9C1361G01 is a precision-manufactured aerospace engine high-pressure turbine (HPT) shroud segment, compliant with AS9100D quality standards and FAA/EASA regulations, designed for large commercial turbofan engines. It forms the static outer boundary of the HPT flow path, guiding high-temperature, high-pressure exhaust gas to flow through the HPT rotor blades in a designed path, which is critical for reducing aerodynamic loss, maintaining the pressure difference required for energy conversion, and protecting the engine's outer static components from high-temperature gas erosion.

Made from high-strength, heat-resistant and oxidation-resistant nickel-based superalloy, it withstands operating temperatures up to 1470°C and continuous scouring from high-speed exhaust gas. Weighing 0.35kg with a precision-machined inner surface, it allows for fast installation and condition inspection during HPT MRO overhauls. FAA Part 25 certified, it is a key component for HPT operational efficiency.