Engine-Level Simulation of Liquid Rocket Combustion Instabilities: Transcritical Combustion Simulations in Single Injector Configurations

摘要: Abstract : Detailed understanding of turbulent combustion in liquid rocket engines (LRE) requires an ability to predict the coupling between transient features, acoustics, vortex/shear layer dynamics and unsteady heat release. Conventional ad hoc models that mimic or match one set conditions but fail another test case cannot be used for reliable predictions. This paper presents a simulation strategy based on Large-Eddy Simulation (LES) uses finite-volume scheme multi-block, structured grids solves full multi-species, compressible LES equations using hybrid central-upwind capture both turbulence shear flow large density gradients. The sensitivity predictions real gas equation state such as Peng-Robinson is addressed this study. main modeling challenges concern simultaneous flame structure, flame-turbulence interactions regions compressibility. current work focuses three single injector configurations these objectives: (a) trans-critical oxygen (LOX) / gaseous hydrogen (GH2) combustion, (b) LOX/methane (c) high-pressure GOX/methane with thermo-acoustic instabilities. Results will reported core length spreading rate, comparison data where appropriate. Finally, problems, more fundamental challenge determine implication subgrid closures dynamics. As preliminary effort, Linear-Eddy sub-grid model (LEM) being applied some cases.