液体ロケットエンジンの実機スケール燃焼器LESに向けた取り組み

抄録

Efforts to realize the LES of a full-scale combustor for liquid rocket engines are reported. LS-FLOW-HO, which is being developed as a large-scale computation platform in JAXA, has dramatically reduced the computation cost to less than 1/20 compared to conventional in-house solvers, enabling LES of a single-injector combustor or a sub-scale combustor with multiple injectors to be performed in about days to weeks using the JAXA's supercomputer system JSS3. Preliminary results were obtained for the LES of a full-scale combustor with more than 500 injectors, although some issues remain, such as suppression of unphysical pressure oscillations in the early stages of the simulation. Thermoacoustic coupling associated with the acoustic modes specific to the actual combustor geometry is a phenomenon that can only be reproduced by such a large scale and high-fidelity simulation, and it is expected to be a means of predicting combustion stability before conducting tests.