Damper pin for a turbine blade

Abstract

A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially spaced from a second end portion and a spring member that extends axially from an inner surface of the first end portion to an inner surface of the second end portion. The first end portion, the spring member and the second end portion define a generally arcuate top portion of the damper pin. The top portion is configured to contact with a groove defined between the adjacent turbine blades.

What is claimed is: 
     
       1. A damper pin for damping adjacent turbine blades coupled to a rotor shaft, the damper pin comprising:
 a first end portion axially aligned with and axially spaced from a second end portion; 
 a spring member that extends axially from an inner surface of the first end portion to an inner surface of the second end portion, wherein the first end portion, the spring member and the second end portion define a generally arcuate top portion of the damper pin configured to contact with a groove defined between the adjacent turbine blades, 
 a retention pin coaxially aligned with and disposed between the first end portion and the second end portion, wherein the spring member extends circumferentially around the retention pin, and wherein the retention pin is seated within an opening defined by the first end portion or the second end portion. 
 
     
     
       2. The damper pin as in  claim 1 , wherein the spring member is helical shaped. 
     
     
       3. The damper pin as in  claim 1 , wherein the spring member is connected to at least one of the inner surface of the first end portion or the inner surface of the second end portion. 
     
     
       4. The damper pin as in  claim 1 , wherein the spring member comprises a first spring coaxially aligned with a second spring. 
     
     
       5. The damper pin as in  claim 4 , wherein the first spring is connected at one end to the first end portion and the second spring is connected at one to the second end portion. 
     
     
       6. The damper pin as in  claim 1 , wherein a portion of the first end portion is semi-cylindrical. 
     
     
       7. The damper pin as in  claim 1 , wherein a portion of the second end portion is semi-cylindrical. 
     
     
       8. A turbine engine, comprising:
 a rotor shaft that extends axially within the turbine engine; 
 an adjacent pair of turbine blades coupled to the rotor shaft, each turbine blade at least partially defining a groove that extends along a slash face of the corresponding turbine blade; and 
 a damper pin disposed within the groove, the damper pin comprising: 
 a first end portion axially aligned with and axially spaced from a second end portion; 
 a spring member that extends axially from an inner surface of the first end portion to an inner surface of the second end portion, wherein the first end portion, the spring member and the second end portion define a generally arcuate top portion of the damper pin configured to contact with the groove defined between the adjacent turbine blades, 
 a retention pin coaxially aligned with and disposed between the first end portion and the second end portion, wherein the spring member extends circumferentially around the retention pin, and wherein the retention pin is seated within an opening defined by the first end portion or the second end portion. 
 
     
     
       9. The turbine engine as in  claim 8 , wherein the spring member is helical shaped. 
     
     
       10. The turbine engine as in  claim 8 , wherein the spring member is connected to at least one of the inner surface of the first end portion or the inner surface of the second end portion. 
     
     
       11. The turbine engine as in  claim 8 , wherein the spring member comprises a first spring coaxially aligned with a second spring. 
     
     
       12. The turbine engine as in  claim 11 , wherein the first spring is connected at one end to the first end portion and the second spring is connected at one to the second end portion. 
     
     
       13. The turbine engine as in  claim 8 , wherein a portion of the first end portion is semi-cylindrical. 
     
     
       14. The turbine engine as in  claim 8 , wherein a portion of the second end portion is semi-cylindrical.