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.

A turbine wheel assembly adapted for use in a gas turbine engine includes turbine blades made from ceramic matric composite materials.

A turbine wheel assembly adapted for use in a gas turbine engine includes turbine blades made from ceramic matric composite materials. The turbine blades are mounted to a disk and anti-rotation features block movement of the turbine blades around a circumference of the disk.

A ceramic matrix composite (CMC) turbine blade assembly includes a rotor, a CMC turbine blade, and at least one dovetail sleeve. The rotor has a blade slot with at least one slot surface. The slot surface is at a slot angle. The CMC turbine blade is received in the blade slot. The CMC turbine blade includes a dovetail root having at least one root surface. The root surface is at a root angle. The root angle is at least 5 degrees greater than the slot angle. The dovetail sleeve is received in the blade slot of the rotor. The dovetail sleeve has at least one inner surface contacting at least one root surface and at least one outer surface contacting at least one slot surface to radially retain the CMC turbine blade in the blade slot. A dovetail sleeve and a method of mounting a CMC turbine blade are also disclosed.

A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a platform system. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades are coupled with the disk for rotation therewith. The platform system includes a plurality of platforms arranged around the blades and a coverplate that blocks movement of the platforms relative to the disk.

A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a plurality of platforms. The disk is configured to rotate about an axis during operation of the gas turbine engine. Each of the plurality of blades includes a root received in the disk and an airfoil that extends radially away from the root. The platforms are arranged around the blades to define a boundary of a flow path of the gas turbine engine.

A rotor includes a rotor hub, a plurality of blades mounted in a circumferentially-spaced arrangement on the rotor hub and a plurality of platform segments circumferentially arranged, respectively, between neighboring ones of the blades. The platform segments include core gas-path defining surfaces and are mounted with a freedom to circumferentially move relative to the neighboring ones of the blades.

Disclosed is a gas turbine engine component, and a method for forming the component. The component includes a first portion, a second portion formed separately from the first portion, and an intermediate layer provided between the first portion and the second portion.

A wheel assembly for a gas turbine engine includes a disk, a blade-attachment system, and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blade-attachment system is configured to couple the plurality of blades with the disk for rotation therewith.

A ceramic matrix composite (CMC) turbine blade includes an airfoil, a hub extending from the airfoil, and a shank extending from the hub. The airfoil includes a leading edge, a trailing edge, a pressure side, and a suction side. The shank includes a dovetail root having a dovetail path curved in a radial plane. In some embodiments, a leading shank length of the shank at the leading edge and a trailing shank length of the shank at the trailing edge are greater than an intermediate shank length at an intermediate location between the leading edge and the trailing edge. At least one of the airfoil, the hub, and the shank is formed from a CMC. A method of forming the CMC turbine blade includes forming the dovetail root to have a dovetail path curved in a radial plane.