TUNED RETENTION RING FOR ROTOR DISK

• US 20190112928A1
• Filed: 10/18/2017
• Published: 04/18/2019
• Est. Priority Date: 10/18/2017
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: TOMEO, PETER V., ANDERSON, CARNEY R.
• Granted Patent: US 10,458,244 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 11/006 Sealing the gap between rotor blades or blades and rotor
• CPC Class Codes: F01D 25/04 Antivibration arrangements
• CPC Class Codes: F01D 25/06 for preventing blade vibration means on blade-carrying members or blades F01D5/00
• CPC Class Codes: F01D 5/027 Arrangements for balancing for balancing rotating bodies in general F16F15/32; for compensating unbalance G01M1/36
• CPC Class Codes: F01D 5/10 Anti- vibration means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F01D 5/16 for counteracting blade vibration
• CPC Class Codes: F01D 5/26 Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
• CPC Class Codes: F01D 5/3015 with side plates
• CPC Class Codes: F01D 5/3023 of radial insertion type, e.g. in individual recesses
• CPC Class Codes: F01D 5/326 Locking of axial insertion type blades by other means
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F04D 29/321 for axial flow compressors
• CPC Class Codes: F04D 29/325 for axial flow fans blade mountings F04D29/34, blades F04D29/38
• CPC Class Codes: F04D 29/34 Blade mountings for axial flow compressors F04D29/322
• CPC Class Codes: F04D 29/662 Balancing of rotors compensating unbalance G01M1/36
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2260/30 Retaining components in desired mutual position
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A rotor disk assembly may include a rotor disk and a retention ring coupled to the rotor disk. Generally, the retention ring is tuned to adjust a modal frequency response of the rotor disk/rotor disk assembly. In various embodiments, dimensions of the retention ring vary circumferentially. In various embodiments, the retention ring includes an axially extending flange and a radially extending flange. A radial thickness of the axially extending flange may vary circumferentially and/or an axial thickness of the radially extending flange may vary circumferentially.

Claims

1. A rotor disk assembly comprising:

a rotor disk; and

a retention ring coupled to the rotor disk, wherein the retention ring is tuned to adjust a modal frequency response of the rotor disk.

2. The rotor disk assembly of claim 1, wherein dimensions of the retention ring vary circumferentially.

3. The rotor disk assembly of claim 1, wherein the retention ring comprises an axially extending flange and a radially extending flange.

4. The rotor disk assembly of claim 3, wherein a radial thickness of the axially extending flange varies circumferentially.

5. The rotor disk assembly of claim 3, wherein an axial thickness of the radially extending flange varies circumferentially.

6. The rotor disk assembly of claim 3, wherein the radially extending flange is configured to provide axial retention of an airfoil coupled to the rotor disk.

7. The rotor disk assembly of claim 3, wherein the axially extending flange is configured to provide radial retention of an airfoil coupled to the rotor disk.

8. The rotor disk assembly of claim 7, wherein the axially extending flange is a first axially extending flange comprising a first axially extending surface configured to engage the airfoil to provide radial retention, wherein the retention ring further comprises a second axially extending flange comprising a second axially extending surface configured to engage the airfoil to provide radial retention.

9. The rotor disk assembly of claim 1, wherein the retention ring is an integral hoop.

10. A gas turbine engine comprising:

a rotor disk comprising an airfoil coupled to the rotor disk; and

a retention ring coupled to the rotor disk, wherein the retention ring is tuned to adjust a modal frequency response of the rotor disk.

11. The gas turbine engine of claim 10, wherein the retention ring is coupled to a forward side of the rotor disk.

12. The gas turbine engine of claim 10, wherein dimensions of the retention ring vary circumferentially.

13. The gas turbine engine of claim 10, wherein the retention ring comprises an axially extending flange and a radially extending flange.

14. The gas turbine engine of claim 13, wherein a radial thickness of the axially extending flange varies circumferentially.

15. The gas turbine engine of claim 13, wherein an axial thickness of the radially extending flange varies circumferentially.

16. A method of manufacturing a gas turbine engine, the method comprising:

coupling an airfoil to a rotor disk; and

coupling a retention ring to the rotor disk, wherein the retention ring is tuned to adjust a modal frequency response of the rotor disk.

17. The method of claim 16, further comprising tuning the retention ring before coupling the retention ring to the rotor disk.

18. The method of claim 17, wherein turning the retention ring comprises varying dimensions of the of the retention ring circumferentially in response to a predicted modal frequency response.

19. The method of claim 18, wherein coupling the retention ring to the rotor disk comprises aligning the retention ring with the rotor disk in response to the predicted modal frequency response.

20. The method of claim 16, wherein coupling the retention ring to the rotor disk comprises coupling the retention ring to a forward side of the rotor disk.