A multi-piece disk for use in a turbine of a gas turbine engine. The multi-piece disk includes a fore disk segment and an aft disk segment coupled with the fore disk segment for movement with the fore disk segment. The fore disk segment and the aft disk segment are formed to define slots that extend through the disk segments and are configured to receive turbine blades therein.

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.

A turbine blade assembly adapted for use in a gas turbine engine is disclosed in this paper. A primary member of the turbine blade assembly shaped to form an airfoil and comprises ceramic matrix composite materials. A independent platform of the turbine blade assembly is coupled to the primary member of the turbine blade assembly such that the primary member need not be shaped to provide the platform.

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 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.

An airfoil includes an airfoil piece that defines at least a portion of an airfoil profile. The airfoil piece has a radial end and a first radial slot in the radial end. An end section has a second radial slot adjacent the first radial slot. The first radial slot and the second radial slot together form a radial seal slot. A seal is disposed in the radial seal slot.

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 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 blade for a gas turbine engine includes a root and an aerofoil. The root is configured to be coupled with a disc of the gas turbine engine and rotate with the disc about an axis during operation of the gas turbine engine. The aerofoil is coupled with the root of the turbine blade for movement with the root.