Abstract: A gas turbine engine composite disk includes dovetail slots between disk posts extending radially inwardly from a periphery, a hub ring of composite plies circumscribed about a centerline axis, and radial plies extending radially away from hub ring into disk posts. A segmented intermediate ring concentric with and located radially outwardly of hub ring includes intermediate ring segments having nested plies with annular bases circumscribed about centerline axis and substantially radially extending clockwise and counter-clockwise radial ply arms. An outer segmented ring may be concentric with and located radially outwardly of intermediate ring, include annular outer ring segments with circumferentially stacked composite plies disposed within intermediate ring segments between clockwise and counter-clockwise radial ply arms and radially outwardly of annular bases. An outer skin of outermost composite covering plies may extend circumferentially around composite disk.

Abstract: Fan blade containment system includes a composite fan case with an annular composite shell extending from forward flange downstream to aft flange, and circumferentially varying thickness portion of composite shell. Annular composite back sheet spaced radially outwardly of annular composite shell has annular filler layer disposed radially therebetween. Annular forward and aft seams between annular composite shell and composite back sheet may axially trap filler layer. Circumferentially varying thickness portion may include aftwardly extending fingers of composite back sheet in aft seam and first thickness of fingers thicker than second thickness of composite shell circumferentially between fingers. Composite shell may extend from forward flange to aft flange. Aft flange bolted to metallic flange of metallic fan casing aft of aft flange. Containment system may circumscribe and surround fan and fan blades of gas turbine engine fan section.

Abstract: The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.

Abstract: A metal leading edge includes a nose positioned along the leading edge of a fan blade airfoil body. The metal leading edge also includes a first edge extending axially aftward from the nose along a pressure side of the fan blade airfoil body. The metal leading edge further includes a second edge extending axially aftward from the nose along a suction side of the fan blade airfoil body. The first edge and the second edge forming a notch at the conjunction of the first edge, the second edge, and the nose. The metal leading edge also includes a nose length extending from a nose tip to the notch. The nose length at a first radial location is different from the nose length at a second radial location.

Abstract: A composite blade assembly and a method of assembling a composite blade are provided. The composite blade assembly includes a composite blade having a radially inner root. A composite blade assembly includes a first platform and a circumferentially adjacent second platform abutting the first platform at a platform joint. Each of the first platform and the second platform includes a radially outer surface and a radially inwardly extending attachment member. The platform joint includes a slot extending through adjacent edges of the first platform and the second platform. The slot is configured to receive the radially inner root and the radially inner root is configured to be sandwiched between the attachment members. The blade assembly includes an adhesive system configured to join the radially inner root of the composite blade and the attachment members into a unitary structure, and a retaining clip configured to bias the attachment members towards each other.

Abstract: A gas turbine engine composite disk includes dovetail slots between disk posts extending radially inwardly from a periphery, a hub ring of composite plies circumscribed about a centerline axis, and radial plies extending radially away from hub ring into disk posts. A segmented intermediate ring concentric with and located radially outwardly of hub ring includes intermediate ring segments having nested plies with annular bases circumscribed about centerline axis and substantially radially extending clockwise and counter-clockwise radial ply arms. An outer segmented ring may be concentric with and located radially outwardly of intermediate ring, include annular outer ring segments with circumferentially stacked composite plies disposed within intermediate ring segments between clockwise and counter-clockwise radial ply arms and radially outwardly of annular bases. An outer skin of outermost composite covering plies may extend circumferentially around composite disk.

Abstract: A device receives healthcare information that includes information associated with a health of a user. The healthcare information is received from a multiple devices that monitor the health of the user and/or store information regarding the health of the user. The device performs an analysis of the healthcare information via one or more analytics techniques, and identifies a type of health-related motivation, from multiple types of health-related motivations, based on performing the analysis. The device provides the type of health-related motivation to a user device associated with the user.