Simulation of a single-element GCH4/GOx rocket combustor using a non-adiabatic flamelet method

An efficient modeling framework for wall heat flux prediction in rocket combustion chambers using non adiabatic flamelets and wall-functions

“…In the formulation of Marracino and Lentini [42], a uniform enthalphy defect is applied throughout the mixture fraction space. This however was observed [43,44] to result in unphysical temperature values, especially near the fuel and oxidizer boundaries. To avoid this issue, we introduce here a new non-adiabatic formulation wherein a functional dependence modulating the enthalpy loss is envisaged.…”

“…The flamelets are solved with the OpenSMOKE++ [49] library developed by the CRECK modeling group and modified in-house in order to deal with flows under rocket-relevant conditions [50]. The employed chemical mechanism is the GRI 3.0 [51] for an oxygen-methane mixture, which although developed for atmospheric pressures has already found application in previous studies of high pressure methane oxy-combustion in rocket-like configurations [52,44,53,54,50]. The chosen thermodynamic conditions (pressure p = 20 bar, oxidizer inlet temperature T Ox = 278 K, fuel inlet temperature T F = 269 K and Z st = 0.2) refer to the experimental configuration which will be simulated in the following sections.…”

“…The injector channels are not included in the computational mesh as also done in the LES simulations by Zips et al [31]: inlets are therefore patched at the faceplate and adiabatic conditions are imposed on the post-tip and the plate walls; a temperature profile extracted from the experiments is applied over all the chamber walls as a boundary condition. All the simulations are performed in the context of a modified version of the open source software package OpenFOAM [70], implementing the models previously described and already employed in previous works [43,44,50,71,53,72]. The pressurebased PIMPLE [73] solution algorithm is used to handle the pressure-velocity coupling.…”

Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines

“…However, results of a new test including the measure of coolant temperature increase in throat region have been made recently available [5,6]. These data have been considered a testbench for code validation by different Dipartimento di Ingegneria Meccanica ed Aerospaziale, "La Sapienza"-Università di Roma, Rome, Italy research groups making use of both commercial and inhouse CFD software [7][8][9][10][11][12][13][14][15]. In this paper, some aspects of modeling are deepened to get more insight on the driving phenomena for the correct prediction of throat heat flux.…”

Delayed Detached Eddy Simulations with Tabulated Chemistry for Thermal Loads Predictions

“…In particular, recent efforts were initiated by the academic community to provide experimental data for gaseous CH 4 ∕O 2 subscale combustion chambers. A first experimental setup involved a capacitively cooled single-injector combustion chamber [7][8][9][10], which was the object of numerous numerical studies first in the Reynolds-averaged Navier-Stokes (RANS) context [11][12][13][14][15] and later on in large-eddy simulation (LES) [16][17][18]. The original chamber was modified to allocate a film cooling slot [19], in order to investigate film cooling efficiency under different ratio of oxidizer to fuel (ROF) and chamber pressures.…”