Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disc.

An assembly includes: a movable blade for a turbomachine including a tip; and a removable part including an anti-wear material, configured to be attached removably to an edge of the tip to limit wear of the tip.

An article has a cavity defined by an inner surface, the cavity having a size such that a largest sphere placeable in the cavity has a diameter of less than 7 cm and a smallest sphere placeable in the cavity has a diameter of 0.5 mm; and a hard coating on the inner surface, the hard coating having a hardness between 18 to 100 GPa, the hard coating distributed on the inner surface such that a ratio of a coating thickness at a first region of the hard coating to that at a second region of the hard coating ranges from 0.75 to 1.33.

A composite blade formed by laying up composite layers containing reinforcing fiber and resin, the composite blade comprising: a blade root mounted in a blade groove; an airfoil extending from the blade root to a front end side; and a metal patch mounted between the blade groove and the blade root, and bonded to the blade root.

A sealing device including a retaining plate arranged in contact with an axial face of the rotor disc such that the retaining plate covers a gap between one of the retention grooves and the corresponding blade secured therein, along the axial direction; and a horn-shaped member protruding from the retaining plate and extending inside of an extrusion in the blade, the horn-shaped member having a first section seated against a complimentary surface inside the extrusion in the blade, wherein a center of gravity of the sealing device lies proximal to the first section of the horn-shaped member to cause the retaining plate to be pulled against the axial face of the rotor disc when the rotor disc is rotating, in order to secure the sealing device with the rotor disc.

A gas turbine engine blade root shim for use between a composite blade root and a wall of a slot in a rotor includes a longitudinally extending base having distal first and second transversely spaced apart ends, first and second longitudinally extending legs acutely angled inwardly towards the base from the first and second ends, and one or more apertures disposed through each of the longitudinally extending first and second legs. Apertures may include rectangular slots having rounded edges along the first and second outwardly facing surfaces of the first and second legs respectively and/or rounded corners between the first and second outwardly facing surfaces and the first and second inwardly facing surfaces of the first and second legs. Low coefficient of friction coatings may be disposed on outwardly facing surfaces, of the legs. Coatings may include polytetrafluoroethylene powder dispersed in a resin binder and other coatings having polytetrafluoroethylene.

A rotor disk assembly for a gas turbine engine includes a rotor disk with a multiple of blade slots, the rotor disk defined about an axis; a sleeve received within each of the multiple of blade slots; and a ceramic matrix composite rotor blade received within each of the multiple of sleeves.

A turbine blade comprising ceramic matrix composite materials and designed for incorporation into a turbine wheel assembly is disclosed in this paper. Further disclosed are features for managing stiffness and dampening in order to influence vibratory response of such a turbine blade when used as part of a turbine wheel assembly in a gas turbine engine.

A composite blade made of prepreg obtained by impregnating reinforcement fibers with resin and curing the resin-impregnated reinforcement fibers, the composite blade including: a blade root provided on a base end and fitted into a blade groove; an airfoil provided extending from the blade root toward a tip end; and a metal patch provided between the blade groove and the blade root and placed on the blade root. The metal patch includes a plurality of projections protruding toward the blade root.