Additive manufacturing process grown integrated torsional damper mechanism in gas turbine engine blade

Additive manufacturing process grown integrated torsional damper mechanism in gas turbine engine blade

A blade is provided for a gas turbine engine. The blade includes an airfoil portion with at least one internal cavity and a damper located within the internal cavity. The damper includes a cantilever spring arm. A fan blade is provided for a gas turbine engine. The fan blade includes an airfoil port...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: Cabrila, Pauline, Twelves, Jr., Wendell V, Propheter-Hinckley, Tracy A
Format: Patent
Sprache:eng
Schlagworte:
BLASTING
CASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MAKING METALLIC POWDER
MANUFACTURE OF ARTICLES FROM METALLIC POWDER
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
NON-POSITIVE DISPLACEMENT PUMPS
PERFORMING OPERATIONS
POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS
POWDER METALLURGY
PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
STEAM ENGINES
TRANSPORTING
WEAPONS
WORKING METALLIC POWDER
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Beschreibung
Zusammenfassung:A blade is provided for a gas turbine engine. The blade includes an airfoil portion with at least one internal cavity and a damper located within the internal cavity. The damper includes a cantilever spring arm. A fan blade is provided for a gas turbine engine. The fan blade includes an airfoil portion with at least one internal cavity; and a damper located within the internal cavity. The damper includes a cantilever spring arm that terminates with a rub surface pad adjacent to a friction bridge between a concave pressure side and a convex suction side of the airfoil portion. A method is also provided for damping a blade of a gas turbine engine. The method includes deflecting a cantilever spring arm to contact a rub surface pad with a friction bridge between a concave pressure side and a convex suction side of an airfoil portion of the blade.