Abstract: A booster-compressor assembly for supercharging air into a core engine that powers propellers of a turboprop aircraft engine includes an asymmetric annular booster duct aft of the propellers and disposed about a centerline with at least one symmetric annular rotor section with a row of rotor blades disposed therein. The booster duct has a booster flowpath that includes a core flowpath to a core engine inlet and a bypass flowpath around the core engine inlet and the flowpaths circumscribed about the centerline and not symmetric with respect to each other. A low bypass flow rate means sets the airflow through the bypass flowpath such that a bypass flow rate per unit area through the bypass flowpath is substantially less than a core flow rate per unit area through the core flowpath.

Abstract: An aircraft propeller blade is constructed by forming two shells of composite material laminates and bonding the two shells to a metallic spar with foam filler pieces interposed between the shells at desired locations. The blade is then balanced radially and chordwise.

Abstract: A propulsor blade for an aircraft engine includes an airfoil section formed in the shape of a scimitar. A metallic blade spar is interposed between opposed surfaces of the blade and is bonded to the surfaces to establish structural integrity of the blade. The metallic blade spar includes a root end allowing attachment of the blade to the engine.

Abstract: A propulsor blade for an aircraft engine includes an airfoil section formed in the shape of a scimitar. A metallic blade spar is interposed between opposed surfaces of the blade and is bonded to the surfaces to establish structural integrity of the blade. The metallic blade spar includes a root end allowing attachment of the blade to the engine.