lagrangian liquid phase model. The simulations performed in GRC by Miki and coworkers [1,2] rigorously consider spray-fueled combustion and turbulence inside a realistic combustor geometry, the Energy Efficient Engine (EEE) combustor. However, they do not yet account for radiation heat transfer.…”