초록 ▼

A turbine blade includes an airfoil, platform, shank, and dovetail integrally joined together. A cooling chamber is located under the platform and has a portal exposed outwardly from the shank. A damper seat surrounds the portal and is recessed under the platform for receiving a vibration damper to

A turbine blade includes an airfoil, platform, shank, and dovetail integrally joined together. A cooling chamber is located under the platform and has a portal exposed outwardly from the shank. A damper seat surrounds the portal and is recessed under the platform for receiving a vibration damper to sealingly close the chamber across the portal.

대표청구항 ▼

Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims in which we claim: 1. A turbine blade comprising: an airfoil, platform, shank, and dovetail integrally joined longitudinally together; a platform

Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims in which we claim: 1. A turbine blade comprising: an airfoil, platform, shank, and dovetail integrally joined longitudinally together; a platform cooling chamber disposed under said platform and having a portal exposed outwardly from said shank; a damper seat recessed under said platform and surrounding said portal; and a damper disposed adjacent said seat to sealingly close said chamber across said portal. 2. A blade according to claim 1 further comprising: a forward skirt integrally joined to said shank and platform at forward ends thereof; an aft skirt integrally joined to said shank and platform at aft ends thereof, and said chamber is spaced between said skirts to bridge said seat across opposite ends of said portal; and a pair of ledges integrally joined to respective ones of said forward and aft skirts and said shank, and spaced below said platform and portal for supporting said damper adjacent said portal. 3. A blade according to claim 2 wherein said seat is inclined outwardly from said shank to said platform for frictionally supporting said damper at a corresponding inclination angle under centrifugal force. 4. A blade according to claim 3 wherein: said platform terminates at a splitline spaced outwardly from said airfoil; said chamber includes a floor extending outwardly from said shank; and said seat bridges said floor and said platform at said splitline to surround said chamber around said portals. 5. A blade according to claim 4 wherein said airfoil includes opposite pressure and suction sides extending in span from a root at said platform to an opposite tip, and extending in chord between opposite leading and trailing edges, and said chamber extends under said platform outwardly from said airfoil pressure side. 6. A blade according to claim 5 wherein said seat is flat around said portal and is inclined inwardly from said splitline over said ledges to said shank, and provides a perimeter border to frictionally engage said damper to seal closed said chamber. 7. A blade according to claim 6 wherein said platform includes a plurality of film cooling hole outlets extending therethrough in flow communication with said platform chamber. 8. A blade according to claim 7 wherein: said airfoil is hollow and includes a cooling circuit extending through said platform and shank; and said shank includes an aperture inlet extending in flow communication between said cooling circuit and said platform chamber. 9. A blade according to claim 7 wherein said chamber is imperforate except at said portal, and said damper is perforate for channeling cooling air into said chamber. 10. A blade according to claim 7 wherein: said chamber is imperforate except at said portal and said forward skirt; and said forward skirt includes an aperture inlet extending therethrough in flow communication with said chamber adjacent said adjoining ledge. 11. A turbine blade comprising: an airfoil, platform, shank, and dovetail integrally joined longitudinally together; a platform cooling chamber disposed under said platform and having a portal exposed outwardly from said shank; and a damper seat recessed under said platform and surrounding said portal for receiving a vibration damper to sealingly close said chamber across said portal. 12. A blade according to claim 11 wherein said seat is inclined outwardly from said shank to said platform for frictionally supporting said damper at a corresponding inclination angle under centrifugal force. 13. A blade according to claim 12 further comprising: a forward skirt integrally joined to said shank and platform at forward ends thereof; an aft skirt integrally joined to said shank and platform at aft ends thereof; and said chamber is spaced between said skirts to bridge said seat across opposite ends of said portal. 14. A blade according to claim 13 wherein: said platform terminates at a splitline spaced outwardly from said airfoil; said chamber includes a floor extending outwardly from said shank; and said seat bridges said floor and said platform at said splitline to surround said chamber around said portal. 15. A blade according to claim 14 further comprising a pair of ledges integrally joined to respective ones of said forward and aft skirts and said shank, and spaced below said platform and portal for supporting said damper adjacent said portal. 16. A blade according to claim 15 wherein said airfoil includes opposite pressure and suction sides extending in span from a root at said platform to an opposite tip, and extending in chord between opposite leading and trailing edges, and said chamber extends under said platform outwardly from said airfoil pressure side. 17. A blade according to claim 16 wherein said seat is flat around said portal and provides a perimeter border to frictionally engage said damper to seal closed said chamber. 18. A blade according to claim 17 wherein said seat is straight in height across said portal. 19. A blade according to claim 17 wherein said seat is convex along said splitline and floor between said forward and aft skirts. 20. A blade according to claim 17 wherein said platform includes a plurality of film cooling hole outlets extending therethrough in flow communication with said platform chamber. 21. A blade according to claim 20 wherein: said airfoil is hollow and includes a cooling circuit extending through said platform and shank; and said shank includes an aperture inlet extending in flow communication between said cooling circuit and said platform chamber. 22. A blade according to claim 21 further comprising said damper being disposed between said ledges and platform, and covering said portal to close said chamber. 23. A blade according to claim 22 wherein said damper is imperforate. 24. A blade according to claim 23 wherein said damper comprises a pair of wedges integrally joined together by a damper plate therebetween, and said wedges are disposed atop said ledges, and said plate covers said portal for sealing closed said platform chamber. 25. A blade according to claim 24 wherein said damper further comprises a ridge integrally joining together said wedges along said damper plate to form a solid apex being complementary to said chamber floor along said portal. 26. A blade according to claim 25 wherein said damper further comprises an integral rib extending outwardly from said ridge along said damper plate. 27. A blade according to claim 20 wherein said chamber is imperforate at said shank. 28. A blade according to claim 27 further comprising said damper being disposed between said ledges and platform, and covering said portal to close said chamber. 29. A blade according to claim 28 wherein said chamber is imperforate except at said portal, and said damper is perforate for channeling cooling air into said chamber. 30. A blade according to claim 28 wherein said damper plate includes a plurality of impingement holes facing inwardly through the underside of said platform for channeling said cooling air in impingement cooling thereof. 31. A blade according to claim 27 wherein said chamber is imperforate except at said portal and said forward skirt. 32. A blade according to claim 31 wherein said forward skirt includes an aperture inlet extending therethrough in flow communication with said chamber adjacent said adjoining ledge. 33. A blade according to claim 32 further comprising said damper being disposed between said ledges and platform, and covering said portal to close said chamber. 34. A blade according to claim 33 wherein said damper is imperforate. 35. A turbine blade damper comprising: a pair of wedges integrally joined together by a thinner damper plate therebetween to define a hollow cavity behind said plate; and a common ridge integrally joining together said wedges along said damper plate to form an evenly smooth apex therebetween. 36. A damper according to claim 35 wherein said wedges include side gussets extending back only in part from said ridge. 37. A damper according to claim 36 wherein said damper plate is imperforate. 38. A damper according to claim 36 wherein said damper plate is perforate. 39. A damper according to claim 36 wherein said damper further comprises an integral rib extending outwardly from said ridge along said damper plate.