A spacer for use in a hub and blade assembly of a gas turbine engine including a first layer of a first material forming the spacer body having an elongate shape. The first material has a first stiffness. A second layer of a second material is mechanically attached to the first layer. The second material has a second stiffness different from the first stiffness.

A turbine engine including: rotor blades circumferentially arrayed about a rotor wheel; a connection assembly by which each of the rotor blades connects to the rotor wheel, the connection assembly including: an axially oriented slot formed through a perimeter face of the rotor wheel; a root of the rotor blade installed within the slot, the root being shaped in relation to the slot such that the installation therein forms an axially extending shim cavity between opposing exterior surfaces of the root and the slot; and a shim installed within the shim cavity for restraining movement of the rotor blade relative to the rotor wheel in a radial direction.

A fan assembly for an aviation turbine engine, the assembly including a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk, the platform including a box of composite material made from fiber reinforcement densified by a matrix, the box having a flow passage wall, a bottom wall, and two side walls extending radially between the bottom wall and the flow passage wall. The box of the platform includes an upstream opening at an upstream end of the platform and a downstream opening, and the assembly also includes a locking key housed in the box and passing through the upstream and downstream openings of the box, the locking key being blocked at each of its ends by a blocking element.

Assembly for a turbomachine blade, comprising: a fastener (9) defining a pocket (10) for receiving a blade root (11), and comprising two flanks defining between them a passage leading into the pocket (10) and forming stops preventing the root (11) from exiting from the pocket (10) via the passage, a shim (26a, 26b) adapted to be received in the pocket (10) with the root (11), the shim (26a, 26b) having a first support surface (28a, 28b) to bear on the root (11) and a second support surface (30a, 30b) opposite the first support surface (28a, 28b) to bear against the fastener (9), the support surfaces being fixed relative to each other and oriented such that movement of the shim (26a, 26b) in the pocket (10) relative to the fastener (9) varies the value of force exerted by the shim (26a, 26b) on the root (11).

A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The rim includes a first radially outermost rim portion and a second radially outermost rim portion disposed radially inward of the first radially outermost rim portion. First and second blade posts are disposed proximate the first radially outermost rim portion and spaced circumferentially. First and second tabs are disposed proximate the second radially outermost rim portion and positioned radially inward of the first and second blade posts. A slot is disposed circumferentially between the first tab and the second tab. The first tab and the second tab have an axial profile that includes a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion.

A slider for chocking a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc. The slider, in use, is slidingly inserted in an axially-extending cavity formed in the base of the root and in the disc at the base of the slot to urge the blade radially outwardly and thereby mate flanks of the root to flanks of the slot. The slider is arc-shaped and the cavity is correspondingly arc-shaped. The normal to the plane of the arc of the arc-shaped cavity is substantially perpendicular to the engine axis such that, when inserted in the cavity, the slider also retains the root axially in the slot.

A wheel assembly for a gas turbine engine is disclosed. The wheel assembly includes a disk arranged for rotation about a central axis and formed to include a plurality of slots. The wheel assembly also includes a plurality of blades sized to be received in the plurality of slots so that the blades are coupled to the disk for common rotation about the central axis. The wheel assembly further includes a plurality of blade biasers positioned in the slots between the disk and the blades so that the blade biasers are engaged with the disk and the blades to preload the blades away from the central axis.

A gas turbine engine includes a fan forward of a primary flowpath inlet. The fan includes multiple fan blades distributed radially about, and connected to, a hub. A fan nacelle is positioned radially outward of the fan and includes an inner diameter. The inner diameter is sloped relative to an engine axis such that a forward portion of the fan nacelle has a smaller inner diameter than an aft portion of the fan nacelle. A fan blade spacer is disposed between a radially inward facing surface of at least one fan blade and a radially outward facing surface of the hub. The fan blade spacer has a radial thickness at least equal to a slope drop of the fan nacelle.

A turbine engine having a disk, a composite airfoil assembly and a pitch snubber. The disk having a slot. The composite airfoil assembly having an airfoil portion and a dovetail portion. The dovetail portion having a radially inner surface spaced from the slot to define a gap therebetween. The pitch snubber being provided on one of the slot or the radially inner surface of the dovetail portion.

A fan includes a rotor hub comprising a slot and a blade comprising an airfoil extending from a blade root in a first direction. The blade root is configured to be received in the slot. The fan also includes a deformable spacer situated between the rotor hub and the blade root in the slot, a first blade lock situated at a first side of the slot, and a second blade lock situated at a second side of the slot opposite the first side. At least one of the first and second blade locks includes a tab configured to extend between the blade root and the rotor hub and to compress the spacer such that the spacer exerts a force on the blade in the first direction. A method of assembling a fan and another example fan are also disclosed.