HU55108-5 is a precision-manufactured aerospace engine combustion chamber fuel manifold component, compliant with AS9100D quality standards and FAA/EASA regulations, designed for large commercial turbofan engines. It is a core fuel distribution part in the combustion chamber, uniformly distributing aviation fuel to multiple fuel nozzles, which is critical for ensuring consistent fuel supply to different areas of the combustion chamber, optimizing the uniformity of fuel-air mixing, and maintaining stable, low-emission combustion.

Made from high-strength, fuel-resistant nickel-based superalloy with anti-corrosion treatment, it withstands operating temperatures from -60°C to 320°C and long-term contact with aviation fuel. Weighing 0.72kg with a precision-machined flow distribution structure, it allows for fast cleaning and flow uniformity detection during combustion chamber MRO overhauls. FAA Part 25 certified, it is a key component for combustion chamber operational efficiency.