Rufat Kulakhmetov
Purdue University
The development of future Kerosone/LOX engines will require higher chamber pressures to increase performance and reusability in order to decrease operating costs. However higher chamber pressures result in higher heat fluxes through the walls. This places greater stress on the cooling systems. Fuel film cooling is an effective method to reduce the heat flux, however since the fuel is not combusted, it reduces performance of the engine. Furthermore, an issue with using kerosene as coolant is coking that results from the thermal decomposition of the propellant. This decreases heat transfer and reduces the lifespan of the chamber material. This process has been previously studied in regenerative cooled chambers but the mechanisms for coke formation have not been well established. Additionally, in a fuel filmed cooled chamber the process is much more complicated with coking resulting from interactions with the liquid film and gaseous core flow. Currently the only models that exist for coking have been developed for the chemical and petroleum industries. The conditions inside a rocket combustion chamber however are much more severe and extrapolation of existing models will result in large error. Therefore coking models for rocket conditions are in need of development. For this project, an experimental and computational approach is proposed to understand the coking phenomena at rocket conditions. Experiments will be done to study coking behavior in a heated pipe reactor for the liquid fuel and for combusted gaseous products. SEM and an x-ray elemental detection analysis will be performed to determine the chemical characteristics of the coke layer. The results will be compared with another experiment that will involve coking in a liquid fuel film and gaseous core flow environment. Existing coke models will be modified to match the data at the higher pressure and temperature conditions from the experimental results. The end result would be an experimentally validated coking model that would serve to aid in the design of future reusable liquid booster engines and advance NASA’s Launch Propulsion Systems Technology Roadmap.