COMPRESSOR DISK BLEED AIR SCALLOPS

A rotor disk for a gas turbine engine includes a hub; a rim with a forward portion and an aft portion; and a plurality of circumferentially spaced radial scallops in the rim to form cooling slots between two disks when the rotor disk is connected to another rotor disk.

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Bibliographische Detailangaben
Hauptverfasser:	ST. MARY, CHRISTOPHER, YILMAZ, CAGDAS, ODELL, GARY S, BAXLEY, RICHARD C
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 rotor disk for a gas turbine engine includes a hub; a rim with a forward portion and an aft portion; and a plurality of circumferentially spaced radial scallops in the rim to form cooling slots between two disks when the rotor disk is connected to another rotor disk.