Robust Cryogenic Compatible Turbo-machinery and Liquid Rocket Engine coatings

This hase II effort addresses the extension and refinement of the design system begun in the Phase I activity, further developed (toward turbines) in the current Phase II, for coatings and substrate materials and environments that closely match the intended ORSC LOX/RP-1 thrust chamber environment. This Phase II also envisions the design of a very novel bench-scale test apparatus and protocol that is suitable for TBC screening and modeling system validation specifically targeted to the high heat flux levels experienced by thrust chambers. The proposed apparatus and protocol are intended to provide a direct relationship between the coating design system, the coating system screening tests and in-engine performance, to ensure a high degree of confidence in the coating system, enabling predictable performance of these systems in the engine. Finally, this Phase II effort will demonstrate the use of the coatings design system in the design and manufacture of (2) thrust chambers.