Abstract: A rotating machine includes a plurality of rotors. Each of the rotors includes a rotor bore protruding radially inward from a platform. A ring shaped cover plate is interfaced with each rotor bore via at least one snap. The at least one snap includes a first arm extending from the cover plate and having a convex facing contact surface, and multiple second arms extending axially from each rotor bore and having contact surfaces facing the convex surface.

Abstract: A rotating machine includes a plurality of rotors. Each of the rotors includes a rotor bore protruding radially inward from a platform. A ring shaped cover plate is interfaced with each rotor bore via at least one snap. The at least one snap includes a first arm extending from the cover plate and having a convex facing contact surface, and multiple second arms extending axially from each rotor bore and having contact surfaces facing the convex surface.

Abstract: A fan blade assembly for a gas turbine engine is provided. The fan blade assembly having: a non-linear composite airfoil; and a metal root removably attached to the non-linear composite airfoil.

Abstract: A fan rotor, for an aircraft engine, including at least one blade root attachment lug, each blade root attachment lug including an attachment lug surface, wherein at least one cavity is disposed on each attachment lug surface.

Abstract: A rotor disk assembly may include a rotor disk and a retention ring coupled to the rotor disk. Generally, the retention ring is tuned to adjust a modal frequency response of the rotor disk/rotor disk assembly. In various embodiments, dimensions of the retention ring vary circumferentially. In various embodiments, the retention ring includes an axially extending flange and a radially extending flange. A radial thickness of the axially extending flange may vary circumferentially and/or an axial thickness of the radially extending flange may vary circumferentially.

Abstract: A segmented structural link may comprise a base portion having a first face, a tail portion, and a distal end having a second face. The tail portion may extend at an angle relative to the first face. The tail portion may comprise a first bend and may further comprise a second bend. The base portion may comprise at least one of a captured nut, a nut plate, or a self-clinching nut.

Abstract: A rotor disk assembly may include a rotor disk and a retention ring coupled to the rotor disk. Generally, the retention ring is tuned to adjust a modal frequency response of the rotor disk/rotor disk assembly. In various embodiments, dimensions of the retention ring vary circumferentially. In various embodiments, the retention ring includes an axially extending flange and a radially extending flange. A radial thickness of the axially extending flange may vary circumferentially and/or an axial thickness of the radially extending flange may vary circumferentially.

Abstract: A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.

Abstract: A fan section for a gas turbine engine includes a fan hub having blade slots for receiving a root of a fan blade. A lock ring is configured to move rotatably from an unlocked position to a locked position for securing the blade root in the blade slot. A nose cone is secured to the lock ring, and thereby secured to the fan section.

Abstract: A fan blade assembly for a gas turbine engine is provided. The fan blade assembly having: a non-linear composite airfoil; and a metal root removably attached to the non-linear composite airfoil.

Abstract: A rotor assembly for a gas turbine engine includes a plurality of blades including a root portion and an airfoil portion. The rotor includes a plurality of slots that receive the root portion of a corresponding blade. The rotor includes an annular groove for a first and second retaining ring. The retaining rings are received within a common annular groove for holding each of the plurality of blades within the slots of the rotor.

Abstract: A gas turbine engine fan section includes a fan hub configured to rotate about an axis. A nose cone includes a spinner operatively mounted to the fan hub. The spinner supports a first fastening element and the nose cone includes an annular cover arranged over the fastening element. The spinner and annular cover provide an aerodynamic exterior surface of the nose cone without exposed fasteners. A second fastening element cooperates with the first fastening element to secure the spinner relative to the fan hub. The first and second fastening elements are oriented transversely to the axis.

Abstract: A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.

Abstract: A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.

Abstract: A fan rotor, for an aircraft engine, including at least one blade root attachment lug, each blade root attachment lug including an attachment lug surface, wherein at least one cavity is disposed on each attachment lug surface.

Abstract: A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.

Abstract: A gas turbine engine fan blade lock assembly includes a fan hub that has blade slots each configured to receive a root of a fan blade. The fan hub includes circumferentially spaced first slots. A lock ring is configured to move between unlocked and locked positions. The lock ring includes circumferentially spaced second slots aligned with the first slots in the locked position, and multiple discrete pins. Each pin is configured to be slidably received in paired first and second slots in the locked position to prevent rotational movement of the lock ring relative the fan hub.

Abstract: A turbine engine rotor assembly includes a turbine engine rotor disk that extends axially along a centerline between a first disk end and a second disk end, and radially to an outer disk surface. The rotor disk includes one or more blade retention slots arranged circumferentially around the centerline. A first of the blade retention slots extends axially into the rotor disk from a disk end surface at the first disk end to a slot end surface, and radially into the rotor disk from the outer disk surface to a slot base surface.

Abstract: A fan section for a gas turbine engine includes a fan hub having blade slots for receiving a root of a fan blade. A lock ring is configured to move rotatably from an unlocked position to a locked position for securing the blade root in the blade slot. A nose cone is secured to the lock ring, and thereby secured to the fan section.

Abstract: A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.