Vibration damper

• US 8,322,990 B2
• Filed: 07/06/2009
• Issued: 12/04/2012
• Est. Priority Date: 08/01/2008
• Status: Expired due to Fees

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Hunt, David J., Pearce, Wesley J., Elliott, Robert
• Primary Examiner(s): Kershteyn, Igor
• Assistant Examiner(s): Legendre, Christopher R
• Application Number:
  US12/458,241
• Publication Number:
  US 20100028135A1
• Time in Patent Office: 1,247 Days
• Field of Search: 415/119, 416/500, 416/190, 416/119.R, 416/193.A, 416/193.R, 416/220.R, 416/119
• US Class Current: 416/119
• CPC Class Codes: F01D 25/06 for preventing blade vibration means on blade-carrying members or blades F01D5/00
• CPC Class Codes: F01D 5/10 Anti- vibration means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F01D 5/22 Blade-to-blade connections, e.g. for damping vibrations
• 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: F05D 2260/96 Preventing, counteracting or reducing vibration or noise

Abstract

A vibration damper (28) is disclosed for use in a turbomachine, the turbomachine comprising at least one turbine rotor (19) having a plurality of radially extending blades (16, 17). Each blade has an aerofoil (22), a platform (21) and a stem (20). The vibration damper (28) has a seal-region (29) which comprises a pair of sealing surfaces (24, 25) configured for engagement with respective contact surfaces (24, 25) provided on adjacent blade platforms (21). The vibration damper (28) also has a mass-region (30) which is configured to extend radially inwardly from the seal-region (29) and to terminate at a position located between adjacent blade stems (20) (FIG. 4).

Claims

1. A vibration damper for use in a turbomachine having at least one turbine rotor, the at least one turbine rotor having a plurality of radially extending blades, each blade including an aerofoil, a platform located radially inwardly of the aerofoil, and a stem located radially inwardly of the platform, the vibration damper comprising:

a seal-region comprising a pair of sealing surfaces configured for engagement with respective contact surfaces provided on adjacent blade platforms; and

a mass-region configured to extend radially inwardly from the seal-region and to terminate at a position located between adjacent blade stems, wherein

the seal-region is shaped such that;

i) a first one of the pair of sealing surfaces lies in a substantially radial plane relative to the rotor, for engagement with a radial contact surface on one of the adjacent blade platforms, and ii) said sealing surfaces converge in a radially outward direction relative to the rotor, for engagement with similarly converging contact surfaces on the adjacent blade platforms,

the platform of each rotor blade comprises a projection located substantially radially inwardly of a second contact surface to define a recess between the second contact surface and the projection,

the seal-region defines a stepped region,

a portion of the seal-region and the stepped region is positioned within the recess,

the mass-region is shaped such that the mass-region has a greater mass on a side of the damper having the stepped region than on an adjacent side of the mass-region away from the stepped region, and

the side of the mass-region having a greater mass is positioned radially below the recess.

2. The vibration damper according to claim 1, wherein said mass-region is generally elongate in form.

3. The vibration damper according to claim 1, wherein said mass-region has a relatively narrow section adjacent said seal-region, and a relatively large section radially inwardly thereof.

4. The vibration damper according to claim 1, having a centre-of-gravity located substantially within, or generally adjacent, to said mass-region.

5. The vibration damper according to claim 1, wherein said sealing surfaces make an acute angle to one another.

6. The vibration damper according to claim 1, configured so as to have a mass-distribution such that a line of centrifugal force, acting upon the damper during rotation of the rotor, passes through a mid-chord region of the second of said pair of sealing surfaces.

7. The vibration damper according to claim 1, wherein said portion of said seal-region and said stepped region are configured for loose engagement within said recess for retention when centrifugal forces acting on the vibration damper are insufficient to urge the seal-surfaces into engagement with the contact surfaces.

8. A turbomachine comprising:

at least one turbine rotor having a plurality of radially extending turbine blades, each blade including;

an aerofoil,

a platform located radially inwardly of the aerofoil, and

a stem located radially inwardly of the platform, and

a plurality of vibration dampers comprising;

a seal-region comprising a pair of sealing surfaces configured for engagement with respective contact surfaces provided on adjacent blade platforms; and

a mass-region configured to extend radially inwardly from the seal-region and to terminate at a position located between adjacent blade stems, wherein

the seal-region is shaped such that a first one of the pair of sealing surfaces lies in a substantially radial plane relative to the rotor, for engagement with a radial contact surface on one of the adjacent blade platforms, and

the platform of each rotor blade comprises a projection located substantially radially inwardly of a second contact surface to define a recess between the second contact surface and the projection,

the seal-region defining a stepped region,

a portion of the seal-region and the stepped region being positioned within the recess,

the mass-region being shaped such that the mass-region has a greater mass on a side of the damper having the stepped region than on an adjacent side of the mass-region away from the stepped region,

the side of the mass-region having a greater mass is positioned radially below the recess, and

the plurality of vibration dampers are configured so as to have a mass-distribution such that a line of centrifugal force, acting upon each vibration damper during rotation of the rotor, passes through a mid-chord region of the second of said pair of sealing surfaces.

9. The turbomachine according to claim 8, wherein

the platform is configured to define a first contact surface to one side of the aerofoil, a second contact surface to the opposite side of the aerofoil,

the first contact surface lies in a substantially radial plane relative to the rotor,

the second contact surface lies in a plane making an acute angle to the radial plane, and

the aerofoil has a suction side and a pressure side.

10. The turbomachine according to claim 9, wherein said first contact surface is provided on the suction side of the aerofoil, and said second contact face is provided on the pressure side of the aerofoil.

11. The turbomachine according to claim 9, wherein each damper is provided such that the seal-region of each damper is located substantially within a space defined between the first contact surface of one blade and the second contact surface of an adjacent blade.

12. The turbomachine according to claim 8, wherein the plurality of vibration dampers are arranged between adjacent turbine blades of the plurality of radially extending turbine blades.