Composite blades for gas turbine engines

Patent metadata

Field	Value
Publication number	US-10180071-B2
Application number	US-201514968199-A
Country	US
Kind code	B2
Filing date	Dec 14, 2015
Priority date	Nov 20, 2014
Publication date	Jan 15, 2019
Grant date	Jan 15, 2019

Abstract

A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material. The blades each include a root to fit within dovetail slots of the rotor disk to couple the blades to the rotor disk.

First claim

What is claimed is:

1. A turbine wheel for a gas turbine engine, the turbine wheel comprising
a disk formed to include a dovetail slot that extends through the disk in an axial direction from a forward side to an aft side of the disk and inwardly in a radial direction from an outer diameter of the disk toward a central axis, and
a blade comprising ceramic-matrix materials, the blade formed to include an airfoil that extends outwardly in the radial direction from the outer diameter of the disk and a root that extends into the dovetail slot,
wherein the root includes a stem that extends from the airfoil into the dovetail slot, a root core, and a root casing that extends from the stem around the root core to couple the root core to the stem, the root casing comprising ceramic-matrix materials and positioned to engage an inner surface of the dovetail slot formed by the disk to retain the blade in place relative to the disk during rotation of the disk,
wherein portions of the airfoil and root casing are formed by at least one continuous ply of ceramic-containing material having a first end forming a portion of the airfoil and extending radially inward from the airfoil to wrap around the root core and extending along itself back radially outward to a second end also forming a portion of the airfoil.

2. The turbine wheel of claim 1 , wherein the dovetail slot includes a pair of blocker walls defining a radially-facing opening extending through the outer diameter of the disk into the dovetail slot and the inner surface, and wherein the inner surface connects the blocker walls.

3. The turbine wheel of claim 2 , wherein the root of the blade has a substantially cylindrical outer profile and the inner surface of the dovetail slot substantially matches the outer profile of the root.

4. The turbine wheel of claim 2 , wherein the root of the blade has a substantially pentagonal outer profile and the inner surface of the dovetail slot substantially matches the outer profile of the root.

5. The turbine wheel of claim 1 , wherein wherein the continuous ply of ceramic-containing material forms at least part of the airfoil and at least part of the root by extending radially inward from the first end, wrapping around the root core, and extending along itself back radially outward to the second end such that the first and second ends are adjacent to one another.

6. The turbine wheel of claim 1 , wherein the blade further includes a cooling channel extending from the root core radially outward through the airfoil such that at least a portion of the airfoil is hollow to allow cooling air to pass through the root core, through the blade, and out of a tip of the airfoil.

7. A turbine wheel for a gas turbine engine, the turbine wheel comprising
a disk formed to include a dovetail slot that extends through the disk in an axial direction from a forward side to an aft side of the disk and inwardly in a radial direction from an outer diameter of the disk toward a central axis, and
a blade formed to include an airfoil that extends outwardly in the radial direction from the outer diameter of the disk and a root that extends into the dovetail slot, the airfoil and root being formed as a composite structure, the root including a stem that extends from the airfoil into the dovetail slot, a root core comprising ceramic-matrix material, and a root casing that extends from the stem around the root core to couple the root core to the stem, the root casing comprising ceramic-matrix materials and positioned to engage an inner surface of the dovetail slot formed by the disk to retain the blade in place relative to the disk during rotation of the disk,
wherein the root core includes at least one tube formed from woven ceramic-containing fibers without an axially extending seam,
wherein at least one continuous ply of ceramic-containing material includes a first end and a second end, and wherein the continuous ply of ceramic-containing material forms at least part of the airfoil and at least part of the root by extending radially inward from the first end, wrapping around the root core, and extending along itself back radially outward to the second end forming at least a part of the airfoil.

8. The turbine wheel of claim 7 , wherein the root core further includes a filler positioned within the at least one tube.

9. The turbine wheel of claim 8 , wherein the filler comprises a plurality of ceramic-containing fibers aligned with one another along a length of the one or more tubes and suspended in a ceramic matrix material.

10. The turbine wheel of claim 8 , wherein the filler comprises a ply of ceramic-containing material continuously rolled onto itself to form a cylinder of ceramic-containing material.

11. The turbine wheel of claim 8 , wherein the filler comprises an infiltrated ceramic foam.

12. The turbine wheel of claim 7 , wherein the continuous ply of ceramic-containing material forms at least part of the airfoil and at least part of the root by extending radially inward from the first end, wrapping around the root core, and extending along itself back radially outward to the second end such that the first and second ends are adjacent to one another.

13. The turbine wheel of claim 12 , wherein the blade further includes a cooling channel positioned between the first and second ends of the at least on continuous ply and extending from the root core radially outward through the airfoil such that at least a portion of the airfoil is hollow to allow cooling air to pass through the root core, through the blade, and out of a tip of the airfoil.

14. The turbine wheel of claim 13 , further including at least one aperture formed through the one or more tubes forming the root core and extending from a hollow interior of the one or more tubes to the cooling channel.

15. The turbine wheel of claim 14 , further including ports formed through the root casing and root core extending from an exterior of the root casing to the hollow interior of the one or more tubes forming the root core.

16. The turbine wheel of claim 13 , further including one or more spacers positioned between the first and second ends of the at least one continuous ply of ceramic-containing material.

17. The turbine wheel of claim 16 , wherein the one or more spacers comprise reticulated ceramic foam.

18. A method of making a turbine wheel, the method comprising
positioning a root of a composite blade in a dovetail slot of a rotor disk such that a root casing of the root is positioned to engage an inner surface of the dovetail slot formed by the disk to retain the blade in place relative to the disk during rotation of the disk,
wherein the root includes a stem that extends from the airfoil into the dovetail slot, a root core, and the root casing, the root casing comprising ceramic-matrix materials and extending from the stem around the root core to couple the root core to the stem,
bonding together plies of ceramic-containing material into a ceramic structure, wherein at least one of the plies forms at least part of the airfoil and at least part of the root casing by extending radially inward from a first end, wrapping around the root core, and extending along itself back radially outward to a second end.

19. The method of claim 18 , further comprising forming the composite blade wherein the root core includes at least one tube formed from at least one of the other plies, and the first and second ends are adjacent to one another.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Nam Tech Inc

Inventors

• Freeman Ted J
• Vetters Daniel K

Classifications

• F05D2230/23

  by permanently joining parts together · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D5/3007

  of axial insertion type · CPC title

• F01D5/284 Primary

  Selection of ceramic materials · CPC title