Turbine blade with friction and impact vibration damping elements
A turbine blade includes an airfoil body having an outer tip and a platform; and a part-span shroud positioned between the outer tip and the platform of the airfoil body. The part-span shroud has a first opening extending through the airfoil body and having a first inner surface. The airfoil body includes a second opening extending radially from the first opening and having a second inner surface. A first elongated vibration-damping element is disposed in the first opening, and a second elongated vibration-damping element disposed radially in the second opening. The second elongated vibration-damping element includes a free radially outer end and a radially inner end coupled to the first elongated vibration-damping element. The first elongated vibration-damping element frictionally damps vibration, and the second elongated vibration-damping element damps vibration using impact within the second opening.
1. A turbine blade, comprising:
an airfoil body having an outer tip and a platform;
a part-span shroud positioned between the outer tip and the platform of the airfoil body, the part-span shroud having a first opening having a first inner surface, the first opening extending through the airfoil body;
a second opening in the airfoil body extending radially outward from the first opening and having a second inner surface;
a first elongated vibration-damping element disposed in the first opening; and
a second elongated vibration-damping element disposed radially in the second opening, the second elongated vibration-damping element including a free radially outer end and a radially inner end coupled to the first elongated vibration-damping element.
2. The turbine blade of claim 1 , wherein the first elongated vibration-damping element engages at least a portion of the first inner surface of the first opening, allowing the first elongated vibration-damping element to damp vibrations through frictional engagement with the first inner surface of the first opening.
3. The turbine blade of claim 1 , wherein the second opening has a dimension greater than a corresponding outer dimension of the second elongated vibration-damping element, allowing the second elongated vibration-damping element a limited movement range within the second opening for damping vibrations through impact with the second inner surface of the second opening.
4. The turbine blade of claim 3 , wherein the first elongated vibration-damping element engages at least a portion of the first inner surface of the first opening, allowing the first elongated vibration-damping element to damp vibrations through frictional engagement with the first inner surface of the first opening.
5. The turbine blade of claim 1 , wherein the airfoil body includes an internal wall defining an elongated internal cavity extending inwardly from the outer tip of the airfoil body, and wherein the second opening extends radially within the internal wall.
6. The turbine blade of claim 1 , wherein the first elongated vibration-damping element and the second elongated vibration-damping element collectively have an upside-down T shape in the airfoil body.
7. The turbine blade of claim 1 , wherein the radially inner end of the second elongated vibration-damping element is threadably coupled in an opening in the first elongated vibration-damping element.
8. The turbine blade of claim 1 , wherein the part-span shroud is positioned more than half way radially outward on the airfoil body from the platform.
9. The turbine blade of claim 1 , wherein the second opening has a circular cross-sectional shape; and wherein the second damping element has a cross-sectional shape selected from the group consisting of a circle, an ellipse having a major and a minor axis of different lengths, and a polygon.
10. An article, comprising:
an airfoil body having an outer tip and a platform;
a part-span shroud positioned between the outer tip and the platform of the airfoil body, the part-span shroud having a first opening having a first inner surface, the first opening extending through the airfoil body;
a first elongated vibration-damping element disposed in the first opening and frictionally engaging the first inner surface for frictionally damping vibrations; and
a second elongated vibration-damping element disposed radially in a second opening in the airfoil body, the second elongated vibration-damping element having a radially inner end coupled to the first elongated vibration-damping element and a free radially outer end for damping vibrations by impacting a second inner surface of the second opening.
11. The article of claim 10 , wherein the second opening has a dimension greater than a corresponding outer dimension of the second elongated vibration-damping element, allowing the second elongated vibration-damping element a limited movement range within the second opening for damping vibrations by impacting the second inner surface of the second opening.
12. The article of claim 10 , wherein the airfoil body includes an internal wall defining an elongated internal cavity extending inwardly from the outer tip of the airfoil body, and wherein the second opening extends radially within the internal wall.
13. The article of claim 10 , wherein the first elongated vibration-damping element and the second elongated vibration-damping element collectively have an upside-down T shape in the airfoil body.
14. The article of claim 10 , wherein the radially inner end of the second elongated vibration-damping element is threadably coupled in an opening in the first elongated vibration-damping element.
15. The article of claim 10 , wherein the part-span shroud is positioned more than half way radially outward on the airfoil body from the platform.
16. The article of claim 10 , wherein the second opening has a circular cross-sectional shape; and wherein the second damping element has a cross-sectional shape selected from the group consisting of a circle, an ellipse having a major and a minor axis of different lengths, and a polygon.
17. The article of claim 10 , wherein the article includes a turbine blade in a turbine.
18. A method of damping vibration in a turbine blade, the method comprising:
damping vibration by friction in a part-span shroud positioned between an outer tip and a platform of an airfoil body of the turbine blade, the part-span shroud having a first opening having a first inner surface and a first elongated vibration-damping element disposed in the first opening and frictionally engaging the first inner surface; and
damping vibration by impact of a second elongated vibration-damping element disposed radially in a second opening in the airfoil body, the second elongated vibration-damping element having a radially inner end coupled to the first elongated vibration-damping element and a radially outer end capable of damping vibrations by impacting with an inner surface of the second opening.
19. The method of claim 18 , wherein the airfoil body includes an internal wall defining an elongated internal cavity extending inwardly from the outer tip of the airfoil body, and wherein the second opening extends radially within the internal wall.
20. The method of claim 18 , wherein the first elongated vibration-damping element and the second elongated vibration-damping element collectively have an upside-down T shape in the airfoil body.