Multidisciplinary simulation of a regeneratively cooled thrust chamber of liquid rocket engine: Turbulent combustion and nozzle flow

Effective Modeling of Conjugate Heat Transfer and Hydraulics for the Regenerative Cooling Design of Kerosene Rocket Engines

“…In addition, the nonuniform mixing field formed initially by the peripheral fuel cooling injection is predicted by a simplified mixing model based on integration of a presumed mass flow distribution of individual injector over the whole face plate, which provides the inlet boundary condition of the axisymmetric CFD solver. The present paper presents numerical procedure for regenerative cooling analysis model and its linkage with the CFD solver, whereas more details regarding the turbulent reacting flow simulation can be found in our preceding paper [16].…”

“…[16]). At each node, the channel data needed for the cooling analysis, such as number, spiral angle, height, and width, as well as the wall material and thickness, are specified from the actual design.…”

“…During one time step of the CFD solver, the turbulent reacting flow simulation [16] is carried out with latest updated distribution of wall heat flux as thermal boundary condition along the entire chamber wall. With the newly calculated hot gas …”

“…In order to realistically predict the wall heat flux from the combustion gas, the cooling analysis module is incorporated into the turbulent reacting flow solver in a unified framework as schematically illustrated in Figure 1. With regard to simulation of the turbulent reacting flow field within the nonadiabatic thrust chamber, numerical modeling and comparisons with measured propulsion parameters have already been reported in detail through our recent publication [16] and will not be repeated here. As the other part of the unified methodology, this paper presents numerical modeling issues related to regenerative cooling itself.…”

“…In order to supplement the regenerative cooling, 12% of total fuel mass flow is injected equally through 54 fuel cooling injectors installed near the periphery of the face plate. More details regarding the injection system and its modeling can be found in our preceding paper [16]. The chamber consists of four parts, cylindrical combustion chamber (Section A), nozzle throat (Section B), first divergent nozzle (Section C), and second one (Section D), which were fabricated separately and electron beam welded together.…”