Granted Patent B2

US 12,366,171 · App. 18/202,506 · Granted Jul 22, 2025

Inventors: Vaishnav Raghuvaran (Bangalore, IN); Bhaskar Nanda Mondal (Bangalore, IN); Gary W. Bryant (Loveland, OH)

Assignee: General Electric Company

F01D5/3007F01D5/021F05D2220/36F05D2240/24F05D2250/712

Abstract

Claims (24)

1. A rotor disk for a gas turbine engine, the rotor disk comprising:

a disk body comprising disk posts extending in a radial direction from a central region of the disk body, the disk posts comprising disk post pressure surfaces that define a first array of dovetail recesses;

disk inserts retained within the first array of dovetail recesses, the disk inserts comprising disk insert pressure surfaces that define a second array of dovetail recesses; and

blades retained within the second array of dovetail recesses;

wherein the disk inserts each comprise an outer dovetail portion that includes an outer pair of the disk insert pressure surfaces and an inner dovetail portion that includes an inner pair of the disk insert pressure surfaces, the outer dovetail portion and the inner dovetail portion connected by a disk insert neck of reduced circumferential dimension compared to the outer and inner dovetail portions;

wherein the inner dovetail portion and disk insert neck of each disk insert are configured such that centrifugal force acting on the rotor disk during operation of the rotor disk moves each disk insert to a radially outermost position providing a disk insert gap between each disk insert and a central region of the disk body and the disk post pressure surfaces and the disk insert pressure surfaces are configured such that the disk insert neck from the inner dovetail portion to the outer dovetail portion is located entirely radially outside the respective one of the first array of dovetail recesses with the disk inserts in the radially outermost position, where, in the radially outermost position, the disk insert pressure surfaces are positioned such that a radial offset is provided between each disk post and each blade opening a blade gap between each disk post and each blade due to the centrifugal force.

2. The rotor disk of claim 1 , wherein the blades are circumferentially aligned with the disk posts.

3. The rotor disk of claim 1 , wherein the disk inserts comprise a first material and the disk posts comprise a second material different from the first material.

4. The rotor disk of claim 1 , wherein the disk inserts comprise a first disk insert and a second disk insert in slidable contact with the first disk insert.

5. The rotor disk of claim 4 , wherein:

the first disk insert comprises a first side surface;

the second disk insert comprises a second side surface; and

the first side surface is in slidable contact with the second side surface.

6. The rotor disk of claim 5 , wherein the first side surface and the second side surface are aligned with the radial direction.

7. The rotor disk of claim 1 , wherein the disk body is made from a first material and the disk inserts are made from a second material different from the first material.

8. The rotor disk of claim 1 , wherein the disk insert pressure surfaces of the disk inserts comprise outer pressure surfaces and inner pressure surfaces, wherein the outer pressure surfaces define a concave shape within the disk inserts.

9. The rotor disk of claim 1 , wherein the disk insert pressure surfaces of the disk inserts comprise outer pressure surfaces and inner pressure surfaces, wherein the inner pressure surfaces define a concave shape within the disk inserts.

10. The rotor disk of claim 1 , wherein the disk inserts are configured to move in the dovetail recesses during a fan blade out event.

11. A rotor disk for a gas turbine engine, the rotor disk comprising:

rotational support means comprising disk posts extending in a radial direction, the disk posts comprising disk post pressure surfaces that define a first array of dovetail recesses; and

insert means for retaining blades within a second array of dovetail recesses;

wherein the insert means comprises disk inserts retained within the first array of dovetail recesses, the disk inserts defining the second array of dovetail recesses;

wherein the disk inserts each comprise an outer dovetail portion that includes an outer pair of the disk insert pressure surfaces and an inner dovetail portion that includes an inner pair of the disk insert pressure surfaces, the outer dovetail portion and the inner dovetail portion connected by a disk insert neck of reduced circumferential dimension compared to the outer and inner dovetail portions, wherein the inner dovetail portion and disk insert neck of each disk insert being are configured such that centrifugal force acting on the rotor disk during operation of the rotor disk moves each disk insert to a radially outermost position providing a disk insert gap between each disk insert and a central region of the disk body and the disk post pressure surfaces and the disk insert pressure surfaces are configured such that the disk insert neck from the inner dovetail portion to the outer dovetail portion is located entirely radially outside the respective one of the first array of dovetail recesses with the disk inserts in the radially outermost position, where, in the radially outermost position, the disk insert pressure surfaces are positioned such that a radial offset is provided between each disk post and each blade opening a blade gap between each disk post and each blade due to the centrifugal force.

12. The rotor disk of claim 11 , wherein the disk inserts comprise a first material and the disk posts comprise a second material different from the first material.

Assignments (1)

Continuity (1)

References Cited (17)