DISC FOR A ROTOR OF A GAS TURBINE ENGINE, AND A ROTOR AND A GAS TURBINE COMPRISING THE SAME

A disc of a gas turbine engine (10) system is provided. The disc includes a disc hub (203; 403; 603) including, an interstage coupling (207; 307; 407; 607) disposed on an axially extending surface (212; 312; 412; 612) at a peripheral edge of the disc hub that includes a protrusion that extends axial...

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Bibliographische Detailangaben
Hauptverfasser:	PORTER, Steven D, OREN, Nicholas Waters
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A disc of a gas turbine engine (10) system is provided. The disc includes a disc hub (203; 403; 603) including, an interstage coupling (207; 307; 407; 607) disposed on an axially extending surface (212; 312; 412; 612) at a peripheral edge of the disc hub that includes a protrusion that extends axially beyond an outer surface of the disc hub, and a groove (233; 333; 533; 633) formed on the axially extending surface of the disc hub wherein an aft surface (216; 316; 416; 516; 616) of the groove is also a forward surface of the interstage coupling, wherein the groove includes a forward surface (213; 313; 413; 513; 613) that extends radially into the disc hub to a groove floor (214; 314; 414; 514; 614) that is cut into the disc hub and extends axially to the aft surface that extends radially outward to at least the axially extending surface of the disc hub, and a disc web (202; 602) that extends radially outward from the disc hub, relative to an axis of rotation of the gas turbine engine.