Airfoil tip shroud damper
View Patent ↗A turbine disk includes a rotor and a plurality of turbine blades, each comprising a root at a proximal end secured to the rotor and a tip having a shroud at a distal end. The shroud includes a inner diameter surface, an outer diameter surface and a segmented sidewall surface separating the inner and outer diameter surfaces. The shrouds of adjacent turbine blades are separated by a tip shroud damper, and which includes a retention rail that cooperates with the outer diameter surface to maintain a positional relationship of the damper, a inner flange that engages the segmented sidewall surface, and a web that separates the retention rail and the inner flange. The tip shroud damper reduces the vibratory responses of modes involving axial and radial shroud motion to prevent high cycle fatigue (HCT).
1. A turbine, comprising:
a plurality of turbine blade tip shroud segments, each tip shroud segment having a outer wall and a inner wall; and
a damper disposed between two of the plurality of turbine blade tip shroud segments, the damper having an I-beam configuration, where a radial gap extends between an upper portion of the I-beam section and the outer walls of the two of the plurality of tip shroud segments, and where a lower portion of the I-beam section sealingly abuts the inner wall of the I-beam section, and the damper is axially conforming to the geometry of the plurality of the tip shroud segments.
2. The turbine of claim 1 , where the I-beam comprises a web that connects the upper portion and the lower portion, and the web comprises a plurality of through holes.
3. The turbine of claim 1 , where the damper comprises a unibody damper.
4. A turbine disk, comprising:
a rotor;
a plurality of turbine blades, each comprising a root at a proximal end secured to the rotor, and a tip having a shroud at a distal end, where the shroud includes a inner diameter surface, an outer diameter surface and a segmented sidewall surface separating the inner and outer diameter surfaces; and
a plurality of tip shroud dampers, where each of the plurality of dampers separate the shrouds of adjacent turbine blades, and each damper includes a retention rail that cooperates with the outer diameter surfaces to maintain a positional relationship of the tip shroud damper, an inner flange that engages the segmented sidewall surface, and a web that separates the retention rail and the inner flange.
5. The turbine disk of claim 4 , where the segmented sidewall comprises a first segment substantially perpendicular to the outer diameter surface and extending from the outer diameter surface, and a curved second segment extending from the first segment.
6. The turbine disk of claim 5 , where the inner flange comprises a first curved surface positioned adjacent to the curved second segment.
7. The turbine disk of claim 4 , where the segmented sidewall separates the inner and outer diameter surfaces, and the sidewall includes a first segment substantially perpendicular to the outer diameter surface and extending from the outer diameter surface, and a second straight segment extending from the first segment to the inner diameter surface.
8. The turbine disk of claim 7 , where the inner flange includes a flange surface substantially parallel to the second straight segment.
9. The turbine disk of claim 4 , where the segmented sidewall comprises a first segment substantially perpendicular to the outer diameter surface, and a curved second segment extending from the first segment to the inner diameter surface.
10. The turbine disk of claim 9 , where the inner flange includes a curved damper segment that extends from the web to an outer flange surface that is substantially flush with the inner diameter surfaces when the turbine disk rotates.
11. The turbine disk of claim 10 , where the curved second segment and the curved damper segment are in face-to-face contact when the disk rotates.
12. The turbine disk of claim 4 , where the segmented sidewall comprises a first segment substantially perpendicular to the outer diameter surface and extending from the outer diameter surface, a second segment substantially parallel to the outer diameter surface, and a third segment substantially parallel to the first segment and extending from the second segment to the inner diameter surface.
13. The turbine disk of claim 4 , where a first one of the plurality of dampers comprises a unibody damper having an I-beam configuration, and a radial gap extends between the outer diameter surface and the retention rail of the first one of the plurality of dampers.
14. A gas turbine engine, comprising:
a fan;
a compressor;
a combustor;
a turbine, which comprises,
a turbine disk;
a plurality of turbine blades, each comprising a root at a proximal end secured to the rotor, and a tip having a shroud at a distal end, where the shroud includes a inner diameter surface, an outer diameter surface and a segmented sidewall surface separating the inner and outer diameter surfaces; and
a plurality of tip shroud dampers, where each of the plurality of dampers separate the shrouds of adjacent turbine blades, and each damper includes a retention rail that cooperates with the outer diameter surfaces to maintain a positional relationship of the tip shroud damper, an inner flange that engages the segmented sidewall surface, and a web that separates the retention rail and the inner flange.
15. The gas turbine engine of claim 14 , where the segmented sidewall comprises a first segment substantially perpendicular to the outer diameter surface and extending from the outer diameter surface, and a curved second segment extending from the first segment.
16. The gas turbine engine of claim 14 , where the inner flange comprises a first curved surface positioned adjacent to the curved second segment.
17. The gas turbine engine of claim 14 , where the segmented sidewall separates the inner and outer diameter surfaces, and the sidewall includes a first segment substantially perpendicular to the outer diameter surface and extending from the outer diameter surface, and a second straight segment extending from the first segment to the inner diameter surface.
18. The gas turbine engine of claim 17 , where the inner flange includes a flange surface substantially parallel to the second straight segment.
19. The gas turbine engine of claim 14 , where the segmented sidewall comprises a first segment substantially perpendicular to the outer diameter surface, and a curved second segment extending from the first segment to the inner diameter surface.
20. The gas turbine engine of claim 14 , where the retention rail comprises a scalloped surface extending substantially in an axial direction.
21. The gas turbine engine of claim 20 , where the web comprises a through hole.
22. The gas turbine engine of claim 20 , where the retention rail comprises first and section parallel scalloped edges.
23. The gas turbine engine of claim 14 , where a first one of the plurality of dampers comprises a unibody damper having an I-beam configuration, and a radial gap extends between the outer diameter surface and the retention rail of the first one of the plurality of dampers.