Abstract: The present disclosure provides devices and methods related to rotor disk bosses. For example, a rotor disk assembly comprises a first rotor disk, wherein the first rotor disk comprises a web, disposed between a rim and a bore. The rotor disk assembly further comprises a second rotor disk operatively coupled to the first rotor disk, an inter-disk device disposed on the second rotor disk and extending axially toward the first rotor disk, and a boss disposed on the first rotor disk, wherein the boss protrudes axially from the web toward the inter-disk device.

Abstract: The present disclosure provides devices and methods related to rotor disk bosses. For example, a rotor disk assembly comprises a first rotor disk, wherein the first rotor disk comprises a web, disposed between a rim and a bore. The rotor disk assembly further comprises a second rotor disk operatively coupled to the first rotor disk, an inter-disk device disposed on the second rotor disk and extending axially toward the first rotor disk, and a boss disposed on the first rotor disk, wherein the boss protrudes axially from the web toward the inter-disk device.

Abstract: The present disclosure provides devices and methods related to rotor disk bosses. For example, a rotor disk assembly comprises a first rotor disk, wherein the first rotor disk comprises a web, disposed between a rim and a bore. The rotor disk assembly further comprises a second rotor disk operatively coupled to the first rotor disk, an inter-disk device disposed on the second rotor disk and extending axially toward the first rotor disk, and a boss disposed on the first rotor disk, wherein the boss protrudes axially from the web toward the inter-disk device.

Abstract: A fan blade of a gas turbine engine may include a blade body having an inner surface defining a cavity in the blade body. A blade filler may be disposed in the cavity. The blade filler may include a bump integrally formed on a first surface of the blade filler. An adhesive may be formed on the first surface of the blade filler. The first surface of the blade filler may be bonded to a fan blade component.

Abstract: The present disclosure provides devices and methods related to rotor disk bosses. For example, a rotor disk assembly comprises a first rotor disk, wherein the first rotor disk comprises a web, disposed between a rim and a bore. The rotor disk assembly further comprises a second rotor disk operatively coupled to the first rotor disk, an inter-disk device disposed on the second rotor disk and extending axially toward the first rotor disk, and a boss disposed on the first rotor disk, wherein the boss protrudes axially from the web toward the inter-disk device.

Abstract: A rotor for a gas turbine engine includes an annular structure having a blade slot. A hub engagement feature is provided on the annular structure. The hub engagement feature includes first and second surfaces transverse to one another and joined by a fillet that is recessed with respect to the first and second surfaces. A method of manufacturing a rotor includes the steps of machining an annular hub engagement feature into a rotor. The hub engagement feature includes first and second surfaces transverse to one another and is joined by a fillet that is recessed with respect to the first and second surfaces. The method includes the step of peening the fillet, and grinding the first and second surfaces.

Abstract: A fan frame (10) for a gas turbine is provided. The fan frame (10) has fan exit guide vanes (100) that are connected to an intermediate case (50) for structural support, and are constrained from movement in a radial direction by a first joint (110, 110a) and constrained from movement in an axial and radial direction by a second joint (120a, 110a). The intermediate case (50) provides structural integrity while reducing weight by providing struts (56, 95) with a width that increases in a direction away from a central bearing (55) as the thickness of the struts (56, 95) decreases.