Turbine wheel with clamped blade attachment

Patent metadata

Field	Value
Publication number	US-10689991-B2
Application number	US-201816049142-A
Country	US
Kind code	B2
Filing date	Jul 30, 2018
Priority date	Jan 13, 2015
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

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 from a composite comprising ceramic matrix material. The blades each include a root that fits within dovetail slots of the rotor disk and cooperates with a blade retention assembly 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 rotor disk formed to include a slot cut into the rotor disk at a broach angle (α) relative to a central axis of the rotor disk that extends through the rotor disk from a forward side to an aft side of the rotor disk and inwardly in a radial direction from an outer diameter of the rotor disk toward the central axis,
a blade comprising ceramic-containing materials, the blade formed to include an airfoil that extends outwardly in the radial direction from the outer diameter of the rotor disk and a root that extends into the slot, the root including a stem that extends from the airfoil into the slot and a retention head that extends from the stem and is arranged in the slot, and
a blade retention assembly including at least two clamp blocks, wherein the at least two clamp blocks are formed to include recesses that receive the retention head of the blade, wherein the clamp blocks engage the retention head and are configured to transfer centrifugal loads from the retention head through the blade retention assembly to the rotor disk when the turbine wheel is rotated about the central axis, and wherein the recesses formed in the clamp blocks are arranged at an angle (β) relative to the slot such that the blade is positioned at a relatively greater angle (θ) to the central axis than the broach angle alone.

2. The turbine wheel of claim 1 , wherein the retention head extends axially out from the stem.

3. The turbine wheel of claim 2 , wherein the retention head extends circumferentially out from the stem.

4. The turbine wheel of claim 1 , wherein the at least two clamp blocks are moveable independent of one another within the slot.

5. The turbine wheel of claim 1 , wherein the at least two clamp blocks are fixed to one another to trap the root of the blade engaged by the at least two clamp blocks.

6. The turbine wheel of claim 5 , wherein the at least two clamp blocks are diffusion bonded to one another.

7. The turbine wheel of claim 5 , wherein the at least two clamp blocks are diffusion brazed to one another.

8. The turbine wheel of claim 5 , wherein the at least two clamp blocks are fixed to one another in positions to exert clamp force on the root of the blade engaged by the at least two clamp blocks when the turbine wheel is stationary.

9. The turbine wheel of claim 8 , further comprising at least one compliant member having greater compliance than the at least two clamp blocks and the root of the blade, wherein the at least one compliant member is arranged between at least one of the two clamp blocks and the root of the blade to distribute clamp force applied to the root of the blade by the clamp blocks.

10. The turbine wheel of claim 1 , wherein the slot has a dovetail cross-sectional shape and the clamp blocks cooperate to form a corresponding dovetail shape.

11. The turbine wheel of claim 1 , wherein the slot has a fir tree cross-sectional shape and the clamp blocks cooperate to form a corresponding fir tree shape.

12. The turbine wheel of claim 1 , wherein the retention head extends in an axially forward and aft direction out from the stem.

13. The turbine wheel of claim 12 , wherein the retention head extends circumferentially out from the stem.

14. A turbine wheel for a gas turbine engine, the turbine wheel comprising
a rotor disk formed to include a slot cut into the rotor disk at a broach angle (α) relative to a central axis of the rotor disk that extends through the rotor disk from a forward side to an aft side of the rotor disk,
a blade formed to include an airfoil and a root that extends into the slot, the root including a stem that extends from the airfoil into the slot and a retention head arranged in the slot, and
a blade retention assembly including two clamp blocks, wherein the two clamp blocks are formed to include recesses that receive the retention head of the blade, wherein the clamp blocks engage the retention head, and wherein the recesses formed in the clamp blocks are arranged at an angle (β) relative to the slot such that the blade is positioned at a relatively greater angle (θ) to the central axis than the broach angle (α) alone.

15. The turbine wheel of claim 1 , wherein the retention head extends in an axially forward and aft direction out from the stem.

16. The turbine wheel of claim 15 , wherein the retention head extends circumferentially out from the stem.

17. The turbine wheel of claim 15 , wherein the two clamp blocks are fixed to one another to trap the root of the blade engaged by the two clamp blocks.

18. The turbine wheel of claim 17 , wherein the two clamp blocks are fixed to one another in positions to exert clamp force on the root of the blade engaged by the two clamp blocks when the turbine wheel is stationary.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

• Engel Todd Z
• Freeman Ted J
• Shinavski Robert J
• Thomson Ian

Classifications

• Y02T50/60

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

• F05D2230/236

  Diffusion bonding · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F01D5/3007

  of axial insertion type · CPC title

• F01D5/3053

  by means of pins · CPC title