Turbine wheel assembly with circumferential blade attachment

Patent metadata

Field	Value
Publication number	US-10934863-B2
Application number	US-201816189682-A
Country	US
Kind code	B2
Filing date	Nov 13, 2018
Priority date	Nov 13, 2018
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

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

First claim

What is claimed is:

1. A turbine wheel assembly adapted for rotation about a central reference axis within a gas turbine engine, the assembly comprising
a multi-piece disk made of metallic materials, the multi-piece disk including a forward drum and an aft drum, each of the forward drum and the aft drum having a hub that extends around the central reference axis and a rim that provides a radially-outer portion of the multi-piece disk, the rim of the forward drum and the rim of the aft drum shaped to provide a radially-outwardly opening root channel that forms a dovetail shape when viewed circumferentially around the central reference axis,
a turbine blade made of ceramic matrix composite materials, the turbine blade shaped to include a root having a dovetail shape that is arranged in the root channel of the multi-piece disk to couple the turbine blade to the multi-piece disk and an airfoil arranged radially outward of the multi-piece disk, and
a disk linkage configured to fix the forward drum to the aft drum of the multi-piece disk when the root of the turbine blade is arranged in the root channel of the multi-piece disk so that the root is retained in the root channel, the disk linkage including (i) a curvic coupling having a plurality of axially-rearwardly extending teeth in the forward drum and a plurality of axially-forwardly extending teeth in the aft drum intermeshed with the plurality of axially-rearwardly extending teeth to provide radial and circumferential alignment of the forward drum with the aft drum relative to the central reference axis and (ii) a plurality of fasteners that extend radially from the forward drum to the aft drum of the multi-piece disk to provide clamping of the forward drum to the aft drum,
wherein each of the plurality of fasteners extends through one of the plurality of axially-rearwardly extending teeth or one of the plurality of axially-forwardly extending teeth; further comprising an anti-rotation feature arranged along a floor of the root channel of the multi-piece disk that is configured to block movement of the turbine blade relative to the multi-piece disk about the central reference axis and the anti-rotation feature extends radially into at least one of the plurality of axially-rearwardly extending teeth or the plurality of axially-forwardly extending teeth.

2. The assembly of claim 1 , wherein the forward drum portion of the coupling is radially positioned between the hub and the rim of the forward drum, and the aft drum portion of the coupling is radially positioned between the hub and the rim of the aft drum.

3. The assembly of claim 1 , wherein each of the plurality of fasteners includes a tie bolt that extends through the multi-piece disk and a nut threadedly engaged with the tie bolt.

4. The assembly of claim 3 , wherein the coupling is located radially between the hub of the forward drum and the rim of the forward drum, and the coupling is located radially between the hub of the aft drum and the rim of the aft drum.

5. The assembly of claim 3 , wherein each tie bolt included in the plurality of fasteners extends through the forward drum at a location in the multi-piece disk where hoop stress is equal to radial stress resulting in the multi-piece disk during rotation of the assembly about the central reference axis.

6. The assembly of claim 1 , wherein the anti-rotation feature includes an anti-rotation pin that extends radially outward from the floor of the root channel and is configured to engage the root of the turbine blade to block movement of the turbine blade relative to the multi-piece disk about the central reference axis and an anti-rotation pin slot formed in the multi-piece disk into which at least a portion of the anti-rotation pin extends and the anti-rotation pin slot is defined by the at least one of the plurality of axially-rearwardly extending teeth or the plurality of axially-forwardly extending teeth.

7. The assembly of claim 6 , wherein the anti-rotation pin engages a circumferential face of the root of the turbine blade.

8. A turbine wheel assembly adapted for rotation about a central reference axis within a gas turbine engine, the assembly comprising
a multi-piece disk made of metallic materials, the multi-piece disk including a forward drum and an aft drum, each of the forward drum and the aft drum having (i) a hub that extends around and directly faces the central reference axis, (ii) a coupling portion having a plurality of axially-rearwardly extending teeth in the forward drum and a plurality of axially-forwardly extending teeth in the aft drum intermeshed with the plurality of axially-rearwardly extending teeth, and (iii) a rim that extends radially outwardly from the coupling portion, wherein the coupling portion of the forward drum engages the coupling portion of the aft drum to radially and circumferentially align the forward drum with the aft drum, and wherein the rim of the forward drum and the rim of the aft drum are shaped to provide a root channel that forms a dovetail shape when viewed circumferentially around the central reference axis,
a turbine blade made of ceramic matrix composite materials, the turbine blade shaped to include a root having a dovetail shape that is arranged in the root channel of the multi-piece disk,
at least one tie bolt that clamps the forward drum of the multi-piece disk to the aft drum of the multi-piece disk to axially retain the coupling portion of the forward drum relative to the coupling portion of the aft drum so that a coupling between components of the multi-piece disk is established, and
an anti-rotation feature arranged along a floor of the root channel configured to block movement of the turbine blade relative to the multi-piece disk about the central reference axis and the anti-rotation feature extends into at least one of the plurality of axially-rearwardly extending teeth or the plurality of axially-forwardly extending teeth.

9. The assembly of claim 8 , wherein the at least one tie bolt includes a plurality of tie bolts circumferentially spaced from one another about the central reference axis.

10. The assembly of claim 9 , wherein each tie bolt included in the plurality of tie bolts extends through the forward drum and aft drum at a location in the multi-piece disk where hoop stress is equal to radial stress resulting in the multi-piece disk during rotation of the assembly about the central reference axis.

11. The assembly of claim 9 , wherein the plurality of tie bolts extend through the coupling portion of the forward drum and the coupling portion of the aft drum.

12. The assembly of claim 11 , wherein each of the plurality of tie bolts extends through one of the plurality of axially-rearwardly extending teeth or one of the plurality of axially-forwardly extending teeth.

13. The assembly of claim 8 , wherein the at least one tie bolt extends through the forward drum at a location in the multi-piece disk where hoop stress is equal to radial stress resulting in the multi-piece disk during rotation of the assembly about the central reference axis.

14. The assembly of claim 8 , wherein the anti-rotation feature includes an anti-rotation pin that extends radially outward from the floor of the root channel and is configured to engage the root of the turbine blade to block movement of the turbine blade relative to the multi-piece disk about the central reference axis and an anti-rotation pin slot formed in at least one of the plurality of axially-rearwardly extending teeth or the plurality of axially-forwardly extending teeth of the multi-piece disk into which at least a portion of the anti-rotation pin extends.

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Morrison Daniel K
• Freeman Ted J

Classifications

• F01D5/3084 Primary

  the blades being made of ceramics · CPC title

• F01D5/3069 Primary

  between two discs or rings · CPC title

• F01D5/30

  Fixing blades to rotors; Blade roots {; Blade spacers} · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title