Abstract: An airfoil assembly (30) comprises a composite airfoil (40) having a leading edge (32) and a trailing edge (34), a pressure side (36) extending between the leading edge and the trailing edge, a suction side (38) extending between the leading edge and the trailing edge, opposite the leading edge, a metallic leading edge assembly (130) disposed over the composite air-foil, the metallic leading edge assembly including a high density base (50), the metallic leading edge assembly also including a nose (60) disposed over the base, an adhesive bond layer disposed between the composite airfoil and the metallic leading edge assembly.

Abstract: A method of operating a gas turbine engine is provided. The method includes channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a cavity defined in the shroud hanger assembly, directing the cooling air through a plurality of cooling passages extending from the cavity, and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger.

Abstract: A method of operating a gas turbine engine is provided. The method includes channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a cavity defined in the shroud hanger assembly, directing the cooling air through a plurality of cooling passages extending from the cavity, and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger.

Abstract: A preferred embodiment of the present invention is a gas turbine engine rotor assembly having axially spaced apart forward and aft disks circumferentially disposed about an axis. The forward disk has an aftwardly extending annular forward arm and the aft disk has a forwardly extending annular aft arm. Forward and aft flanges are located at forward and aft ends of the forward and aft arms respectively. Forward and aft pluralities of aligned forward and aft bolt holes extending axially through the forward and aft flanges respectively. A scalloped annular ring having a plurality of circumferentially spaced apart tabs with spaces therebetween is disposed between the flanges. A plurality of ring bolt holes extend axially through the plurality of circumferentially spaced apart tabs such that corresponding ones of the ring, forward, and aft bolt holes are axially aligned.

Abstract: A balance weight for the rotor of a gas turbine engine is adapted to mount within the cavity formed between the innermost surface of the dovetail slots formed in the circumference of the rotor disk and the bottom of the dovetail root of the rotor blades inserted within the dovetail slots. The balance weight has a head portion formed with a bottom surface which mates with the innermost surface of the dovetail slots, and a lip connected to the head portion which engages the aft surface of the rotor disk. The balance weight is supported in an aft direction within the dovetail slots by an aft blade retainer having a shoulder or projection which contacts the balance weight.

Abstract: A boltless blade retainer for preventing forward axial movement of the rotor blades in a turbo machine relative to the rotor disk comprises an annular extension or hook formed on each dovetail post on the web of the rotor disk, an impeller or blade retainer formed with a flange which is carried against the web and dovetail posts and a retaining ring interposed between the hooks of the dovetail posts and the flange of the impeller. The retaining ring secures the impeller in a fixed axial position relative to the dovetail posts and rotor disk, and is positioned to engage the rotor blades carried in the axial slots between adjacent dovetail posts to prevent their movement in a forward axial direction.