Robust Cryogenic Compatible Turbo-machinery and Liquid Rocket Engine coatings

ABSTRACT: The goal of this Phase I is to demonstrate the feasibility of a ICME-based approach to the design of thermal barrier coating architectures and processes to guide the design and selection of a newly defined material/coating system, and to demonstrate this systems'ability to survive in an environment representative of a reusable oxygen-rich staged combustion engine turbine via limited, exploratory testing in test environments that mimic key characteristics of the intended operational environment. BENEFIT: The TBC modeling system and LOX-Hydrocarbon compatible TBC systems envisioned in this proposal have obvious commercial potential, especially for designers and manufacturers of reusable LOX-Hydrocarbon rocket engines. The techniques and test protocol/apparatus envisioned for the Phase II activity have clear potential for dual use in the rocket engine, aircraft engine and stationary power generation sectors.