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US 10,428,661 B2Granted
Turbine wheel assembly with ceramic matrix composite components
AssigneesRoll-Royce North American Technologies Inc., ROLLS-ROYCE plc
InventorsDavid J. Thomas, Ted J. Freeman, Aaron D. Sippel, Daniel K. Vetters
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a turbine section having static turbine vane rings and turbine wheel assemblies. The vane rings are arranged to direct combustion products toward blades included in the turbine wheel assemblies to cause the turbine wheel assemblies to rotate.
Claims14
A turbine wheel assembly adapted for use in a turbine section of a gas turbine engine, the turbine wheel assembly comprising
- a disk comprising metallic materials and arranged around a central axis,
- a plurality of blades comprising ceramic matrix composite materials, each of the plurality of blades including a root received in a slot formed in the disk to couple the blade to the disk, an airfoil arranged radially outward of the disk, and a platform that extends circumferentially from the airfoil around a portion of the disk without extending axially forward or axially aft of the airfoil to define a portion of a primary gas path located radially outward of the platform, and
- a first face plate coupled to the disk, the first face plate including a main ring arranged axially adjacent to the roots of the plurality of blades to block movement of the root out of the slots and a first seal flange that extends axially from the main ring adjacent to the platforms of the blades to resist movement of gas into and out of the primary engine gas path,
- wherein the first seal flange of the first face plate has a radially-outwardly facing surface that is co-radial with an outer surface of the platforms of the blades so as to define another portion of the primary gas path,
- wherein the main ring of the first face plate has a radially-outwardly facing surface that is co-radial with an outer surface of the platforms of the blades to define another portion of the primary gas path.
2 more elements
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, the inner band of the vane ring includes a gas path member that defines a portion of a primary engine gas path and a static seal ring that extends inward in a radial direction, 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 gas path member of the inner band of the vane ring such that the first seal ring is located radially directly inward of the gas path member to establish a seal configured to resist movement of gas into and out of the primary engine gas path defined, in part, by the inner band of the vane ring and the platforms of the blades,
- wherein the static seal ring of the inner band is arranged axially between the first seal ring of the face plate and the blade included in the turbine wheel assembly and the static seal ring and the first seal ring overlap in the radial direction,
- wherein the first seal ring is spaced axially from the main ring along the central axis,
- wherein the face plate includes a plurality of secondary seal rings that extends radially outward from the seal flange toward the inner band of the vane ring and each of the plurality of secondary seal rings are spaced axially from the first seal ring.
4 more elements
A turbine wheel assembly comprising
- a plurality of blades comprising ceramic matrix composite materials arranged around a central axis of the turbine wheel assembly, each of the plurality of blades including an airfoil having a leading edge and a trailing edge spaced axially apart from the leading edge, a root arranged radially inward of the airfoil, and a platform that extends circumferentially from the airfoil around a portion of the central axis without extending axially forward of the leading edge or axially aft of the trailing edge of the airfoil, the platforms each include a radially-outwardly facing outer surface to define a portion of a primary engine gas path,
- a forward face plate including a forward main ring arranged axially adjacent to the roots of the plurality of blades and a forward seal flange that extends axially from the forward main ring adjacent to the platforms of the blades, and
- an aft face plate including an aft main ring arranged axially adjacent to the roots of the plurality of blades and a first aft seal flange that extends axially from the aft main ring adjacent to the platforms of the blades, wherein the first aft seal flange has a radially-outwardly facing surface that is co-radial with the outer surface of the platforms of the blades so as to define another portion of the primary engine gas path.
Dependencies are inferred from the claim text.