Blade damper and method for making same

• US 6,354,803 B1
• Filed: 06/30/2000
• Issued: 03/12/2002
• Est. Priority Date: 06/30/2000
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Grover, Garth Kneeland, Liotta, Gary Charles
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): EDGAR, RICHARD A
• Application Number:
  US09/607,750
• Time in Patent Office: 620 Days
• Field of Search: 415/119, 416/190, 416/193.A, 416/500, 416/1, 277/491, 277/411, 277/531, 277/433, 188/378, 298/892, 298/892.1, 298/897.1
• US Class Current: 416/190
• CPC Class Codes: F01D 11/006 Sealing the gap between rotor blades or blades and rotor
• 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: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10S 416/50 Vibration damping features
• CPC Class Codes: Y10T 29/49321 Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
• CPC Class Codes: Y10T 29/49337 Composite blade

Abstract

A turbine engine blade damper for damping vibrations of blades in a turbine engine. The blade damper includes an elongate body extending between a forward end and a rearward end opposite the forward end. The body is sized and shaped for receipt within a gap formed between adjacent platforms of the blades so the body frictionally engages the adjacent platforms to dampen vibrations of the blades and to prevent air from passing through the corresponding gap during engine operation. The damper also includes a retainer mounted on at least one of the forward and rearward ends of the body. The retainer is sized and shaped for receipt within a recess formed in at least one of the adjacent blades to hold the body between the blades. The retainer is sized and shaped to prevent air from passing between the blades and the retainer during engine operation.

Claims

1. A turbine engine blade damper for damping vibrations of blades in a turbine engine, said blade damper comprising:

an elongate body extending between a forward end and a rearward end opposite said forward end, the body being sized and shaped for receipt within a gap formed between adjacent platforms of the blades so that the body frictionally engages said adjacent platforms to dampen vibrations of said blades and to prevent air from passing through said gap during engine operation; and

a retainer mounted on at least one of said forward end and said rearward end of the body, the retainer being sized and shaped for receipt within a recess formed in at least one of the adjacent blades to hold the body between the blades, said retainer being sized and shaped to prevent air from passing between the blades and the retainer during engine operation.

2. A damper as set forth in claim 1 wherein said retainer is a forward retainer mounted on said forward end of the body and the damper further comprises a rearward retainer mounted on said rearward end of the body, the rearward retainer being sized and shaped for receipt within a recess formed in at least one of the adjacent blades to hold the body between the blades, said rearward retainer being sized and shaped to prevent air from passing between the blades and said rearward retainer during engine operation.

3. A damper as set forth in claim 1 wherein the body is a wire.

4. A damper as set forth in claim 3 wherein the wire is cylindrical.

5. A damper as set forth in claim 4 wherein the wire has a diameter greater than a width of the gap formed between adjacent platforms of the blades.

6. A damper as set forth in claim 1 wherein the retainer is cylindrical.

7. A damper as set forth in claim 1 wherein the body has a central axis and the retainer is offset from said central axis.

8. A damper as set forth in claim 7 wherein the retainer is angled with respect to the central axis of the body.

9. A damper as set forth in claim 1 wherein the body has a length generally equal to the platforms of the blades.

10. A method of manufacturing a turbine engine blade damper for damping vibrations of blades in a turbine engine, said method comprising the steps of

cutting a wire to a length corresponding to a groove formed in a blade platform with which the damper is to be used;

and

attaching a retainer to an end of the wire.

11. A method as set forth in claim 10 further comprising the step of forming the cut wire to a shape corresponding to the groove.

12. A method as set forth in claim 10 wherein the step of attaching the retainer is performed by swaging the retainer onto the wire.

13. A turbine engine comprising:

a disk having a generally circular periphery;

a plurality of blades mounted about the periphery of the disk, each of said blades including an airfoil extending outward from a platform; and

a damper for damping vibrations of said plurality of blades, the damper including an elongate body extending between a forward end and a rearward end opposite said forward end, the body being sized and shaped for receipt within a gap formed between adjacent platforms of said plurality of blades so that the body frictionally engages said adjacent platforms to dampen vibrations of said blades and to prevent air from passing through said gap during engine operation, the damper having a retainer mounted on at least one of said forward end and said rearward end, the retainer being sized and shaped for receipt within a recess formed in at least one of the adjacent blades to hold the damper between the blades, said retainer preventing air from passing between the blades and the retainer during engine operation.

14. An engine as set forth in claim 13 wherein the platform of each of said plurality of blades has a suction side and a pressure side, and wherein one of said suction side and said pressure side extends radially.

15. An engine as set forth in claim 14 wherein said suction side extends radially.