Turbine wheels with preloaded blade attachment

Patent metadata

Field	Value
Publication number	US-10215035-B2
Application number	US-201514974475-A
Country	US
Kind code	B2
Filing date	Dec 18, 2015
Priority date	Dec 29, 2014
Publication date	Feb 26, 2019
Grant date	Feb 26, 2019

Abstract

A wheel assembly for a gas turbine engine is disclosed. The wheel assembly includes a disk arranged for rotation about a central axis and formed to include a plurality of slots. The wheel assembly also includes a plurality of blades sized to be received in the plurality of slots so that the blades are coupled to the disk for common rotation about the central axis. The wheel assembly further includes a plurality of blade biasers positioned in the slots between the disk and the blades so that the blade biasers are engaged with the disk and the blades to preload the blades away from the central axis.

First claim

What is claimed is:

1. A wheel assembly for a gas turbine engine, the assembly comprising
a disk arranged for rotation about a central axis, the disk formed to include a plurality of slots circumferentially arranged adjacent one another,
a plurality of blades, the plurality of blades including roots sized to be received in the plurality of slots so that the plurality of blades are coupled to the disk for common rotation about the central axis, and
a plurality of blade biasers positioned in the plurality of slots between the disk and the roots of each of the plurality of blades, the blade biasers being engaged with the disk and the roots of the plurality of blades to preload the plurality of blades away from the central axis when the wheel assembly is at rest and reduce the range of centrifugal loads experienced by the disk and the plurality of blades during rotation of the wheel assembly within the gas turbine engine,
wherein the plurality of blade biasers move in an aft direction during rotation of the wheel assembly within the gas turbine engine.

2. The assembly of claim 1 , wherein the blade biasers each include (i) a wedge and (ii) a biasing element coupled to the wedge.

3. The assembly of claim 2 , wherein each of the wedges has (i) a first portion adjacent the biasing element having a first thickness and (ii) a second portion opposite the first portion having a second thickness, and each of the wedges is tapered so that the first thickness is less than the second thickness.

4. The assembly of claim 2 , wherein the biasing elements are arranged to urge the wedges to move parallel to the central axis through the slots to cause the wedges to engage the disk and the roots of each of the plurality of blades to preload the plurality of blades away from the central axis.

5. The assembly of claim 2 , wherein (i) each of the biasing elements includes a generally U-shaped spring member, and (ii) the generally U-shaped spring members of the biasing elements are positioned outside of the slots.

6. The assembly of claim 2 , further comprising a coating applied between each of the wedges and the disk to resist degradation of the wedges and the disk resulting from relative movement between the wedges and the disk parallel to the central axis during operation of the gas turbine engine.

7. The assembly of claim 2 , wherein each blade biaser is a monolithic component.

8. The assembly of claim 2 , wherein the wedge of at least one of the blade biasers comprises a pin having an elliptical cross-sectional shape.

9. The assembly of claim 8 , wherein the biasing element of the at least one of the blade biasers comprises an arm coupled to the pin.

10. A wheel assembly for a gas turbine engine, the assembly comprising
a disk arranged for rotation about a central axis, the disk formed to include a plurality of slots circumferentially arranged adjacent one another,
a plurality of blades, the plurality of blades including roots sized to be received in the plurality of slots so that the plurality of blades are coupled to the disk for common rotation about the central axis, and
a plurality of blade biasers positioned in the plurality of slots between the disk and the roots of each of the plurality of blades, the blade biasers each including (i) a wedge and (ii) a biasing element coupled to the wedge and having an arm positioned outside of the slots during operation of the gas turbine engine.

11. The assembly of claim 10 , wherein (i) each of the wedges includes a first portion and a second portion arranged closer to the biasing element than the first portion, and (ii) the first portion has a greater thickness than the second portion.

12. The assembly of claim 11 , wherein the biasing elements are arranged to urge the wedges to move parallel to the central axis through the slots to cause the first portions of the wedges to engage the disk and the roots of each of the plurality of blades.

13. The assembly of claim 10 , further comprising a coating applied between each of the wedges and the disk to resist degradation of the wedges and the disk resulting from relative movement between the wedges and the disk parallel to the central axis during operation of the gas turbine engine.

14. The assembly of claim 10 , wherein each of the wedges comprises a pin having an elliptical cross-sectional shape.

15. The assembly of claim 14 , wherein the arm is coupled to the pin.

16. A method of preloading a blade of a wheel assembly for a gas turbine engine, the method comprising
arranging a blade biaser in one of a plurality of slots formed in a disk of the wheel assembly between the disk and a root of the blade sized to be received in the one of the plurality of slots so that the blade biaser engages the disk and the root of the blade in a first position prior to operation of the wheel assembly, and
operating the wheel assembly to cause the blade to experience a centrifugal load during operation of the wheel assembly that allows the blade biaser to move in the one of the plurality of slots to engage the disk and the root of the blade in a second position different from the first position to preload the blade away from a center of the disk,
wherein operating the wheel assembly comprises rotating an oval-shaped portion of the blade biaser in the one of the plurality of slots between the first position and the second position.

17. The method of claim 16 , wherein (i) arranging the blade biaser in the one of the plurality of slots comprises arranging a first portion of the blade biaser having a first thickness in the one of the plurality of slots so that the first portion engages the disk and the root of the blade in the first position, and (ii) operating the wheel assembly comprises engaging a second portion of the blade biaser having a second thickness greater than the first thickness with the disk and the root of the blade in the second position.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Dierksmeier Douglas D
• Heffernan Tab M

Classifications

• F01D5/323

  Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor · CPC title

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• F01D5/3007 Primary

  of axial insertion type · CPC title

• F05D2240/24

  for turbines · CPC title