Turbine blisk including ceramic matrix composite blades and methods of manufacture

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

• a disk comprising metallic materials and forming an outer surface, the outer surface being a continuous circumferential surface that extends around a central axis that defines an axial direction parallel thereto and a radial direction perpendicular thereto,
• a blade comprising ceramic matrix composite materials, the blade including a root arranged radially outward of the outer surface formed by the disk and an airfoil extending radially outward from the root, and
• a ring coupled to the disk and extending around the outer surface formed by the disk, the ring formed to include an opening that receives at least a portion of the root included in the blade to couple the blade to the ring while at least a portion of the airfoil included in the blade is arranged outside of the opening radially outward of the ring to interact with gasses radially outward of the ring,
• wherein a diameter of the outer surface formed by the disk is greater than a radially-inner surface of the ring when the disk and the ring are at the same temperature so that the disk and the ring are interference fit with one another and wherein an end surface of the root is spaced apart from at least one of the outer surface formed by the disk and the inner surface of the ring by a distance d and wherein the distance d is a distance greater than zero.

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

• a disk comprising metallic materials and forming an outer surface, the outer surface being a continuous circumferential surface that extends around a central axis that defines an axial direction parallel thereto and a radial direction perpendicular thereto,
• a blade comprising ceramic matrix composite materials, the blade including a root arranged radially outward of the outer surface formed by the disk and an airfoil extending radially outward from the root, and
• a ring coupled to the disk and extending around the outer surface formed by the disk, the ring formed to include an opening that receives at least a portion of the root included in the blade to couple the blade to the ring while at least a portion of the airfoil included in the blade is arranged outside of the opening radially outward of the ring to interact with gasses radially outward of the ring,
• wherein the opening formed in the ring extends radially through the ring from a radially-inner surface of the ring to a radially-outer surface of the ring,
• wherein the root of the blade forms a dovetail shape or tapered outward shape and the opening formed in the ring forms a negative shape corresponding to at least a portion of the root, and
• wherein the opening and the at least a portion of the root received by the opening are sized to allow for relative motion between the blade and the ring so that differing rates of thermal expansion between the blade and the disk can be accounted for.

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

• a disk having an outer surface, the outer surface being a continuous circumferential surface;
• a coupling member having a first surface and a second surface, and defining a plurality of openings between the first surface and the second surface, the first surface configured to be coupled to the outer surface of the disk;
• and
• a plurality of blades, a portion of a blade from the plurality of blades being disposed within an opening from the plurality of openings when the first surface of the coupling member is coupled to the outer surface of the disk such that the blade is coupled to the disk,
• wherein the portion of the blade is a root of the blade, the root having a radially-innermost end surface that is spaced radially apart from the radially-outermost surface of the disk when the first surface of the coupling member is coupled to the outer surface of the disk and wherein relative motion between the blade and one of the ring and the disk is allowed.

A method of constructing a turbine disk assembly adapted for use in a gas turbine engine, the method comprising

• inserting a blade through an opening defined by a ring such that a root of the blade is matingly disposed within the opening,
• heating the ring,
• cooling a disk,
• disposing the ring about the disk, and
• equalizing the temperature of the disk and the ring such that an inner surface of the ring is interference fit with an outer surface of the disk and relative motion between the blade and one of the ring and the disk is allowed.