Tuned retention ring for rotor disk

• US 10,458,244 B2
• Filed: 10/18/2017
• Issued: 10/29/2019
• 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.
• Primary Examiner(s): Low, Lindsay M
• Assistant Examiner(s): Wang, Yi-Kai
• Application Number:
  US15/787,478
• Publication Number:
  US 20190112928A1
• Time in Patent Office: 741 Days
• Field of Search: 416220 R
• 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 dimensions of the retention ring vary circumferentially such that the retention ring is tuned to adjust a predicted modal frequency response of the rotor disk.

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

3. The rotor disk assembly of claim 2, wherein a radial thickness of the axially extending flanges is non-uniform around the retention ring.

4. The rotor disk assembly of claim 2, wherein an axial thickness of the radially extending flange is non-uniform around the retention ring.

5. The rotor disk assembly of claim 1, wherein the retention ring is configured to provide axial retention of an airfoil coupled to the rotor disk.

6. The rotor disk assembly of claim 1, wherein the retention ring is configured to provide radial retention of an airfoil coupled to the rotor disk.

7. The rotor disk assembly of claim 6, wherein the axially extending flange, wherein the retention ring further comprises a second axially extending flange.

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

9. 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 dimensions of the retention ring vary circumferentially such that the retention ring is tuned to adjust a predicted modal frequency response of the rotor disk.

10. The gas turbine engine of claim 9, wherein the retention ring is coupled to a forward side of the rotor disk.

11. The gas turbine engine of claim 9, wherein the retention ring comprises an axially extending flange and a radially extending flange.

12. The gas turbine engine of claim 11, wherein a radial thickness of the axially extending flange is non-uniform in a circumferential direction.

13. The gas turbine engine of claim 11, wherein an axial thickness of the radially extending flange is non-uniform in a circumferential direction.

14. 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 at least one of radial dimension and an axial dimension of the retention ring is non-uniform around the retention ring such that the retention ring tuned to adjust a predicted modal frequency response of the rotor disk.

15. The method of claim 14, further comprising tuning the retention ring before coupling the retention ring to the rotor disk.

16. The method of claim 15, wherein tuning the retention ring comprises varying the at least one of the radial dimensions and the axial dimension of the of the retention ring circumferentially in response to a predicted modal frequency response.

17. The method of claim 16, 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.

18. The method of claim 14, wherein coupling the retention ring to the rotor disk comprises coupling the retention ring to a forward side of the rotor disk.