Turbine wheel assembly with ceramic matrix composite components

A turbine section adapted for use in a gas turbine engine, the turbine section comprising

• a vane ring that extends around a central axis, the vane ring including an outer band, an inner band spaced radially inward of the outer band, and a plurality of vane airfoils that extend from the outer band to the inner band, and
• a turbine wheel assembly mounted for rotation about the central axis, the turbine wheel assembly including a disk comprising metallic materials, a plurality of blades, and a face plate coupled to the disk for rotation therewith,
• wherein each of the plurality of blades includes a root received in a slot formed in the disk to couple the blade to the disk, a turbine airfoil arranged radially outward of the disk, and a platform that extends circumferentially from the turbine airfoil around a portion of the disk without extending axially forward or axially aft of the turbine airfoil, and
• wherein the face plate includes a main ring arranged axially adjacent to the roots of the plurality of blades to block movement of the roots out of the slots, a seal flange that extends axially from the main ring, and a first seal ring that extends radially outward from the seal flange toward the inner band of the vane ring to establish a seal configured to resist movement of gas into and out of a primary engine gas path defined, in part, by the inner band of the vane ring and the platforms of the blades.