Methods for the manufacture of gas turbine engine rotors including intra-hub stress relief features

Embodiments of a gas turbine engine rotor (60) including stress relief features are provided, as are embodiments of method (88) for producing a gas turbine engine rotor. In one embodiment, the method includes producing (90) a hub preform (102) in which a plurality of elongated sacrificial cores (94)...

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Bibliographische Detailangaben
Hauptverfasser:	Hann, Brian, Kington, Harry Lester
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING CASTING COMBINED OPERATIONS ENGINE PLANTS IN GENERAL FOUNDRY MOULDING HEATING LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MAKING METALLIC POWDER MANUFACTURE OF ARTICLES FROM METALLIC POWDER MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES OTHER WORKING OF METAL PERFORMING OPERATIONS POWDER METALLURGY STEAM ENGINES TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS WORKING METALLIC POWDER
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Beschreibung
Zusammenfassung:	Embodiments of a gas turbine engine rotor (60) including stress relief features are provided, as are embodiments of method (88) for producing a gas turbine engine rotor. In one embodiment, the method includes producing (90) a hub preform (102) in which a plurality of elongated sacrificial cores (94) are embedded. Blades (72) are attached (120) to an outer circumference of the hub preform by, for example, bonding a blade ring (124) to the outer circumference of the preform. The blades are spaced about the rotational axis (40) of the gas turbine engine rotor and circumferentially interspersed with the plurality of elongated sacrificial cores. The plurality of elongated sacrificial cores are then removed (126) from the hub preform to yield a plurality of stress distribution tunnels (76) extending in the hub preform.