A fan platform includes a platform body that has gaspath and non-gaspath sides, leading and trailing ends, first and second circumferential sides that are contoured to follow profiles of adjacent fan blades, and lugs that project from the non-gaspath side and define fastener openings. The platform body includes a core and a fiber-reinforced polymer matrix composite skin attached on the core at least on portions of the gaspath and non-gaspath sides.

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction. The airfoil section includes a metallic sheath that receives a composite core. The core includes first and second ligaments received in respective internal channels defined by the sheath such that the first and second ligaments are spaced apart along the root section with respect to the chordwise direction. Each one of the first and second ligaments includes at least one interface portion in the root section, and at least one interface portion of the first ligament and the at least one interface portion of the second ligament define respective sets of bores aligned to receive a common retention pin.

A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral base and top portions. The airfoil may include a pin connector connecting the top portion to the base portion. The pin connector may include: a tab extending from the top portion; a complimentary slot for receiving the tab formed in the base portion; an elongated pin cavity formed through an interior region of the airfoil, where the pin cavity intersects the slot to divide the pin cavity into first and second pin cavity segments; a tab aperture formed through the tab, where the tab aperture is positioned so align with the pin cavity upon the tab being received within the slot; and a locking pin that extends continuously through the first segment of the pin cavity, the tab aperture, and the second segment of the pin cavity.

A blade assembly for use in a gas turbine engine. The blade assembly includes a blade, a platform distinct from the blade and configured to extend around the blade, and a pin that couples the platform with the blade.

A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.

A platform for a gas turbine engine according to an example of the present disclosure includes, among other things, a platform body that has a gas path surface extending axially between a leading edge and a trailing edge and extending circumferentially between opposed mate faces. A plurality of platform flanges extend from the platform body to define one or more slots. The one or more slots are dimensioned to receive a respective flange of a rotatable hub, and each platform flange has a retention member dimensioned to receive a retention pin to mount the platform body. The platform body includes a composite wrap extending about a perimeter of the platform body to define an internal cavity. At least one honeycomb core has a plurality of cells that is disposed in the internal cavity.

A turbine-blade assembly for use in a gas turbine engine is disclosed. The turbine-blade assembly includes an attachment body, a heat shield, and a retainer. The heat shield surrounds a portion of the attachment body. The retainer is configured to retain the heat shield on the turbine-blade assembly.

A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral base and top portions. The airfoil may include a pin connector connecting the top portion to the base portion. The pin connector may include: a tab extending from the top portion; a complimentary slot for receiving the tab formed in the base portion; an elongated pin cavity formed through an interior region of the airfoil, where the pin cavity intersects the slot to divide the pin cavity into first and second pin cavity segments; a tab aperture formed through the tab, where the tab aperture is positioned so align with the pin cavity upon the tab being received within the slot; and a locking pin that extends continuously through the first segment of the pin cavity, the tab aperture, and the second segment of the pin cavity.

A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material. The blades each include a root that fits within dovetail slots of the rotor disk and cooperates with a blade retention assembly to couple the blades to the rotor disk.

Rotor assemblies and methods for manufacturing airfoils for rotor assemblies are provided. For example, a rotor assembly comprises a rotary structure extending circumferentially about an axial centerline of a gas turbine engine, an airfoil having a root and a tip, and a pin extending through the root. The root is coupled to the rotary structure and has a bulbous shape, and the airfoil is formed from a plurality of composite plies. The pin defines both a planar first surface and a planar second surface on a pin body having a generally circular cross-section. Further, the pin includes a first end and a second end that contact the rotary structure. The first and second surfaces together form a point that is oriented toward the tip of the airfoil. In one embodiment, the rotary structure is an outer rotor of an interdigitated rotor assembly and the airfoil extends radially inward.