DAMPER FOR AN INTEGRALLY BLADED ROTOR

• US 20130004313A1
• Filed: 06/28/2011
• Published: 01/03/2013
• Est. Priority Date: 06/28/2011
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: El-Aini, Yehia M., Davis, Gary A.
• Granted Patent: US 9,151,170 B2
• Time in Patent Office: Days
• US Class Current: 416/134.R
• CPC Class Codes: F01D 5/10 Anti- vibration means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/34 Rotor-blade aggregates of unitary construction , e.g. formed of sheet laminae; discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2250/75 given by its similarity to a letter, e.g. T-shaped
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise

Abstract

A Rotor includes a disk having a rim with an axial face, the rim defines a circumferential groove. A damper engaged with the rim at both the axial face and the circumferential groove.

Claims

1. A rotor comprising:

a disk having a rim, said rim having an axial face facing one of a forward or rearward direction, said rim defines a circumferential groove; and

a damper engaged with said rim at both said axial face and said circumferential groove.

2. The rotor as recited in claim 1, wherein said axial face is a front face.

3. The rotor as recited in claim 1, wherein said axial face is a rear face.

4. The rotor as recited in claim 1, wherein said damper is a split ring damper that is U-shaped in cross section.

25. The rotor as recited in claim 1, wherein said disk includes a rotor hub having a hub inner surface facing a longitudinal axis about which said rotor hub rotates and said rim being spaced radially outwardly relative to said hub inner surface, and wherein said axial face extends radially inwardly from said rim to said hub inner surface.

26. The rotor as recited in claim 25, wherein said circumferential groove is formed within said hub inner surface, and wherein said damper comprises a split ring damper with a first leg mounted within said circumferential groove and a second leg that extends from said first leg, surrounds a radial lip of said hub inner surface, and extends radially outwardly to contact said axial face.

5. An integrally bladed rotor comprising:

a rotor hub that defines a hub face facing one of a forward or rearward direction and a hub inner surface with a circumferential groove within said hub inner surface; and

a split ring damper mounted within said circumferential groove and in contact with said hub face.

6. The integrally bladed rotor as recited in claim 5, wherein said split ring includes a first leg and a second leg, said first leg engaged within said circumferential groove and said second leg in contact with said hub face.

7. The integrally bladed rotor as recited in claim 6, wherein said first leg includes a multiple of scallops.

8. The integrally bladed rotor as recited in claim 6, wherein said first leg includes a multiple of lightening apertures.

9. The integrally bladed rotor as recited in claim 6, wherein said second leg includes a multiple of radial slits.

10. The integrally bladed rotor as recited in claim 6, further comprising a hub rim opposite said hub inner surface, a multiple of airfoils integral with said hub rim.

11. The integrally bladed rotor as recited in claim 6, wherein said split ring damper defines a coefficient of friction in the range of 0.20 to 0.60.

27. The integrally bladed rotor as recited in claim 5, wherein said hub inner surface faces a longitudinal center axis about which said rotor hub rotates and wherein rotor hub includes an outer hub rim that is spaced radially outwardly relative to said hub inner surface, said outer hub rim supporting a plurality of airfoils, and wherein said hub face extends radially inwardly from said outer hub rim to said hub inner surface.

28. The integrally bladed rotor as recited in claim 27, wherein said circumferential groove is formed within said hub inner surface, and wherein said split ring damper includes a first leg mounted within said circumferential groove and a second leg that extends from said first leg, surrounds a radial lip of said hub inner surface, and extends radially outwardly to contact said hub face.

29. The integrally bladed rotor as recited in claim 27 wherein said hub face comprises a front face facing the forward direction.

30. The integrally bladed rotor as recited in claim 27 wherein said hub face comprises a rear face facing the rearward direction.

12-16. -16. (canceled)

17. An integrally bladed rotor comprising:

a rotor hub that defines a hub face facing one of a forward or rearward direction and a hub rim transverse to said hub face;

a multiple of airfoils integral with said hub rim; and

a split ring damper mounted to said rotor hub and including a portion in contact with said hub face.

18. The integrally bladed rotor as recited in claim 17, wherein said split ring damper is mounted within a circumferential groove within a hub inner surface generally opposite said hub rim.

19. The integrally bladed rotor as recited in claim 18, wherein said split ring includes a first leg and a second leg, said first leg engaged within said circumferential groove and said second leg in contact with said hub face.

21. The integrally bladed rotor as recited in claim 17, wherein said rotor hub comprises a hub inner surface facing a longitudinal axis about which said rotor hub rotates and said hub rim being spaced radially outwardly relative to said hub inner surface, and wherein said hub face extends radially inwardly from said hub rim to said hub inner surface.

22. The integrally bladed rotor as recited in claim 21, wherein said hub face comprises a front face of said rotor hub and faces the forward direction.

23. The integrally bladed rotor as recited in claim 21, wherein said hub face comprises a rear face of said rotor hub and faces the rearward direction.

24. The integrally bladed rotor as recited in claim 21, including a circumferential groove formed within said hub inner surface, and wherein said split ring damper includes a first leg mounted within said circumferential groove and a second leg that extends from said first leg to surround a radial lip of said hub inner surface and to contact said hub face.

20. (canceled)