Modeling of Fuel Film Cooling on Chamber Hot Wall
Technical paper, Jun-Jul 2014
AIR FORCE RESEARCH LAB EDWARDS AFB CA ROCKET PROPULSION DIV
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A steady Reynolds-averaged Navier-Stokes model with multiple species, conjugate heat transfer and equilibrium chemistry is constructed to simulate hydrocarbon fuel film cooling of the hot-gas side of liquid rocket engine chamber walls. The predictive performance of the model is studied by comparison to experimental heat flux data for several flow conditions and film cooling mass flow rates. Physics and chemistry aspects are identified that are either not modeled in sufficient detail in the current model or the representation of which otherwise involves uncertainty. The sensitivity of the wall heat flux to these factors is evaluated by perturbing the corresponding parameters and conditions in the model. A key finding is that, under the conditions of the experiments used for comparison, radiative heat flux is comparable to convective heat flux upstream of the injection slot. The sensitivity studies show that the other major factors potentially affecting the heat flux are soot formation accompanied by the deposit of a thermal barrier coating of carbon on the wall, and the magnitude of turbulent mass diffusivity in supercritical high-density ratio shear layers.
- Liquid Propellant Rocket Engines