General Electric Company

Joey L Nelson

Wu-Yang Tseng

Martin C Hemsworth

Sidney B Elston, Iii

Rollin G Giffin, Iii

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.

Asymmetric turboprop booster

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.

Method of making counterrotating aircraft propeller blades

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.

Growing community of inventors

Southgate, KY, United States of America

Joey L Nelson